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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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05-02-2020 дата публикации

Интеллектуальная система технического зрения беспилотного летательного аппарата для решения задач навигации, построения трехмерной карты окружающего пространства и препятствий и автономного патрулирования

Номер: RU0000195749U1
Автор: Денис Владимирович Тюляев, Евгений Сергеевич Бондаренко, Павел Вячеславович Скрибцов
Принадлежит: Общество с ограниченной ответственностью "МИРП-Интеллектуальные Системы"

Интеллектуальная система технического зрения беспилотного летательного аппарата предназначена для автоматического управления беспилотными летательными аппаратами на основе анализа данных, полученных из разных источников и в условиях недоступности сигналов глобальных навигационных спутниковых систем. Интеллектуальная система обладает функциями навигационной системы, системы технического зрения, системы мониторинга окружающего пространства, системы принятия решения и системы полуавтоматического и ручного управления БПЛА. Интеллектуальная система состоит из программно-аппаратного комплекса в составе бортового вычислителя на основе одноплатного компьютера с платой расширения на базе 32-разрядного контроллера, инерционного измерительного блока, позволяющего определить положение беспилотного летательного аппарата в пространстве и включающего в себя гироскоп, акселерометр, барометр, бортовой видеокамеры, RGB-D-камеры, полетного контроллера, приемника радиосигналов, вращающегося лазерного дальномера, стационарного лазерного дальномера, интерфейсов подключения устройств управления движением, интерфейсов подключения внешних датчиков. 2 з.п. ф-лы, 7 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 195 749 U1 (51) МПК B64C 13/10 (2006.01) B64C 19/02 (2006.01) G01C 23/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК B64C 13/00 (2019.08); B64C 19/02 (2019.08); G05D 1/00 (2019.08); G01C 23/00 (2019.08) (21)(22) Заявка: 2019122166, 15.07.2019 (24) Дата начала отсчета срока действия патента: Дата регистрации: (73) Патентообладатель(и): Общество с ограниченной ответственностью "МИРП-Интеллектуальные Системы" (RU) 05.02.2020 (45) Опубликовано: 05.02.2020 Бюл. № 4 1 9 5 7 4 9 R U (54) Интеллектуальная система технического зрения беспилотного летательного аппарата для решения задач навигации, построения трехмерной карты окружающего пространства и препятствий и автономного патрулирования (57) Реферат: Интеллектуальная система ...

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Номер записи: 1
04-10-2012 дата публикации

Flight Control Laws for Constant Vector Flat Turns

Номер: US20120253558A1
Автор: Kevin Thomas Christensen, Shyhpyng Jack Shue, Troy Sheldon Caudill
Принадлежит: BELL HELICOPTER TEXTRON INC

An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector across a ground surface. The aircraft includes a control system in data communication with control actuators, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The lateral control architecture controls the aircraft in the lateral direction, while the longitudinal control architecture controls the aircraft in the longitudinal direction. The initialization command logic automatically activates the lateral control architecture and the longitudinal control architecture to maintain a constant vector across the ground whenever a directional control input is made at low speed.

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Номер записи: 2
01-11-2012 дата публикации

Method and device of calculating aircraft braking friction and other relating landing performance parameters based on the data received from aircraft's on board flight data management system

Номер: US20120277937A1
Автор: Zoltán Iván Radó
Принадлежит: Aviation Safety Technologies LLC

This invention relates to a method and apparatus for the calculation of aircraft braking friction and other relating landing parameters, including but not limited to aircraft braking action, aircraft takeoff distance, aircraft landing distance, runway surface conditions and runway surface friction based on the data collected by and available in the aircraft Flight Data Recorder (FDR) or other flight data management system, for example, the Quick Access Recorder (QAR), to provide all involved personnel in the ground operations of an airport and airline operations, including but not limited to aircraft pilots, airline operation officers and airline managers as well as airport operators, managers and maintenance crews, with the most accurate and most recent information on the true aircraft landing performance parameters to help better and more accurate safety and economical decision making.

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Номер записи: 3
18-04-2013 дата публикации

RADIO CONTROLLED AIRCRAFT, REMOTE CONTROLLER AND METHODS FOR USE THEREWITH

Номер: US20130096736A1
Автор: Reynolds Michael D., Stuckman Katherine C.
Принадлежит:

A radio controlled (RC) vehicle includes a receiver that is coupled to receive an RF signal from a remote control device, the RF signal containing command data in accordance with a first coordinate system, wherein the first coordinate system is from a perspective of the remote control device. A motion sensing module generates motion data based on the motion of the RC vehicle. A processing module transforms the command data into control data in accordance with a second coordinate system, wherein the second coordinate system is from a perspective of the RC vehicle. A plurality of control devices control the motion of the RC vehicle based on the control data. 1. A radio controlled (RC) vehicle comprising:a receiver that is coupled to receive an RF signal from a remote control device, the RF signal containing command data in accordance with a first coordinate system, wherein the first coordinate system is from a perspective of a user of the remote control device;a motion sensing module, that generates motion data based on the motion of the RC vehicle;a processing module, coupled to the motion sensing module and the receiver, that transforms the command data into control data, based on the motion data, and in accordance with a second coordinate system, wherein the second coordinate system is from a perspective of the RC vehicle; anda plurality of control devices, coupled to the processing module, that control the motion of the RC vehicle based on the control data.2. The RC vehicle of wherein the command data includes roll-axis command data and pitch-axis command data claim 1 , the control data includes roll-axis control data and wherein the processor generates the roll-axis control data based on the roll-axis command data and pitch-axis command data.3. The RC vehicle of wherein the motion data includes yaw-axis motion data and the processor generates the roll-axis control data as a function of the roll-axis command data claim 2 , pitch-axis command data and the yaw-axis ...

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Номер записи: 4
02-05-2013 дата публикации

Energy Protection Device For An Aircraft

Номер: US20130110324A1
Автор: Moune Marie-Claire, MULLER Jean
Принадлежит: AIRBUS OPERATIONS SAS

The device () comprises means () for automatically deactivating an energy protection function and for automatically managing an autothrottle (), when the return of the aircraft in an operational flight domain is detected after the activation of the protection function. 2. The method according to claim 1 , the current corrected speed of the aircraft is larger, during at least one predetermined period of time, than the sum of a reference speed depending on the current flight configuration of the aircraft and of a predetermined threshold value; and', 'the conditions for triggering the energy protection are not longer achieved., 'wherein, at step c), a return of the aircraft back to said operational flight domain is detected, when the two following conditions are simultaneously met3. The method according to claim 1 ,wherein at step d):d1a) if the memorized engagement state indicates that the autothrottle was engaged upon triggering the protection function, said autothrottle is maintained engaged; andd1b) if the memorized engagement state indicates that the autothrottle was disengaged upon said triggering, said autothrottle is automatically disengaged, out of a particular situation of going around of the aircraft.4. The method according to claim 3 ,wherein, if the aircraft is in a go around situation in the case a return back to the operational flight domain is detected and if it is not in a smooth configuration, the autothrottle is maintained engaged at step d1b).5. The method according to claim 1 ,wherein at step d):d2a) if the memorized engagement state indicates that the autothrottle was engaged upon triggering the protection function, said autothrottle is maintained engaged; andd2b) with the exception of two particular situations, if the memorized engagement state indicates that the autothrottle was disengaged upon said triggering, said autothrottle is maintained engaged, but a target speed of the autothrottle is synchronized with a maneuver speed.6. The method ...

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Номер записи: 5
02-05-2013 дата публикации

Particle sensor for in situ atmospheric measurement

Номер: US20130110326A1
Автор: Roland Kelm
Принадлежит: AIRBUS OPERATIONS GMBH

A measuring device for an aircraft is provided in order to determine physical properties of aerosol particles in real time. The device includes a heating device that separates volatile and solid aerosol particles, and a particle sensor that measures acquired data. The physical properties of the solid aerosol particles are determined with an analyzer. The determined analytical data is forwarded to other internal aircraft systems via a communication interface. Due to the formation of a measuring data or analytical data network with several airliners equipped with the measuring device, accurate and up-to-date information on the particle pollution, for example, along flight paths, can be obtained and used for defining no-fly zones, if so required.

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Номер записи: 6
02-05-2013 дата публикации

Method And Device For Controlling Engine Speed Of An Aircraft During A Take-Off

Номер: US20130110327A1
Автор: Fernandez Brice
Принадлежит: AIRBUS OPERATIONS SAS

According to the invention, the device () comprises means () for automatically controlling the speed of engines (M to M) in such a way that, as long as all engines of an aircraft (AC) do not have, at least at given moment of a take-off, a driving parameter value (N to N) roughly equal to a preset intermediate value of said parameter (N), the speed of engines cannot exceed an intermediate speed associated with said preset intermediate value. 3. The method according to claim 1 , wherein the engines are turbojets claim 1 ,{'b': '1', 'wherein the driving parameter associated with the engines is the ratio EPR between the gas pressures at the outlet and at the inlet of the engines, or the rotation speed N of the fan of the engines.'}4. The method according to claim 1 ,wherein the take-off is initiated when the throttle levers respectively associated with the engines are brought in a position corresponding to the determined take-off speed.5. The method according to claim 1 ,wherein the detection step is carried out continuously during the whole take-off.8. An aircraft claim 1 ,{'claim-ref': {'@idref': 'CLM-00006', 'claim 6'}, 'wherein it comprises a controlling device such as specified in .'} The present invention relates to a method and a device for controlling engine speed in a multi-engine aircraft during a take-off, as well as an aircraft provided with such a device.Although the present invention is particularly adapted for airplanes provided with turbojets, it is by no way limited to such an application. It could be equally implemented on airplanes provided with turboprop engines.It is known that such turbojets are controlled by a reliable parameter, referred to as a driving parameter, representative of the thrust level of said turbojets and that there are two kinds of driving parameters, one of them being the ratio EPR between the gas pressure at the outlet and at the inlet of the turbojets and the other one being linked to the speed N of the fan thereof.For a ...

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Номер записи: 7
23-05-2013 дата публикации

APPARATUS, SYSTEM, AND METHOD FOR CONTROLLED INFRARED ILLUMINATOR

Номер: US20130129357A1
Автор: Belnap Carl I., Dean Lamont P.
Принадлежит: DESIGN CRITERIA, INC.

An apparatus for a controlled infrared illuminator includes an unmanned aerial system capable of sustained flight and an infrared light source coupled to the unmanned aerial system by attachment means. The infrared light source includes a plurality of laser diodes arranged in a pattern. The apparatus also includes a remote control that controls either the movements of the unmanned aerial system, the position of the infrared light source, or both. 1. An apparatus comprising:an unmanned aerial system capable of sustained periods of flight;an infrared light source coupled to the unmanned aerial system by attachment means, wherein the infrared light source comprises a plurality of laser diodes arranged in a pattern; anda remote control configured to control one or more of the movements of the unmanned aerial system and the position of the infrared light source.2. The apparatus of claim 1 , wherein the infrared light source provides one or more of light within the near infrared portion of the infrared spectrum and light within the mid infrared portion of the infrared spectrum.3. The apparatus of claim 1 , wherein the remote control adjusts one or more of the intensity and beam width of the infrared light source and is capable of turning the infrared light source on and off.4. The apparatus of claim 1 , wherein the infrared light source further comprises a control signal configured to receive claim 1 , translate claim 1 , and transmit one or more signals from the remote control to the infrared light source control.5. The apparatus of claim 1 , wherein subsets of the plurality of laser diodes are configured to alternately turn on and off such that the infrared light source processes more than one phase change.6. The apparatus of claim 5 , wherein the phase change of the infrared light source is controlled by at least one driver claim 5 , wherein each driver of the at least one drivers controls at least one laser diode.7. The apparatus of claim 1 , further comprising a ...

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Номер записи: 8
30-05-2013 дата публикации

PILOT CYCLIC CONTROL MARGIN DISPLAY

Номер: US20130134255A1
Автор: Conway Frank, Fortenbaugh Robert L., Greenwood Jeffery S.
Принадлежит: Bell Helicopter Textron Inc.

A system to control flight of an aircraft includes a rotor blade, an actuator operably associated with the rotor blade, a controller operably associated with the actuator, and a flight control system. The flight control system having a subsystem adapted to modify a flight control limit of the aircraft based upon detection of an impending hazardous flight condition and a display showing available flight control limits provided by modification of design control limits based upon the detection of the impending hazardous flight condition. The method includes generating the control limits, modifying the control limits based upon the impending hazardous flight condition, and displaying the displacement of actuator position relative to the displayed control limits thus cueing the pilot as to the cyclic stick or pedal inputs required to increase the control margin from the impending hazardous condition 1. A rotary aircraft , comprising:a rotor blade;an actuator operably associated with the rotor blade, the actuator being configured to change the pitch of the rotor blade;a controller operably associated with the actuator; and a subsystem configured to modify a flight control limit of the aircraft based upon detection of an impending hazardous flight condition; and', 'a display configured to display a symbol identifying a displacement location of the controller relative to the flight control limits, the display showing a flight control envelope configured to morph in response to the aircraft approaching the impending hazardous flight condition., 'a flight control system, having2. The aircraft of claim 1 , further comprising:a first sensor operably associated with the actuator and the subsystem; anda second sensor operably associated with the rotor blade and the subsystem;wherein the subsystem utilizes information from the first sensor and the second senor to determine whether an impending hazardous flight condition exists.3. The aircraft of claim 1 , further comprising:a ...

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Номер записи: 9
30-05-2013 дата публикации

FLIGHT CONTROL LAWS FOR AUTOMATIC HOVER HOLD

Номер: US20130138270A1
Автор: Caudill Troy Sheldon, Christensen Kevin Thomas, Shue Shyhpyng Jack
Принадлежит: Bell Helicopter Textron Inc.

A system and method to control hovering flight of a rotary aircraft. The system including a lateral speed hold loop, a longitudinal loop, a vertical control loop, and a directional loop. The method includes defining a first flight envelope having a first groundspeed threshold; defining a second flight envelope having a second groundspeed threshold, the second flight envelope being defined within the first envelope; engaging a hover hold with a control law hover hold architecture as the aircraft enters the first flight envelope; and engaging a position hold with a control law position hold architecture as the aircraft enters the second flight envelope. 1. A method to control hovering flight of a rotary aircraft , the rotary aircraft having a longitudinal controller and a lateral controller , the method comprising:defining a first flight envelope having a first groundspeed threshold;defining a second flight envelope having a second groundspeed threshold, the second flight envelope being defined within the first envelope;engaging an automatic hover hold with a control law hover hold architecture as the aircraft enters the first flight envelope; andengaging an automatic position hold with a control law position hold architecture as the aircraft enters the second flight envelope.2. The method of claim 1 , further comprising:maneuvering the rotary aircraft within the first envelope with a translational rate command, the translational rate command being adapted to control longitudinal flight of the rotary aircraft with movement of the longitudinal controller and lateral flight of the rotary aircraft with movement of the lateral controller.3. The method of claim 1 , further comprising:disengaging the translational rate command as the aircraft groundspeed exceeds the first groundspeed threshold.4. The method of claim 1 , wherein the first groundspeed threshold is 10 knots.5. The method of claim 1 , wherein the second groundspeed threshold is 1 knot.6. The method of claim 1 , ...

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Номер записи: 10
06-06-2013 дата публикации

Method, Device and System for Guaranteeing a Temporal Spacing Between an Aircraft and At Least One Reference Moving Object

Номер: US20130144518A1
Автор: DACRE-WRIGHT Benoît, DEKER Guy
Принадлежит: THALES

A method is provided for guaranteeing a temporal spacing between an aircraft and at least one reference moving object, said spacing needing to be guaranteed no later than at a point in the flight plan called the point of interception, with the aircraft following a current flight plan. The feasibility of guaranteeing the spacing at a date Tcour by regulating the speed of the aircraft while maintaining the current flight plan is verified in a first step. In a second step it is verified whether the date Tcour is contained within a feasibility range. In a third step the current flight plan is modified when the feasibility is not verified, a lateral trajectory between the current position Xcour of the aircraft and the point of interception being implemented in this case such that the spacing can be attained by regulating the speed. 1. A method for guaranteeing a temporal spacing between an aircraft and at least one reference moving object , said spacing needing to be guaranteed no later than at a point in the flight plan called the point of interception , with the aircraft following a current flight plan , wherein the feasibility of guaranteeing the spacing at a date Tcour by regulating the speed of the aircraft while maintaining the current flight plan is verified comprising at least the following steps:determining two speed profiles Tmin(X), Tmax(X) which comply with the transit at a date ETAreq which guarantees the spacing and which is associated with the point of interception, a speed profile being composed of points indexed by a date and a position index, the two speed profiles Tmin(X), Tmax(X) being determined by taking into account the minimum speed and maximum speed, respectively, which the aircraft can attain,verifying whether the date Tcour is contained within a feasibility range, the two limits Bmin, Bmax of which are respectively equal to the values taken by the two speed profiles Tmin(X) and Tmax(X) for the position Xcour of the aircraft at the date Tcour, ...

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Номер записи: 11
20-06-2013 дата публикации

System for assisting the pilot of an aircraft by haptic means

Номер: US20130154319A1
Автор: Christian NOUVEL, Guillaume Lapeyronnie, Jean-Paul Berger
Принадлежит: Thales SA

The invention relates to a system for assisting the pilot of an aircraft, which comprises aboard the aircraft: a computer, a set of sensors able to provide data to the computer and, a seat for the pilot equipped with haptic actuators controlled by the computer. The computer comprises means for controlling each actuator or groups of actuators independently of one another, as a function of the data provided by the sensors. The seat comprising a back and a cushion, the actuators of the back and of the cushion comprise single-axis mini-rams distributed in the back and the cushion of the seat, whose displacement axes are respectively perpendicular to the back and to the cushion of the seat.

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Номер записи: 12
20-06-2013 дата публикации

Energy Management On Board an Aircraft

Номер: US20130158750A1
Автор: Joel Bosson, Vincent Gomez
Принадлежит: Liebherr Aerospace Toulouse SAS, Thales SA

Energy management on board an aircraft includes: a plurality of thermal and electrical energy sources, a plurality of loads which are capable of being supplied with power by the various energy sources, among which at least one load is capable of being supplied with power by an electrical energy source and by a thermal energy source, and real-time management means for energy transfers from the various energy sources to the various loads as a function of the present and future energy requirement of the various loads and the present and future availability of the various sources, with the management means providing a permanent and standardized correlation between thermal and electrical energies.

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Номер записи: 13
27-06-2013 дата публикации

Aircraft with an arrangement of flow-influencing devices

Номер: US20130166110A1
Автор: Burkhard GÖLLING, Rudibert King, Ulrich Notger HEINZ, Wolfgang Nitsche
Принадлежит: AIRBUS OPERATIONS GMBH

An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device, wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment, wherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located.

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Номер записи: 14
27-06-2013 дата публикации

METHOD FOR CONTROLLING A HIGH-LIFT DEVICE OR A FLIGHT CONTROL SURFACE, SYSTEM AND AIRCRAFT OR SPACECRAFT

Номер: US20130166111A1
Автор: Fervel Marc, Ruckes Ina, Rumpf Tobias Sebastian
Принадлежит:

The present invention discloses a method for controlling a high-lift device or a flight control surface of an aircraft or spacecraft, especially with a system according to the present invention, comprising the steps of receiving, at at least one first control unit, a command signal from a commander unit via a data network, providing a primary control signal to at least one secondary control unit via the data network, wherein the primary control signal depends on the received command signal, receiving, at the at least one second control unit, a sensor signal of one or more sensors of the high-lift device or flight control surface, and providing a secondary control signal to one or more actuators of the high-lift device or flight control surface, wherein the secondary control signal depends on the received sensor signal. Furthermore, the present invention discloses a system and an aircraft or spacecraft. 1. A method for controlling a high-lift device or a flight control surface of an aircraft or spacecraft comprising the steps of:receiving, at at least one first control unit, a command signal from a commander unit via a data network;providing a primary control signal to at least one secondary control unit via the data network, wherein the primary control signal depends on the received command signal;receiving, at the at least one second control unit, a sensor signal of one or more sensors of the high-lift device or flight control surface; andproviding a secondary control signal to one or more actuators of the high-lift device or flight control surface, wherein the secondary control signal depends on the received sensor signal and the primary control signal.2. The method according to claim 1 , wherein providing a secondary control signal comprises providing at least one of the secondary control units in one actuator and/or one sensor claim 1 , the actuator and/or sensor being directly connected to the primary control unit via a data network or being indirectly ...

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Номер записи: 15
27-06-2013 дата публикации

Method and Device for Determining a Lateral Trajectory of an Aircraft and Associated Flight Management System

Номер: US20130166112A1
Автор: DEWAS Emmanuel, SAVARIT Vincent
Принадлежит: THALES

A method, and an associated device, is provided for the determination, by a flight management system of an aircraft, of a lateral trajectory of said aircraft on the basis of a predefined flight plan allowing consecutive conflicts to be resolved in an improved manner. This allows an improved lateral trajectory to be designed in the case where multiple trajectory conflicts exist. The trajectory obtained is closer to the flight plan defined by the pilot. The propagation of trajectory conflicts to the following flight segments is thus avoided. In fact, instead of propagating the trajectory conflict from one resolution to another, the method allows the conflict to be resolved in a space delimited at most by the input of the first conflict and the output of the last conflict. 1. A method for the determination , by a flight management system of an aircraft , of a lateral trajectory of said aircraft on the basis of a predefined flight plan , said flight plan comprising consecutive flight segments delimited by crossing points , said method comprising:calculating a first transition between a first segment and a second segment consecutive to the first segment and a second transition between the second segment and a third segment consecutive to the second segment,detecting a first conflict between the first transition and the second transition,if no conflict is detected, then returning to the transition calculation step applied to the second segment, to the third segment and to a fourth segment consecutive to the third segment,otherwise resolving the first detected conflict,calculating a third transition between the third segment and a fourth segment,detecting a second conflict between the second transition and the third transition,if no conflict is detected, then the return to the transition calculation step applied to the third segment, to the fourth segment and to a fifth segment consecutive to the fourth segment,otherwise jointly resolving the first conflict and the second ...

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Номер записи: 16
11-07-2013 дата публикации

MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL

Номер: US20130175390A1
Автор: Hollman Jeremy, Peverill James, Vulikh Greg, Woodworth Adam
Принадлежит: AURORA FLIGHT SCIENCES CORPORATION

An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. 17-. (canceled)8. An aerial vehicle for reducing impact loads , the aerial vehicle comprising:an airframe;a payload module coupled to the airframe via one or more passive engagement tabs;a ramp interface (i) disposed between the airframe and the payload module, and (ii) angled approximately 45 degrees to a typical impact load direction:,a plurality of contact pins interconnecting parallel conductive surfaces between the airframe and the payload module; anda battery module configured to interface with the airframe and the payload module,wherein the payload module and the battery module are configured to eject from the airframe during impact.9. The aerial vehicle of claim 8 , wherein the battery module is configured to eject from the airframe along an ejection path that does not intersect with another aircraft component.10. (canceled)11. The aerial vehicle of claim 8 , wherein the payload module comprises avionics and sensor payloads.12. The aerial vehicle of claim 8 , further comprising two or more thrust-vectoring modules for providing propulsion forces in an aerial vehicle claim 8 , each thrust vectoring module comprising a propeller claim 8 , an electric motor and a positioning device configured to position the electric motor.13. The aerial vehicle of claim 12 , ...

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Номер записи: 17
18-07-2013 дата публикации

METHOD FOR THE AUTOMATIC MONITORING OF AIR OPERATIONS NECESSITATING GUARANTEED NAVIGATION AND GUIDANCE PERFORMANCE

Номер: US20130184899A1
Автор: NICOLAS Arnaud, Raynaud Sylvain
Принадлежит: AIRBUS OPERATIONS (SAS)

A method is disclosed for automatic monitoring of a flight management assembly of an aircraft implementing air operations necessitating guaranteed navigation and guidance performance, wherein flight path data generated by first and second flight management systems respectively, are compared in order to check their consistency; first and second flight management systems transmit their flight path data to a third flight management system; the third flight management system receives a current position of the aircraft, calculates deviations between this current position and a flight path depending on the flight path data received from the first and second flight management systems, which it utilizes only if they are identical, and calculates, according to these deviations, guidance commands for slaving onto this flight path. Monitoring can compare deviations and guidance commands received from the first second and third flight management systems in order to be able to detect an inconsistency between them. 1. A method for automatic monitoring of a flight management assembly of an aircraft implementing air operations necessitating guaranteed navigation and guidance performance , the flight management assembly comprising a first flight management system and a second flight management system , which are independent , and which , in use , allow pilots of the aircraft to manage a flight plan of the aircraft and generate deviations and guidance commands , the flight management assembly comprising a third flight management system , wherein:a) flight path data generated by the first and second flight management systems respectively, are compared in order to check their consistency;b) the first and second flight management systems transmit their flight path data to the third flight management system;c) the third flight management system receives a current position of the aircraft, calculates deviations between this current position of the aircraft and a flight path depending on ...

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Номер записи: 18
18-07-2013 дата публикации

Vehicle energy control system with a single interface

Номер: US20130184900A1
Автор: Fabien Perrin, Florian Constans, Matthieu Mayolle
Принадлежит: AIRBUS OPERATIONS SAS

A system for controlling energy of a vehicle, for example an aircraft, characterized in that it comprises: a control interface ( 10 ), said control interface comprising a movable element ( 12 ) configured to move along a path ( 13 ), said path defining at least two path portions ( 14, 17 ) respectively associated with at least two combinations of actuators acting on the energy of said vehicle, at least one of said at least two combinations of actuators being associated according to a current phase of movement of the aircraft, and a control unit configured to generate an energy instruction according to a command associated with a current position of said movable element on one of said at least two path portions, and according to said current phase of movement of the vehicle, said instruction being for the associated combination of actuators.

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Номер записи: 19
18-07-2013 дата публикации

VEHICLE ENERGY AND POWER MANAGEMENT METHOD AND SYSTEM

Номер: US20130184901A1
Автор: Adgar Stephen, Self Kristian Alexander, Wall Derek Sean
Принадлежит: ROLLS-ROYCE PLC

A method of managing energy and/or power in a vehicle, including: one or more vehicle power systems adapted to control one or more power consuming components of the vehicle and one or more power producing components of the vehicle; and one or more propulsive power systems adapted to control a propulsive power unit of the vehicle. The method includes: proposing a vehicle route for a predetermined mission and/or destination; determining a time-based operational plan for each of the vehicle power consuming components; determining the power required by the vehicle power consuming components and the propulsive power required by the vehicle; determining the power required from the vehicle power producing components and the propulsive power required by the propulsive power unit as a function of time during the operational plan; and varying the proposed vehicle route and/or the operational plan to optimize a predetermined performance criterion for the vehicle. 1. A method of managing energy and/or power in a vehicle , the vehicle comprising:one or more vehicle power systems adapted to control one or more power consuming components of the vehicle and one or more power producing components of the vehicle; andone or more propulsive power systems adapted to control one or more propulsive power units of the vehicle,wherein the method comprises:(i) proposing a vehicle route for a predetermined mission and/or destination;(ii) determining a time-based operational plan;(iii) determining the power required by the vehicle power consuming components and the propulsive power required by the vehicle as a function of time during the operational plan;(iv) determining the power required from the vehicle power producing components and the propulsive power required by the propulsive power units as a function of time during the operational plan; and(v) varying the proposed vehicle route and/or the operational plan and repeating at least steps (iii) to (iv) to optimise a predetermined ...

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Номер записи: 20
25-07-2013 дата публикации

VEHICLE ENERGY CONTROL SYSTEM

Номер: US20130190949A1
Автор: BOURRET Thierry, Constans Florian, PERRIN Fabien
Принадлежит: AIRBUS OPERATIONS (SAS)

A system for controlling energy of a vehicle, for example an aircraft, comprising a control interface able to be in at least one first and one second state, the first state being an instruction state in which the interface generates at least a first instruction for speed of variation of a current energy of the vehicle and the second state being a resting state in which it gives no instruction, the interface furthermore being configured to return into the second state after having been brought into the first state. 1. A system for controlling energy of an aircraft comprising:{'b': 404', '805, 'a control interface (, ) for generating at least one first instruction for speed of variation of a current energy of the aircraft, and'}{'b': 401', '804', '409, 'a regulating unit (, ) for receiving said at least one first instruction and for controlling at least one device of the aircraft () to bring the aircraft to an energy in accordance with said at least one first instruction.'}wherein the control interface may be in at least one first and one second state, the first state being an instruction state in which the interface generates said at least one first instruction and the second state being a resting state in which it does not give any instruction and wherein the control interface is configured to return to the second state after having been brought into the first state.2. A system according to claim 1 , wherein the first instruction corresponds to a variation in thrust of at least one engine of the aircraft.3. A system according to claim 1 , wherein the first instruction corresponds to a command for an aerodynamic device of the aircraft.4. A system according to claim 1 , wherein the interface is configured to generate a second control instruction for a thrust value of at least one engine of the vehicle.5305003150136. A system according to claim 1 , wherein the interface comprises a lever ( claim 1 , ) configured to move angularly around a rotational axis ( claim 1 , ) ...

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Номер записи: 21
01-08-2013 дата публикации

MULTI-AXIS SERIALLY REDUNDANT, SINGLE CHANNEL, MULTI-PATH FLY-BY-WIRE FLIGHT CONTROL SYSTEM

Номер: US20130197722A1
Автор: De Serres Pierre, Lin Shu, Smith Timothy
Принадлежит: Bombardier Inc.

A multi-axis serially redundant, single channel, multi-path fly-by-wire control system comprising: serially redundant flight control computers in a single channel where only one “primary” flight control computer is active and controlling at any given time; a matrix of parallel flight control surface controllers including stabilizer motor control units (SMCU) and actuator electronics control modules (AECM) define multiple control paths within the single channel, each implemented with dissimilar hardware and which each control the movement of a distributed set of flight control surfaces on the aircraft in response to flight control surface commands of the primary flight control computer; and a set of (pilot and co-pilot) controls and aircraft surface/reference/navigation sensors and systems which provide input to a primary flight control computer and are used to generate the flight control surface commands to control the aircraft in flight in accordance with the control law algorithms implemented in the flight control computers. 1. A multi-axis fly-by-wire flight control system that generates flight surface commands to control the movement of a set of flight control surfaces to control the pitch , roll or yaw directional axes of an aircraft , the system comprising: [ (i) at least one servo loop assigned to said flight control path of the single flight control channel, said servo loop controlling the movement of at least one predetermined flight control surface such that the at least one servo loop in said control path operates to control the aircraft in at least one of the roll, pitch or yaw directional axes;', '(ii) at least one flight control surface controller that receives at least one of the cockpit controls signals and is coupled to said at least one servo loop; and, '(a) a plurality of control paths, each control path controlling a different subset of the set of flight control surfaces, each control path including, '(B) a single flight control channel ...

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Номер записи: 22
01-08-2013 дата публикации

METHOD AND DEVICE FOR AIDING THE PILOTING OF AN AIRCRAFT DURING A LANDING PHASE

Номер: US20130197727A1
Автор: ESSADOUNI Malika, MULLER Jean
Принадлежит: AIRBUS OPERATIONS (S.A.S.)

Method and device for aiding the piloting of an airplane during a landing phase for ensuring, during rollout on a landing runway, that in the nominal case the airplane will stop level with a selected exit, while guaranteeing that in the case of a fault the airplane will stop before the end of the runway. 2. The device as claimed in claim 1 , wherein said data comprise at least one of the following data:a value of ground speed of the airplane;an estimation of the distance between the airplane and the threshold of the runway used for landing;a value of length of the runway used for landing.3. The device as claimed in claim 1 , wherein said first means comprise a plurality of inertial reference systems able to generate ground speeds of the airplane claim 1 , as well as passivation means for providing a ground speed as given data claim 1 , solely in the case of consistency between the ground speeds arising respectively from said inertial reference systems.4. The device as claimed in claim 1 , wherein said first means comprise means which are integrated into said flight controls computer and which are formed so as to estimate the distance between the airplane and the threshold of the runway used for landing claim 1 , by integrating a ground speed.5. The device as claimed in claim 1 , wherein said first means comprise:storage means which are integrated into said flight controls computer and which store a value of length of the runway used for landing; anda display computer of the cockpit of the airplane, which receives this value and displays it on a screen of the flight deck.6. The device as claimed in claim 5 , wherein the display computer of the cockpit of the airplane is DAL A certified according to standard DO-178B.7. The device as claimed in claim 1 , wherein said second means compute said minimum deceleration on the basis of an estimation of the distance between the airplane and the threshold of the runway and of the length of the runway claim 1 , by implementing a ...

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Номер записи: 23
08-08-2013 дата публикации

CONTROL BOX

Номер: US20130200212A1
Автор: LECOURTIER Gilbert
Принадлежит: MESSIER-BUGATTI-DOWTY

The invention provides a control box for selectively delivering orders to receivers (), the control box comprising: 1812. A control box for selectively delivering orders to receivers ( , ) , the control box comprising:{'b': 14', '24, 'a shaft () mounted to turn about an axis of rotation (X), while being capable of sliding along said axis (X) between a rest position towards which it is urged by return means (), and an active position;'}{'b': 16', '11', '14', '14, 'order delivery means (, ) co-operating with the shaft () to deliver orders as a function of the angular position of the shaft ();'}{'b': '15', 'rotary drive means () for causing the shaft to turn; and'}{'b': 23', '27', '28', '27', '28', '15, 'safety actuation means () for causing the shaft to slide from the rest position in which anti-rotation means (, ) prevent the shaft from turning to the active position in which the anti-rotation means (, ) leave the shaft free to turn under drive from the rotary drive means ().'}22728271428282714282714. A control box according to claim 1 , wherein the anti-rotation means ( claim 1 , ) comprise longitudinal grooves () formed in a portion of the shaft () and co-operating with a stationary finger () of the control box so that the finger () is engaged in one of the grooves () when the shaft () is in the rest position and the finger () is disengaged from the grooves () when the shaft () is in the active position.3412714. A control box according to claim 2 , also including at least one retractable finger () adapted to penetrate selectively into one of the grooves () in order to prevent the shaft () from turning.44140. A control box according to claim 3 , wherein the retractable finger () is a moving portion of an electromechanical solenoid actuator ().53637381414. A control box according to claim 1 , further including detector means ( claim 1 , claim 1 , ) adapted to co-operate with the shaft () in order to detect whether the shaft () is in the rest position or in the active ...

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Номер записи: 24
15-08-2013 дата публикации

Display system

Номер: US20130211629A1
Автор: Keith David Stickels
Принадлежит: Individual

A display system for displaying a layout of controls in a simulator including at least one of an information display, a switch such as a toggle or push-button switch, and a monitoring device such as an indicator, or a gauge, for a vehicle, the display system including a touch sensitive screen which is generally transparent over a significant portion of its area, and a plurality of projectors which project onto a back of the screen, images of the vehicle controls, the projectors each being operatively connected to a computer controller which responds to the front of the screen being touched where a depicted control is displayed, to change the display in a manner to mimic the result of a corresponding actual vehicle control being operated.

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Номер записи: 25
15-08-2013 дата публикации

Integrated Aircraft Flight Control Units

Номер: US20130211631A1
Автор: Bradley D. Linton, Travis L. Yates
Принадлежит: BELL HELICOPTER TEXTRON INC

According to one embodiment, an integrated aircraft trim assembly features a shaft, a mechanical stop, a trim motor, a clutch, and a measurement device. The mechanical stop device is operable to at least partially prevent rotation of the shaft outside of an allowable range of motion. The trim motor has an output component in mechanical communication with the shaft. The clutch separates the trim motor from the shaft. The measurement device is proximate to the shaft and operable to measure a position of the shaft and communicate the measured position to a flight control computer operable to change a position of a flight control device.

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Номер записи: 26
15-08-2013 дата публикации

INTERACTIVE DIALOG DEVICES AND METHODS FOR AN OPERATOR OF AN AIRCRAFT AND A GUIDANCE SYSTEM OF THE AIRCRAFT

Номер: US20130211635A1
Автор: BOURRET Thierry, Chauveau Nicolas, Drieux Sebastien, Giuliano Sebastien, Louise Pascale, Ollagnon Claire
Принадлежит:

Interactive dialog devices and methods are provided for use by an operator of an aircraft with a guidance system of the aircraft. The dialog devices and methods can include an interaction on a screen that can represent, on the one hand, a playback element indicating the value of a guidance target of the guidance system of the aircraft, and on the other hand, a control element that can be grasped or selected and moved on a display along a path, such as for example a curve, by an operator to modify the value of the guidance target. 1. A method for performing one or more incremental adjustments on a guidance system of an aircraft , comprising:performing an approximate adjustment on a scale via a first interaction with a primary interaction element to modify at least one guidance target value of the guidance system;displaying at least one secondary interaction element; andperforming one or more incremental adjustments to the at least one guidance target value on the scale via a second interaction with the at least one secondary interaction element.2. The method of claim 1 , wherein the approximate adjustment is larger in value than the incremental adjustment.3. The method of claim 1 , wherein the primary interaction element is a control element that can be grasped or selected and moved by an operator.4. The method of claim 3 , wherein performing approximate adjustments comprises grasping or selecting and moving the primary interaction element along the scale.5. The method of claim 1 , further comprising of displaying at least one directional indicia associated with the at least one secondary interaction element.6. The method of claim 1 , wherein displaying at least one secondary interaction element comprises displaying a first secondary interaction element configured for making positive incremental adjustments on the scale claim 1 , and displaying a second secondary interaction element configured for making negative incremental adjustments on the scale.7. The method of ...

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Номер записи: 27
29-08-2013 дата публикации

Method and device of calculating aircraft braking friction and other relating landing performance parameters based on the data received from aircraft's on board flight data management system

Номер: US20130226430A1
Автор: Rado Zoltan Ivan
Принадлежит: Aviation Safety Technologies, LLC

This invention relates to a computer network for calculating and distributing the true braking coefficient of aircraft on runways and taxiways using, in part, the aircraft itself, by utilizing dynamic aircraft properties recorded on and obtained from the aircraft's flight data management system. Environmental and aircraft parameters may also be used to calculate the braking friction coefficient. A computer and network are used to obtain data and to calculate the friction coefficient, and may be used to distribute the result. The network may utilize, at least in part, wireless local area networks to facilitate data transfer and distribution of the result. The computer for calculating the braking coefficient may be located on the aircraft. 1. A computer network for calculating and distributing a true aircraft braking friction coefficient for an aircraft runway or taxiway comprising:(A) An aircraft having a flight data management system for recording one or more sets of data points thereon, wherein the one or more sets of data points pertain to one or more of the following aircraft properties measured at various times for the aircraft: aircraft ground speed, aircraft brake pressure, aircraft longitudinal acceleration, aircraft engine thrust setting, aircraft reverse thrust setting, aircraft engine revolutions per minute, aircraft air speed, aircraft vertical acceleration, aircraft spoiler setting, aircraft airbrake setting, aircraft aileron setting, aircraft flap configuration, aircraft pitch, and aircraft autobrake setting;(B) A computer which obtains the one or more sets of data points pertaining to the one or more aircraft properties; and(C) Wherein the computer calculates the true aircraft braking friction coefficient of the aircraft runway or taxiway using at least one of the one or more sets of the data points pertaining to the one or more aircraft properties obtained by the computer.2. The computer network for calculating and distributing the true aircraft ...

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Номер записи: 28
05-09-2013 дата публикации

SYSTEMS AND APPLICATIONS OF LIGHTER-THAN-AIR (LTA) PLATFORMS

Номер: US20130231106A1
Автор: BARKLEY Bruce Alan, FRISCHE Eric A., KNOBLACH Gerald M.
Принадлежит:

Innovative new methods in connection with lighter-than-air (LTA) free floating platforms, of facilitating legal transmitter operation, platform flight termination when appropriate, environmentally acceptable landing, and recovery of these devices are provided. The new systems and methods relate to rise rate control, geo-location from a LTA platform including landed payload and ground-based vehicle locations, and steerable recovery systems. 110-. (canceled)11. A method for determining a location of a device transmitting wireless signals to a plurality of free-floating lighter than air platforms comprising taking signal path delay measurements from the plurality of free-floating lighter than air platforms and determining the location of the device transmitting wireless signals based on the signal path delay measurements , wherein the plurality of free-floating lighter than air platforms have a speed relative to the surface of the earth of less than 100 miles per hour and float at an altitude of 60 ,000-140 ,000 feet , wherein the method does not require a Doppler shift correction.12. The method of claim 11 , wherein the signal path delay measurements are performed by measuring the difference between a time of arrival of a wireless signal of the device transmitting wireless signals and a standard time.13. The method of claim 11 , wherein the determining the location of the device transmitting wireless signals is based on the signal path delay measurements from at least three independent free-floating lighter than air platforms.14. The method of claim 11 , wherein the device transmitting wireless signals is located on (a) a free-floating lighter than air platform that has landed on the earth or (b) a ground-based vehicle claim 11 , and the device is a transmitter or a transceiver.15. The method of claim 11 , wherein the determining the location of the device transmitting wireless signals based on the signal path delay measurements comprises determining distances from ...

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Номер записи: 29
12-09-2013 дата публикации

VEHICLE CONTROL AND INTERFACE WITH MOBILE DEVICE

Номер: US20130238168A1
Автор: Reyes Jerome
Принадлежит:

A vehicle control system is described herein that uses a mobile computing device to interface with a remotely operated vehicle. The system provides a link between an existing device with Wi-Fi or other networking to a radio controlled vehicle. The system provides an application that runs on the mobile device and uses the networking facilities of the device to send control information to receiving hardware attached to the vehicle. The system may also provide a receiving module that interfaces with an existing flight control module of the vehicle to allow a vehicle that was not specifically designed to be controlled by a mobile phone to have this capability added. Thus an operator unsophisticated in the flight of remote control vehicles can show up to a job site, deploy the vehicle, and have his or her mobile device guide the vehicle through a flight pattern that captures useful measurements. 1. A system as substantially shown and described herein , and equivalents thereof.2. A method as substantially shown and described herein , and equivalents thereof. The present application claims the benefit of U.S. Provisional Patent Application No. 61/608,104 (Attorney Docket No. ROOFERS002) entitled “VEHICLE CONTROL AND INTERFACE WITH MOBILE DEVICE,” and filed on 2012-03-07, which is hereby incorporated by reference.Measurements are obtained for a variety of types of purposes, including by contractors bidding on construction work. One area where measurements are useful for determining job costs is in the field of roofing. Currently, measurements are obtained by placing personnel on the roof to manually walk the roof and take measurements. These measurements are later used to draw the roof based off notes, or provided to a paid service to draw the roof (potentially as it existed prior to any damage by using old photographs from satellites or fast moving airplanes from thousands of feet away).The current method does not give sufficient documentation or accuracy as additions to ...

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Номер записи: 30
12-09-2013 дата публикации

METHOD AND DEVICE FOR DISPLAYING SPEED INFORMATION ON AN AIRCRAFT

Номер: US20130238171A1
Автор: MULLER Jean, Poujol Christophe
Принадлежит: AIRBUS OPERATIONS (SAS)

The display device () comprises means () for correcting an acceleration value used for displaying on a screen () a speed trend of the airplane, making it possible to zero a speed trend symbol () when the Mach number of the airplane does not vary. This application is based on and claims priority from France Application No. 12 51322, filed on Feb. 13, 2012, the entire contents of which is incorporation herein by reference.The present invention relates to a method and a device for displaying speed information on an airplane, in particular a transport airplane.It is known that, on new-generation airplanes, the air speed of the airplane is presented to the pilot on a piloting screen, of PFD (“Primary Flight Display”) type, which is installed on the instrument panel of the flight deck.The air speed displayed is an air speed of CAS (for “Calibrated Airspeed”, namely a corrected speed) type, that is to say an equivalent of airplane dynamic pressure, and not simply the relative speed of the airplane with respect to the air molecules.In order to enhance the speed indication, the speed information display devices of modern airplanes carry out, in general, in addition a display of a speed trend, in the form of a trend arrow, which indicates the speed that the airplane will have in a predetermined duration, for example in ten seconds, if it retains a constant air acceleration. The size of this trend arrow is therefore proportional to the variation in the speed.Most of the time, during a descent, the airplane flies firstly at constant Mach (either the optimal Mach number for a nominal descent, or the maximum operational Mach number for an emergency descent), and then it flies at constant CAS speed (either the optimal speed for a nominal descent, or the maximum operational speed for an emergency descent).A drawback of the display in terms of speed (CAS) and speed derivative (speed trend arrow) is that, when the airplane descends on an iso-Mach, that is to say with a constant Mach ...

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Номер записи: 31
19-09-2013 дата публикации

METHOD AND APPARATUS FOR CONVERSION OF GPS HEADING DATA FOR USE BY ELECTRONIC FLIGHT DIRECTOR

Номер: US20130245859A1
Автор: STRICKLING James Eugene
Принадлежит:

An improved Horizontal Situation Indicator (HSI) module for use with an aircraft, wherein the HSI module is adapted for accepting Bank Angle Commands or waypoint data from the GPS flight module and for using the same to determine a heading error. The HSI module is further adapted for outputting the heading error to the Flight Director module where it can be used to create a Roll Command for output to the Auto-Pilot, whereby the Auto-Pilot can be commanded to follow a turn using the HSI and the Flight Director without requiring an additional module be added to the aircraft to create the heading error for use by the Flight Director. The waypoint data can be of the “flyover” type or the “flyby” type. 1. A method for use with an aircraft having an Auto-Pilot , a Horizontal Situation Indicator (HSI) module , a Flight Director module and display , and a GPS flight module which outputs a Bank Angle Command and/or waypoint data , the method comprising the steps of:a. the HSI module accepting a Bank Angle Command and/or waypoint data from the GPS flight module;b. the HSI module using the Bank Angle Command and/or waypoint data to determine a heading error;c. the HSI module outputting the heading error to the Flight Director module;d. the Flight Director module creating a Roll Command from the heading error; ande. the Flight Director Module outputting the Roll Command to the Auto-Pilot.2. The method as claimed in wherein the aircraft also has an Attitude Director Indicator claim 1 , the method further comprising outputting the Roll Command from the Flight Director to the Attitude Director Indicator.3. The method as claimed in further comprising outputting the Heading Error to the Flight Director display.4. The method as claimed in wherein the Heading Error outputted to the Flight Director display is outputted by the Flight Director module.5. The method as claimed in wherein a Bank Angle Command is generated by the aircraft's GPS Flight module and the HSI module uses the Bank ...

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Номер записи: 32
26-09-2013 дата публикации

INTEGRATED WAFER SCALE, HIGH DATA RATE, WIRELESS REPEATER PLACED ON FIXED OR MOBILE ELEVATED PLATFORMS

Номер: US20130248656A1
Автор: Mohamadi Farrokh
Принадлежит:

Methods and systems are provided for relocatable repeaters for wireless communication links to locations that may present accessibility problems using, for example, small unmanned aerial systems (sUAS). An sUAS implemented as an easy-to-operate, small vertical take-off and landing (VTOL) aircraft with hovering capability for holding station position may provide an extended range, highly secure, high data rate, repeater system for extending the range of point-to-point wireless communication links (also referred to as “crosslinks”) in which repeater locations are easily relocatable with very fast set-up and relocating times. A repeater system using beam forming and power combining techniques enables a very high gain antenna array with very narrow beam width and superb pointing accuracy. The aircraft includes a control system enabling three-dimensional pointing and sustaining directivity of the beam independently of flight path of the aircraft. 1. A system comprising:an aircraft having a plurality of wing unit propellers for vertical takeoff and landing;a flight control system included in the aircraft for controlling flight of the aircraft both autonomously and from an operator location remote from the aircraft; and a first RF receiver configured to receive a first high-data rate, multiplexed, data signal using a planar array of low noise amplifiers and corresponding antenna arrays to form spatial power combining from a narrow beam transmitter on a first channel;', 'a first RF transmitter configured to transmit the first high-data rate, multiplexed, data signal using a planar array of power amplifiers and corresponding antenna arrays to form spatial power combining and beam forming on the first channel;', 'a second RF receiver configured to receive a second high-data rate, multiplexed, data signal using a planar array of low noise amplifiers and corresponding antenna arrays to form spatial power combining from a narrow beam transmitter on a second channel;', 'a second ...

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Номер записи: 33
26-09-2013 дата публикации

Computing device and method for controlling unmanned aerial vehicle in flight space

Номер: US20130253733A1
Автор: Chang-Jung Lee, Chih-Ping Lo, Hou-Hsien Lee
Принадлежит: Hon Hai Precision Industry Co Ltd

In a method for controlling an unmanned aerial vehicle (UAV) in a flight space using a computing device, a 3D sample database is created and store in a storage device of the computing device. The computing device includes a depth-sensing camera that captures a 3D scene image of a scene in front of a user, and senses a depth distance between the user and the depth-sensing camera. A 3D person image of the user is detected from the 3D scene image, and gesture information of the user is obtained by comparing the 3D person image with human gesture data stored in the 3D sample database. The method converts the gesture information of the user into one or more flight control commands, and drives a driver of the UAV to control the UAV to fly in a flight space according to the flight control commands

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Номер записи: 34
03-10-2013 дата публикации

VEHICLE MANAGEMENT SYSTEM USING FINITE STATE MACHINES

Номер: US20130261853A1
Автор: Shillings John J., Shue Shyhpyng Jack
Принадлежит: Bell Helicopter Textron Inc.

A system includes a plurality of actuators and a management system operably associated with the plurality electronic and mechanical devices. The management architecture includes interfaces configured to the entire electronics and mechanics to provide a parameter to a computer. The computer includes a control and management architecture using modular finite state flow designs configured to analyze the parameter. The computer with a plurality of finite state machines can conduct a plurality of control laws operably associated with one or more actuators for finite functions of mobility. The method includes matching the parameter with the finite state machine and controlling the actuator via control law operably associated with finite state machine. The method can therefore be achieved either manually, semi-autonomously and autonomously with seamless and switchless control using a central control computer with integration of electronic and mechanic sensors and devices. 1. A vehicle , comprising:a plurality of actuators; and an interface configured to provide a parameter; and', a plurality of finite state machines; and', 'a plurality of control laws operably associated with one or more actuators;, 'a control architecture configured to analyze the parameter, the control architecture having, 'a computer operably associated with the interface, the computer having, 'wherein the computer is configured to selectively match the parameter to a finite state machine in the plurality of finite state machines;', 'wherein the finite state machine is operably associate with a control law in the plurality of control laws; and', 'wherein the control law is configured to provide command to one or more actuators of the plurality of actuators., 'a management system, having2. The vehicle of claim 1 , the plurality of finite state machines comprising:an automatic mode selection state machine configured to override control of the vehicle during normal operation situations.3. The vehicle of ...

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Номер записи: 35
10-10-2013 дата публикации

METHOD AND A DEVICE FOR ADAPTING THE MAN-MACHINE INTERFACE OF AN AIRCRAFT DEPENDING ON THE LEVEL OF THE PILOT'S FUNCTIONAL STATE

Номер: US20130268146A1
Автор: Baudry Jean-Pierre
Принадлежит: EUROCOPTER

A method of adapting a man-machine interface () of an aircraft () depending on the functional level of a pilot, the method comprising a plurality of successive steps. Firstly, before starting a mission, the characteristics of said mission and the characteristics and the physiological state of said pilot are determined. Thereafter, during said mission, the state of the mission and the current state of said aircraft together with a current behavior of said pilot are determined and a current functional level of said pilot is estimated. Thereafter, said current functional level of said pilot is compared with reference functional levels, and said man-machine interface () is then adapted in order to assist said pilot automatically and in optimum manner in making the pilot aware of the situation, in the pilot's decision-making, or in the actions taken by the pilot depending on the pilot's stress state or work load state. 1. A method of adapting a man-machine interface of an aircraft , the method comprising:a first step, performed before starting a mission, of determining the characteristics of said mission and the characteristics of said pilot and the pilot's initial physiological state;a second step of determining the state of advance of said mission and a current state of said aircraft together with a current behavior of said pilot during said mission;a third step of determining a current functional level of said pilot CFLP by using said characteristics of said mission, said characteristics and said initial physiological state of said pilot, said state of advance of said mission, said current state of said aircraft, and said current behavior of said pilot;a fourth step of determining a comparison value CV as a function of said current functional level CFLP;a fifth step of comparing said comparison value CV with at least one reference functional level ValRef; anda sixth step of acting on said man-machine interface as a function of said comparison value CV and of each ...

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Номер записи: 36
17-10-2013 дата публикации

EXTENSION OF THREE LOOP CONTROL LAWS FOR SYSTEM UNCERTAINTIES, CALCULATION TIME DELAY AND COMMAND QUICKNESS

Номер: US20130274963A1
Автор: Schillings John J., Shue Shyhpyng Jack
Принадлежит: Bell Helicopter Textron Inc.

A system includes a plurality of actuators and a control system operably associated with the plurality of actuators. The control system having a control logic architecture having a dynamic command input shaping model associated with an input command, a robust inner loop associated with the dynamic command input shaping model, and a time delay cancellation model. The method includes selecting a control law based upon a flight performance of an aircraft, decoupling the control law into a first individual component and a second individual component of the aircraft flight motion, analyzing each individual component separately, regrouping the component of flight motion, analyzing the control law with a time delay cancellation model and providing the necessary dynamic flight quickness with a different command input condition. 1. A vehicle , comprising:a plurality of actuators; and a dynamic command input shaping model associated with an input command;', 'a robust inner loop associated with the dynamic command input shaping model; and', 'a time delay cancellation model;, 'a control system operably associated with at least one actuator of the plurality of actuators, the control system having a control logic architecture havingwherein the input command is received by the control system, analyzed with the control logic architecture, and thereafter commands the at least one actuator of the plurality of actuators.3. The vehicle of claim 1 , wherein the command is an autonomous command.4. The vehicle of claim 1 , wherein the vehicle is an aircraft.5. The vehicle of claim 4 , wherein the command is a pilot command.6. The vehicle of claim 1 , wherein the dynamic command input shaping model comprises a plurality of dynamic model transfer functions.7. The vehicle of claim 6 , wherein the dynamic command input shaping model is configured to switch the pilot command between a plurality of model transfer functions of the dynamic model transfer function for a rapid vehicle response.8. ...

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Номер записи: 37
17-10-2013 дата публикации

AUTOMATED TAKE OFF CONTROL SYSTEM AND METHOD

Номер: US20130274965A1
Автор: Griffith Scot, Stange Kent
Принадлежит: HONEYWELL INTERNATIONAL INC.

Methods and systems for operating an avionics system on-board an aircraft are provided. In one embodiment, data associated with a take off roll is received, one or more v-speeds of the aircraft associated with the take off roll are calculated, and during the take off roll, the aircraft is controlled based on the one or more calculated v-speeds. 1. A method for controlling an aircraft during an automated take off , the method comprising:receiving data associated with the aircraft during a take off roll;calculating one or more v-speeds of the aircraft associated with the take off roll; andduring the take off roll, controlling the aircraft based on the one or more calculated v-speeds.2. The method of claim 1 , wherein at least some of the data is received during the take off roll.3. The method of claim 2 , wherein the received data comprises real-time aircraft performance data claim 2 , environmental conditions claim 2 , geographical data claim 2 , or a combination thereof.4. The method of claim 3 , wherein calculating of the one or more v-speeds comprises continuously computing the one of more v-speeds in real-time.5. The method of claim 3 , further comprising aborting the take off if any of the received data exceeds a predetermined threshold.6. The method of claim 3 , further comprising receiving one or more estimated v-speeds from a user input device on-board the aircraft.7. The method of claim 6 , further comprising:comparing the one or more calculated v-speeds to the one or more estimated v-speeds; andgenerating an indication if a difference between the one or more calculated v-speeds and the one or more estimated v-speeds is greater than a predetermined threshold.8. A system for controlling an aircraft during an automated take off claim 6 , the system comprising: receiving data associated with the aircraft during a take off roll;', 'calculating one or more v-speeds of the aircraft associated with the take off roll; and', 'during the take off roll, controlling the ...

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Номер записи: 38
24-10-2013 дата публикации

STANDBY INSTRUMENT FOR AN AIRCRAFT, THE INSTRUMENT PROVIDING FLIGHT INFORMATION, POWER MARGIN INFORMATION, AND ASSISTANCE IN PILOTING

Номер: US20130282205A1
Автор: Bailly Stephane, GERMANETTI Serge, SALESSE-LAVERGNE Marc
Принадлежит: EUROCOPTER

A standby instrument () for an aircraft, the instrument comprising at least one inertial sensor (), at least one pressure sensor (), calculation means () connected to said inertial and pressure sensors (), a display unit (). Said calculation means () are suitable for determining critical flight information for said aircraft, and for displaying said critical flight information on the display unit () in the event of a main information system of said aircraft failing. In addition, said standby instrument () also incorporates stabilization relationships enabling said calculation means () to determine control relationships in order to control the actuators () of an autopilot of said aircraft in the event of said autopilot failing. Finally, said calculation means () are connected to at least one engine operation computer () enabling said instrument () to display information about a first limit of the engine on said display unit (). 1. A standby instrument for an aircraft , the instrument comprising:at least one inertial sensor;at least one pressure sensor;calculation means to which said inertial and pressure sensors are connected and suitable for determining critical flight information for said aircraft;a memory connected to said calculation means; anda display unit capable of displaying said critical flight information in the event of a failure of a main information system of said aircraft;wherein the standby instrument incorporates in said memory stabilization relationships enabling said calculation means to determine stabilization control relationships in order to control actuators of an autopilot of said aircraft in the event of said autopilot failing, said calculation means including at least one output suitable for being connected to said actuators, said calculation means also including at least one input suitable for being connected to at least one FADEC engine computer enabling said standby instrument to display information on said display unit about a first ...

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Номер записи: 39
24-10-2013 дата публикации

Fully Parametrizable Electronic Alerts and Procedures Management System, Intended for an Aircraft

Номер: US20130282207A1
Автор: Michel Mazenoux, Stephane Bertheau, Xavier Chazottes
Принадлежит: Thales SA

An alerts and procedures management system for an aircraft comprises a software kernel aboard the aircraft and a parameterization tool for the software kernel, which comprises a conversion module for converting a configuration file describing an operational need of the system into a database of binary parameters which is able to parameterize the software kernel. The software kernel comprises at least four elementary cells: a first cell for acquiring aircraft signals, a second cell for characterizing state variables of the aircraft, a third cell for computing at least one separate event, a fourth cell for scheduling the separate events for communication with the crew; each of the cells comprising a software engine parameterizable by the database.

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Номер записи: 40
14-11-2013 дата публикации

Method for controlling the piloting of an aircraft

Номер: US20130304283A1
Автор: Eberle Matthias, MANJON SANCHEZ Javier, PERRIN Fabien, Puyou Guilhem
Принадлежит: AIRBUS OPERATIONS (SAS)

A method for controlling the piloting of an aircraft comprising the steps of receiving at least one first instruction for modification of a current velocity vector of the aircraft, determining a target velocity vector of the aircraft, on the basis of said at least one first instruction received, and determining, on the basis at least of said target velocity vector, at least one actuation command intended for at least one actuator of the aircraft in order to modify the movement of the aircraft according to said at least one first instruction received. 1. A method for controlling the piloting of an aircraft comprising the steps of:receiving at least one first instruction for modification of the orientation of a current velocity vector of the aircraft,determining a target velocity vector of the aircraft, on the basis of said at least one first instruction received, anddetermining, on the basis at least of said target velocity vector, at least one actuation command intended for at least one actuator of the aircraft in order to modify the movement of the aircraft according to said at least one first instruction received,the method further comprising the following steps of:receiving an instruction for modification of the orientation of the predetermined target velocity vector, andmodifying the target velocity vector as a function of said command received, said actuation command being determined on the basis of the thus-modified target velocity vector.2. The method according to claim 1 , in which said at least one actuator is capable of setting a control surface of the aircraft in motion.3. The method according to claim 1 , in which at least one instruction for modification of the current velocity vector of the aircraft relates to a flight path track angle.4. The method according to claim 1 , in which at least one instruction for modification of the current velocity vector of the aircraft relates to a flight path angle.5. The method according to claim 1 , further ...

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Номер записи: 41
21-11-2013 дата публикации

AUTOMATIC ATTITUDE CONTROL OF ROTARY WING AIRCRAFTS

Номер: US20130306787A1
Автор: Marton Trygve Frederik, Mellem Geir Morten Egeberg, Muren Petter, Paulsen Dag Henning, Sandberg Pal Hagh
Принадлежит: PROX DYNAMICS AS

A method and device for precise control of and controller design for aircrafts consisting of at least one spinning part and at least one non spinning part is provided. The required torques for control of the spinning parts and for the non-spinning parts are continuously and individually calculated. All torques are combined to get the correct torque for the complete aircraft. Doing this, it's possible to continuously apply the correct torque, both correctly distributed among the roll and pitch axes (correct angle), and correct magnitude. The result is a decoupling of the roll and pitch axes, simplifying controller design to a design of two single input single output controllers, one for each axe. 1. A flight control device outputting actuator steering commands in the yaw , pitch and roll domain from an angular velocity rate control input (wi) controlling a rotary wing aircraft comprising at least one rotor and one fuselage , the flight control device comprising:a rate controller deriving requested angular velocity (w) and angular acceleration (wdot) from wi and a measured velocity rate (wg);an actuator controller deriving actuator steering commands by an aerodynamic function (F2) being modeled by at least the aerodynamics of the rotary wing aircraft; anda torque controller device deriving required torque (T) corresponding to w and wdot by a torque function F1 being dependent of w, wdot, the inertia of the fuselage (If) and the inertia of the rotor (Ir), the torque function device being coupled between the rate controller and the actuator controller, having the outputs w and wdot from the rate controller as inputs and providing T as input to the actuator controller.2. The flight control device of claim 1 , wherein the torque controller device further comprises:a first matrix multiplier multiplying If and wdot resulting in a fuselage torque (Tf2) required to achieve one of the requested angular acceleration and motion;a first adder adding the angular velocity (wf) of ...

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Номер записи: 42
21-11-2013 дата публикации

TRIPLEX COCKPIT CONTROL DATA ACQUISITION ELECTRONICS

Номер: US20130311006A1
Автор: Ahmad Zafar S., Bader Douglas L., Roltgen John W., Singer Mark C.
Принадлежит: ROCKWELL COLLINS, INC.

A system and method are provided for controlling aircraft flight control surfaces. The system may include at least three pilot sensor channels, each pilot sensor channel including a set of pilot sensor data. The system may also include at least three aircraft sensor channels, each aircraft sensor channel including a set of aircraft sensor data. The system may further include an actuator control component configured to synchronously receive and vote on the pilot sensor data and the aircraft sensor data, such that a voted output of the at least three pilot sensor channels is transmitted to a flight control computer and augmented before being transmitted to remote electronics units. The voted output of the at least three pilot sensor channels providing for the control of the aircraft surfaces coupled to the remote electronics units. 1. A system for controlling aircraft flight control surfaces , comprising:at least three pilot sensor channels including a first channel containing a first set of pilot sensor data, a second channel containing a second set of pilot sensor data, and a third channel containing a third set of pilot sensor data;at least three aircraft sensor channels including a primary channel containing a first set of aircraft sensor data, a secondary channel containing a second set of aircraft sensor data, and a tertiary channel containing a third set of aircraft sensor data; anda first actuator control component operatively connected to the at least three pilot sensor channels and the at least three aircraft sensor channels and configured to synchronously receive and vote on the pilot sensor data from each of the at least three pilot sensor channels and the aircraft sensor data from each of the at least three aircraft sensor channels, such that a voted output of the at least three pilot sensor channels is transmitted to a flight control computer and augmented before being transmitted to remote electronics units, the voted output of the at least three pilot ...

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Номер записи: 43
21-11-2013 дата публикации

FLIGHT TECHNICAL CONTROL MANAGEMENT FOR AN UNMANNED AERIAL VEHICLE

Номер: US20130311009A1
Автор: Feist Jon, McAndrew Katherine, Moorman A. Christopher, Watson Linda J.
Принадлежит: HONEYWELL INTERNATIONAL INC.

Two architectures for unmanned aerial vehicles (UAVs) and a method for executing a mission plan are provided. One architecture for a UAV includes a flight command and mission execution (FCME) component making strategic decisions, a flight technical control manager (FTCM) making tactical decisions and a vehicle management system (VMS) providing navigational support. The FCME and FTCM execute on one processor and the VMS executes on a separate processor. The second architecture includes redundant processors for executing the FCME and FTCM as well as redundant processors for executing the VMS. The UAV executes a mission plan, which may include flight plan(s), communication plan(s), weapons plan(s), sensor plan(s), and/or contingent flight plan(s). The UAV may control various optical sensors, training sensors, and lights as well. 120-. (canceled)21. An aerial vehicle comprising:a vehicle management system configured to navigate the aerial vehicle; and receive a mission plan comprising a flight plan and a contingency plan,', 'validate the mission plan by at least determining the mission plan includes the flight plan,', 'after determining the mission plan is valid, execute the mission plan by at least providing the mission plan to the vehicle management system, wherein the vehicle management system is configured to direct the aerial vehicle to travel along the flight plan, and', 'synchronize the first processor and the second processor., 'a redundant processing unit comprising a first processor and a second processor, wherein at least one of the first processor or the second processor is configured to22. The aerial vehicle of claim 21 , wherein the first processor is configured to synchronize the first processor and the second processor by at least communicating data to the second processor.23. The aerial vehicle of claim 22 , wherein the first processor is configured to synchronize the first processor and the second processor by at least communicating data to the second ...

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Номер записи: 44
28-11-2013 дата публикации

Automatic flight control for uav based solid modeling

Номер: US20130317667A1
Автор: Ezekiel Kruglick
Принадлежит: EMPIRE TECHNOLOGY DEVELOPMENT LLC

Technologies are generally described for controlling a flight path of a UAV based image capture system for solid modeling. Upon determining an initial movement path based on an estimate of a structure to be modeled, images of the structure to be modeled may be captured and surface hypotheses formed for unobserved surfaces based on the captured images. A normal vector and a viewing cone may be computed for each hypothesized surface. A set of desired locations may be determined based on the viewing cones for the entire structure to be modeled and a least impact path for the UAV determined based on the desired locations and desired flight parameters.

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Номер записи: 45
28-11-2013 дата публикации

Providing a description of aircraft intent

Номер: US20130317670A1
Автор: Enrique Juan Magana Casado, Francisco Navarro, Javier Lopez Leones, Juan Alberto Besada, Miguel Vilaplana
Принадлежит: Boeing Co

The present disclosure provides a computer-implemented method of generating a description of aircraft intent expressed in a formal language that provides an unambiguous description of an aircraft's intended motion and configuration during a period of flight. A flight intent description is parsed to provide instances of flight intent that span a flight segment, the flight segments together spanning the period of flight. The parsed flight intent is converted into parametric aircraft intent by generating an associated flight segment description for each flight segment that comprises instances of flight intent to close all associated degrees of freedom of motion and of configuration of the aircraft. At least some flight segment descriptions contain a parameter range, and the method further comprises optimising the parametric aircraft intent by determining an optimal value for the parameter of each parameter range.

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Номер записи: 46
28-11-2013 дата публикации

PROVIDING A DESCRIPTION OF AIRCRAFT INTENT

Номер: US20130317671A1
Автор: Besada Juan Alberto, Crespo Jesus, Frontera Guillermo, Lopez Leones Javier, Magana Casado Enrique Juan
Принадлежит: The Boeing Company

The present disclosure provides a computer-implemented method of generating a description of aircraft intent expressed in a formal language that provides an unambiguous description of an aircraft's intended motion and configuration during a period of flight. A description of flight intent is parsed to provide instances of flight intent, each instance of flight intent spanning a flight segment. For each flight segment, an associated flight segment description is generated that comprises one or more instances of flight intent that describe the aircraft's motion in at least one degree of freedom of motion. Flight segment descriptions are compared with constraints and/or objectives and the associated flight segment descriptions are enriched with information describing relevant constraints and/or objectives. The enriched flight intent is converted into aircraft intent by ensuring that the flight segment descriptions close all degrees of freedom of the aircraft during the period of flight. 1. A computer-implemented method of generating a description of aircraft intent expressed in a formal language that provides an unambiguous description of an aircraft's intended motion and configuration during a period of flight , comprising:obtaining a description of flight intent corresponding to a flight plan spanning the period of flight;ensuring that the flight intent description is parsed to provide instances of flight intent, each instance of flight intent spanning a flight segment with the flight segments together spanning the period of flight;for each flight segment, generating an associated flight segment description that comprises one or more instances of flight intent, wherein each instance of flight intent provides a description of the aircraft's motion in at least one degree of freedom of motion thereby closing the associated at least one degree of freedom of motion and/or provides a description of the aircraft's configuration to close at least one degree of freedom of ...

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Номер записи: 47
28-11-2013 дата публикации

PROVIDING A DESCRIPTION OF AIRCRAFT INTENT

Номер: US20130317672A1
Автор: Bernardos Barbolla Ana Maria, Besada Juan Alberto, Frontera Guillermo, Lopez Leones Javier, Magana Casado Enrique Juan, Navarro Francisco
Принадлежит: The Boeing Company

The present disclosure provides a computer-implemented method of generating a description of aircraft intent expressed in a formal language that provides an unambiguous description of an aircraft's intended motion and configuration during a period of flight. A description of flight intent is parsed to provide instances of flight intent, each instance of flight intent spanning a flight segment. For each flight segment, an associated flight segment description is generated that comprises one or more instances of flight intent that describe the aircraft's motion in at least one degree of freedom of motion. One or more instances of flight intent are added to flight segments to close all degrees of freedom of motion. The flight segment descriptions are collated thereby providing a description of aircraft intent for the period of flight expressed in a formal language. 1. A computer-implemented method of generating a description of aircraft intent expressed in a formal language that provides an unambiguous description of an aircraft's intended motion and configuration during a period of flight , comprising:obtaining a description of flight intent corresponding to a flight plan spanning the period of flight;ensuring that the flight intent description is parsed to provide instances of flight intent, each instance of flight intent spanning a flight segment with the flight segments together spanning the period of flight;for each flight segment, generating an associated flight segment description that comprises one or more instances of flight intent, wherein each instance of flight intent provides a description of the aircraft's motion in at least one degree of freedom of motion thereby closing the associated at least one degree of freedom of motion and/or provides a description of the aircraft's configuration to close at least one degree of freedom of configuration;identifying flight segments where not all degrees of freedom are closed and completing the identified flight ...

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Номер записи: 48
05-12-2013 дата публикации

LDV for Airdrops

Номер: US20130325213A1
Автор: CHANG Chia-Chen, CHANGKAKOTI Rupak, Dakin Daniel C., Dakin Elizabeth A., Dede Edgar K., Gatchell Peter, LECLAIR Lance, Mamidipudi Priyavadan, Panabakam Madhukiran, Rogers Philip L.
Принадлежит: Optical Air Data Systems, LLC

A method of using a light detection system for increasing the accuracy of a precision airdrop is described. Radiation is transmitted to target areas between an airborne vehicle and a dropzone target. Scattered radiation is received from the target areas. Respective wind characteristics are determined from the scattered radiation and a wind velocity map is generated, based on the respective wind characteristics, between the airborne vehicle, and at least the dropzone target. An aerial release point for the precision airdrop is computed based on the generated wind velocity map and a location of the dropzone target. 1. A method comprising:transmitting radiation to target areas between an airborne vehicle and a dropzone target;receiving scattered radiation from the target areas;determining respective wind characteristics of the scattered radiation from each of the target areas;generating a wind velocity map based on the respective wind characteristics between the airborne aircraft and at least the dropzone target; andcomputing an aerial release point for a precision airdrop based on the generated wind velocity map and a location of the dropzone target.2. The method of claim 1 , further comprising releasing a person or payload from the airborne vehicle at the computed aerial release point.3. The method of claim 2 , wherein the payload comprises at least one of supplies claim 2 , an explosive device claim 2 , fuel claim 2 , vehicles claim 2 , equipment claim 2 , and medical supplies.4. The method of claim 2 , wherein the payload comprises an actuator configured to steer the payload while in the air.5. The method of claim 1 , further comprising controlling the airborne vehicle based on the respective wind characteristics so as to reduce turbulence experienced by the airborne vehicle.6. The method of claim 1 , wherein the determining respective wind characteristics comprises determining a wind velocity at multiple points along an axis of one or more beams of radiation.7. ...

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Номер записи: 49
05-12-2013 дата публикации

SYSTEM AND METHOD FOR AUTHORIZING STOPPAGE OF PILOTING TASKS

Номер: US20130325216A1
Автор: DE BRITO Gabrielle, Hourlier Sylvain, RIEUNIER Camille, SACLE Jerome
Принадлежит:

A system and method for authorizing stoppage of piloting tasks performed by at least one pilot of an aircraft equipped with automatic piloting means is disclosed. A duration for which the stoppage is authorized is determined, the duration being determined based on the calculation of an instant of commencement of a next action, and the next action being an action not yet carried out that must be carried out first by the pilot. The duration is then displayed. 1. A system for authorizing stoppage of piloting tasks performed by at least one pilot of an aircraft equipped with automatic piloting means , the system comprising:means for determining a duration for which the stoppage is authorized, the duration being determined based on calculation of an instant of commencement of a next action, not yet carried out, that must be carried out first by the at least one pilot; andmeans for displaying the duration.2. The system of claim 1 , wherein the determining means are configured to determine the duration based on:values of parameters representative of a physical state of the at least one pilot,values of parameters representative of a meteorological condition over a flight path of the aircraft,values of parameters representative of air traffic over the flight path of the aircraft,values of parameters representative of an operating state of the aircraft, orvalues of parameters representative of a position of the aircraft and the flight path of the aircraft.3. The system of claim 2 , wherein the determining means comprise:means for comparing the values of the parameters with reference values; andmeans for summarizing results of the comparisons.4. The system of claim 1 , wherein the determining means are further configured to determine the duration based on messages exchanged between the aircraft and entities in charge of air traffic control.5. The system of claim 1 , wherein the display means are configured to be fixed to a control means of the aircraft or to be transported by ...

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Номер записи: 50
26-12-2013 дата публикации

AUTONOMOUS CONTROL OF UNMANNED AERIAL VEHICLES

Номер: US20130345920A1
Автор: Bergee Mark J., Duggan David S., Felio David A., Longhi Vince R., Pate Billy B., Petersen Jerry L.
Принадлежит: L-3 Unmanned Systems, Inc.

An autonomous control system for an unmanned aerial vehicle is provided. In one example, the control system includes a first control mode component configured to generate a first command to provide a first autonomous control mode for the unmanned aerial vehicle, a second control mode component configured to generate a second command to provide a second autonomous control mode for the unmanned aerial vehicle, and an intelligence synthesizer configured to resolve functional conflicts between the first and second autonomous control modes. 1. An autonomous control system for an unmanned aerial vehicle , the autonomous control system comprising:a first control mode component configured to generate a first command to provide a first autonomous control mode for the unmanned aerial vehicle;a second control mode component configured to generate a second command to provide a second autonomous control mode for the unmanned aerial vehicle; andan intelligence synthesizer configured to resolve functional conflicts between the first and second autonomous control modes.2. The autonomous control system of claim 1 , and further comprising:a control mode selection component for responding to an operator control mode selection input by transitioning between the first and second autonomous control modes.3. The autonomous control system of claim 1 , and further comprising:an autopilot system configured to process at least one of the first and second commands.4. The autonomous control system of claim 3 , and further comprising:a vehicle control component configured to actuate control devices of the unmanned aerial vehicle based on process commands received from the autopilot system.5. The autonomous control system of claim 3 , wherein the first and second commands comprise directionally descriptive control commands generated in response to command inputs.6. The autonomous control system of claim 1 , wherein the intelligence synthesizer is configured to prioritize commands from a plurality ...

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Номер записи: 51
02-01-2014 дата публикации

METHOD AND DEVICE FOR ASSISTING THE MISSION TRACKING OF AN AIRCRAFT

Номер: US20140005861A1
Автор: Babando Olivier, DRAMET Julien, Marinelli Mauro, MERE Jean-Claude
Принадлежит:

The device () comprises means () for computing deviations of a flight parameter with respect to a reference flight plan, by taking account of predictions, respectively for a plurality of flight data representing different origins, and display means () for simultaneously presenting the set of said deviations on a screen () of the flight deck of the aircraft, each time indicating the corresponding origin. 1. A method for assisting the mission tracking of an aircraft , according to which method , in the course of a flight of said aircraft , in an automatic manner:the actual values of parameters relating to said aircraft are measured; a prediction is carried out at the current flight point of said flight parameter, on the basis of the flight plan actually flown, taking account of said measured actual values; and', 'the deviation is computed between this prediction obtained on the basis of the flight plan actually flown and the value of said flight parameter that is representative of said reference flight plan, this deviation thus computed being a deviation of said flight parameter relating to the corresponding origin; and, 'for at least one flight parameter, deviations of said flight parameter with respect to a reference flight plan relating to a reference mission are computed, doing so by carrying out, for each of a plurality of flight data representing respectively different origins of deviations, each time the following operations{'b': '6', 'the set of deviations thus computed for said flight parameter is presented simultaneously on a screen () of the flight deck of the aircraft, each time indicating the corresponding origin.'}2. The method as claimed in claim 1 ,wherein said flight parameter represents one of the following parameters:the quantity of fuel at a given point; andthe transit time at a given point.3. The method as claimed in claim 1 ,wherein said flight data representing different origins of deviations, comprise at least some of the following data:the ...

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Номер записи: 52
02-01-2014 дата публикации

Method and Apparatus for Aircraft Sensor and Actuator Failure Protection Using Reconfigurable Flight Control Laws

Номер: US20140005862A1
Автор: Alan Carl Ewing, Eric Thomas Bird, John James Corrigan, Shyhpyng Jack Shue, Tommie Lynn Wood
Принадлежит: BELL HELICOPTER TEXTRON INC

A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators. An exemplary aircraft for using the method and apparatus of a reconfigurable flight control system is a quad tilt rotor. The quad tilt rotor provides a variety of redundant and back-actuators, as such, having a robust and highly qualified reconfigurable flight control system is very desirable.

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Номер записи: 53
09-01-2014 дата публикации

Method for aiding navigation making it possible to manage a vertical constraint in an anticipated manner

Номер: US20140012436A1
Автор: Christophe Pierre, Francois Coulmeau, Xavier Blanchon
Принадлежит: Thales SA

A method for aiding navigation is provided, implemented in a flight management system, for the construction of a vertical trajectory of an aircraft following a predetermined lateral trajectory between a departure point and an arrival point; the departure point and arrival point furthermore being characterized by predefined altitudes, respectively H d and H a , and predefined speeds, respectively V d and V a . The method comprises the steps of: selection of a transition manoeuvre in terms of altitude and speed from a predetermined list of manoeuvres; determination of a manoeuvre point P M on the lateral trajectory, of altitude H d and of speed V d , from which the transition manoeuvre must be initiated so as to allow the aircraft to reach at the arrival point the predefined speed V a and the predefined altitude H a .

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Номер записи: 54
23-01-2014 дата публикации

PROPELLER OPERATION

Номер: US20140023499A1
Автор: Collingbourne Peter Wayne
Принадлежит: BAE SYSTEMS plc

A method of and apparatus for operating a propeller, the propeller moving through a fluid, the method including: measuring a value of a property of the fluid (e.g. a parameter related to the density of the fluid); measuring a value of a parameter, the parameter related to one or more forces applied to the propeller (e.g. a torque applied to the propeller) or derived at least in part from the action of the propeller (e.g. a thrust produced by the action of the propeller, a drag produced by the action of the propeller, or a velocity produced by the action of the propeller); and controlling the propeller depending on a function of the measured value of the property of the fluid and the measured value of parameter. The propeller may be a propeller on an aircraft. 118-. (canceled)19. A method of operating a propeller , the propeller moving through a fluid , the method comprising:measuring a value of a property of the fluid;measuring a value of a parameter, the parameter related to one or more forces applied to the propeller or derived at least in part from action of the propeller; andcontrolling the propeller depending on a function of the measured value of the property of the fluid and the measured value of parameter.20. A method according to claim 19 , wherein the measuring a value of the parameter comprises:measuring a value for thrust produced at least in part by the action of the propeller.21. A method according to claim 19 , wherein the measuring a value of the parameter comprises:measuring a value of a parameter related to drag produced at least in part by the action of the propeller.22. A method according to claim 19 , wherein the measuring a value of the parameter comprises:measuring a value for a torque applied to the propeller; andmeasuring a value for a velocity produced at least in part by the action of the propeller.23. A method according to any of claim 20 , wherein the function is a function for determining a rotational speed for the propeller.27. A ...

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Номер записи: 55
23-01-2014 дата публикации

FLIGHT CONTROL LAWS FOR CONSTANT VECTOR FLAT TURNS

Номер: US20140025237A1
Автор: Caudill Troy Sheldon, Christensen Kevin Thomas, Shue Shyhpyng Jack
Принадлежит: Bell Helicopter Textron Inc.

An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector heading across a ground surface. The aircraft includes a control system in data communication with a model, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The model decouples the directional movement of the aircraft into a lateral equation of motion and a longitudinal equation of motion. The lateral control architecture utilizes the lateral equation of motion to control the aircraft in the lateral direction, while the longitudinal control architecture utilizes the longitudinal equation of motion to control the aircraft in the longitudinal direction. The initialization command logic selectively activates the lateral control architecture and the longitudinal control architecture. 1. A control system for an aircraft , comprising:a lateral control architecture configured to control lateral motion of the aircraft; anda longitudinal control architecture configured to control longitudinal motion of the aircraft;wherein the control system utilizes the lateral control architecture and the longitudinal control architecture to control yaw movement of the aircraft while the aircraft maintains a constant vector heading across a ground surface; andwherein the aircraft continuously moves in a yaw direction while maintaining the constant vector heading.2. The control system of claim 1 , wherein the control system is operably associated with a directional controller manually manipulated by a pilot.3. The control system of claim 2 , further comprising: a directional heading control loop;', 'a directional turn coordination control loop; and', 'a directional yaw rate control loop., 'a directional control architecture, having4. The control system of claim 3 , further comprising:a directional control latch in data communication with the directional control architecture;wherein, as the directional controller is moved out of a ...

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Номер записи: 56
23-01-2014 дата публикации

System and Method for Multiple Aircraft Lifting a Common Payload

Номер: US20140025238A1
Автор: Eichel Justin, SO Wilfred, Szabo Peter, Vu Linda
Принадлежит:

A system and method are provided for controlling a plurality of aircraft to lift a common payload. The system comprises of multiple aircraft tethered to a common payload, where the group of aircraft form a swarm that is controlled by a pilot station. Each aircraft is autonomously stabilized and guided through a swarm avionics unit, which further includes sensor, communication, and processing hardware. At the pilot station, a pilot remotely enters payload destinations, which is processed and communicated to each aircraft. The method for controlling a multi-aircraft lifting system includes of inputting the desired location of the payload, and determining a series of intermediary payload waypoints. Next, these payload waypoints are used by the swarm waypoint controller to generate individual waypoints for each aircraft. A flight controller for each aircraft moves the aircraft to these individual waypoints. 1. A computing device configured for use in controlling a plurality of aircraft attached to a common payload , the computing device comprising:a processor configured to compute a path for said common payload towards a desired payload destination, configured to use said path and a current payload state to compute a desired payload state, and configured to use said current payload state and said desired payload state to compute a respective desired state for each one of said plurality of aircraft to transport said common payload along said path.2. The computing device of configured to transmit said respective desired state for each one of said plurality of aircraft to a respective flight controller of said each one of said plurality of aircraft.3. The computing device of configured to receive an aircraft state from a respective flight controller of each one of said plurality of aircraft.4. The computing device of configured to receive information used to compute the current payload state from a payload avionics unit.5. The computing device of wherein the information is ...

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Номер записи: 57
30-01-2014 дата публикации

HAND LAUNCHABLE UNMANNED AERIAL VEHICLE

Номер: US20140027579A1
Автор: Miller Gerald, Stewart James
Принадлежит:

An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder. 125.-. (canceled)26. An aerial vehicle system , the system comprising:an unmanned aerial vehicle and a portable launcher; a body defining a longitudinal axis,', 'a first wing extending laterally in a first direction from the body,', 'a second wing extending laterally in a second direction from the body, the second direction being opposite the first direction,', 'a first flight control surface supported by the body and configured to control pitch of the vehicle,', 'a second flight control surface supported by the body and configured to control yaw of the vehicle,', 'a controller including a flight control system operably coupled to the first flight control surface and the second flight control surface,', 'a propulsion device operably coupled to the body;', 'an acquisition sensor including an optical receiver for detecting a target, the optical receiver including a video processor and a lens to direct light to the video processor, wherein the video processor including a focal plane array having a collector grid to receive the light from the lens;', 'a navigation system including an inertial measurement system for detecting pitch, roll, and yaw of the aerial vehicle, and an inertial navigational system to determine position, orientation, and velocity of the aerial vehicle;', 'a trigger sensor configured to generate a signal in response to a predefined stimulus; and', 'a responder in electrical communication with the controller ...

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Номер записи: 58
30-01-2014 дата публикации

SYSTEM AND METHOD FOR CONTROLLING AN UNMANNED AIR VEHICLE

Номер: US20140032021A1
Автор: Metzler Bernhard, Siercks Knut
Принадлежит: HEXAGON TECHNOLOGY CENTER GMBH

A geodetic measuring system having a geodetic measuring unit having a beam source for emitting a substantially collimated optical beam. The measuring system also has an automotive, unmanned, controllable air vehicle having an optical module. An evaluation unit is also provided, wherein the evaluation unit is configured in such a manner that an actual state of the air vehicle, as determined by a position, an orientation and/or a change in position, can be determined in a coordinate system from interaction between the optical beam and the optical module. The measuring system has a control unit for controlling the air vehicle, wherein the control unit is configured in such a manner that control data can be produced using an algorithm on the basis of the actual state, which can be continuously determined in particular, and a defined desired state, and the air vehicle can be automatically changed to the desired state. 115-. (canceled)16. A geodetic measuring system comprising: a beam source for emitting a substantially collimated optical beam;', 'a base;', 'a sighting unit which can be pivoted by motor about two axes relative to the base for aligning an emission direction of the optical beam; and', 'angle measurement sensors for determining the alignment of the sighting unit;, 'a geodetic measuring unit comprisinga self-propelled, unmanned, controllable aerial vehicle with an optical module, wherein the aerial vehicle is designed in such a way that the aerial vehicle can be moved in a controlled fashion and/or positioned at a substantially fixed position; andan evaluation unit, wherein the evaluation unit is configured in such a way that it is possible to determine an actual state of the aerial vehicle in a coordinate system, determined by a position, an alignment and/or a change in position, from an interaction of the optical beam with the optical module; andwherein the measuring system comprises a control unit for controlling the aerial vehicle, wherein the control ...

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Номер записи: 59
06-02-2014 дата публикации

METHOD AND DEVICE FOR AIDING THE MANAGEMENT OF THE FLIGHT OF AN AIRCRAFT

Номер: US20140039731A1
Автор: Boada-Bauxell Josep, Constans Florian, Leberquer Charles Renault, Louise Pascale
Принадлежит: AIRBUS OPERATIONS (S.A.S.)

The device comprises servocontrol means which automatically control, in a combined manner, an automatic thrust system of the aircraft and airbrakes of the aircraft, as a supplement to usual means for steering the vertical trajectory, so that the aircraft attains a speed setpoint and/or altitude setpoint, at the location defined by a geographical constraint. 1. A method for aiding the management of the flight of an aircraft , according to which method there is envisaged an interface unit allowing a pilot to enter at least one of the following setpoints: a speed setpoint and an altitude setpoint , as well as means of automatic piloting which apply , in an automatic manner to said aircraft , setpoints thus entered , wherein:a) interface means are envisaged, moreover, allowing a pilot to generate a geographical constraint represented by a distance ahead of the aircraft, defining a position at which he wishes that a setpoint entered be attained; andb) an automatic thrust system of the aircraft and airbrakes of the aircraft are automatically servocontrolled, in a combined manner, so that the aircraft attains said setpoint entered, at the position defined by said geographical constraint.2. The method as claimed in claim 1 , wherein claim 1 , in an automatic manner claim 1 , in a step c) claim 1 , the trajectory flown by the aircraft is determined according to the setpoints of the active guidance mode and according to the thrust and airbrakes profile controlled so as to attain said setpoint at said geographical constraint claim 1 , and at least one part of said trajectory is presented on a viewing screen claim 1 , together with the locations at which the speed and altitude setpoints are attained.3. The method as claimed in claim 2 , wherein there is envisaged on said viewing screen at least one graphical object which is effected in the form of an interaction means which represents:on the one hand, a restitution element which indicates the location of attainment of said ...

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Номер записи: 60
06-03-2014 дата публикации

REMOTE DETECTION, CONFIRMATION AND DETONATION OF BURIED IMPROVISED EXPLOSIVE DEVICES

Номер: US20140062754A1
Автор: Mohamadi Farrokh
Принадлежит:

A small unmanned aerial system (sUAS) is used for remotely detecting concealed explosive devices—such as buried or otherwise hidden improvised explosive devices (IED)—and exploding or disarming the device while an operator of the sUAS, or other personnel, remain at a safe distance. The sUAS system can be operated at an extended, e.g., greater than 100 meters, standoff from the detection apparatus, explosive, and potential harm and may be operated by a single member of an explosive ordnance disposal (EOD) team. The sUAS may be implemented as an easy-to-operate, small vertical take-off and landing (VTOL) aircraft with a set of optical, thermal, and chemical detection modules for detecting an IED by aerial surveillance, confirming the existence of explosives, and providing options for detonating the IED electrically or by delivery of a payload (e.g., object or device) to neutralize the IED while maintaining the sUAS itself safe from harm. 1. A system comprising:an aircraft having a plurality of wing unit propellers for vertical takeoff and landing;a control system included in the aircraft for controlling flight of the aircraft both autonomously and from a remote location;an ultra-wideband (UWB) radar imaging system for detecting the presence of buried objects, wherein the UWB radar imaging system is carried by the aircraft; and 'the system is configured to perform an autonomous scan of a suspect area by autonomously flying the aircraft in a search pattern over the suspect area and interrogating the suspect area with the UWB radar imaging system.', 'a telemetry system carried by the aircraft for providing information from the UWB radar imaging system to the remote location, wherein'}2. The system of claim 1 , further comprising:a global positioning system (GPS) unit carried by the aircraft; and whereinthe system determines a start point for autonomously flying the search pattern from a global positioning system (GPS) waypoint.3. The system of claim 1 , further ...

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Номер записи: 61
06-03-2014 дата публикации

METHOD AND DEVICE FOR CONTROLLING AND MONITORING THE SURROUNDING AREAS OF AN UNMANNED AERIAL VEHICLE (UAV)

Номер: US20140067162A1
Автор: Muren Petter, Paulsen Dag Henning
Принадлежит: PROX DYNAMICS AS

The embodiments herein disclose a method and a remote control for controlling and monitoring surrounding areas of an Unmanned Aerial Vehicle (UAV) by an operator with a remote control comprising a flight display. The embodiments disclose a surprising advantageously effect for the purposes of controlling and monitoring the surroundings of a UAV by combining the image captured by a UAV camera with a transparently overlaid positional and navigation map providing a perception enabling the operator to have a complete overall view of the situation, utilizing a common screen section of a flight display and thereby not having to shift eye view. Viewing images and positional and navigation information in the way described has shown not to interfere with each other, rather on the contrary. 1. A method for controlling , and monitoring surrounding areas of , an Unmanned Aerial Vehicle (UAV) by an Operator with a remote control , comprising:providing a flight display, and a UAV equipped with a camera and a positioning device providing an image of surrounding areas and positioning data of an operating field of the UAV, wirelessly transmitted to a remote control;displaying the image captured by the camera on the flight display;providing a transparent layer upon the image comprising a cardinal-oriented map of a range of the operating field including at least a cardinal point, a UAV symbol oriented on the flight display relative to the cardinal point corresponding to a real compass direction of the UAV provided by the positioning device; anda waypoint symbol positioned relative to the UAV symbol corresponding in distance and direction to a real geographical relation between the UAV and the waypoint.2. The method according to claim 1 , wherein the cardinal-oriented map further comprises an Operator position symbol positioned relative to the UAV symbol and the waypoint symbol corresponding in distance and direction to a real geographical relation between the Operator and the UAV and ...

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Номер записи: 62
27-03-2014 дата публикации

METHOD OF CONTROLLING THE WING FLAPS AND HORIZONTAL STABILIZER OF A HYBRID HELICOPTER

Номер: US20140084105A1
Автор: Eglin Paul
Принадлежит: EUROCOPTER

A method of controlling a high speed rotary wing aircraft () comprising: a fuselage (); at least one main rotor (); at least one variable pitch propulsive propeller (); at least two half-wings (′) positioned on either side of said fuselage (); at least one horizontal stabilizer () provided with a movable surface (′); and at least one power plant driving said main rotor () and each propulsive propeller () in rotation. Said method serves to adjust the lift of said half-wings (′) and the lift of the horizontal stabilizer () so that the collective pitch of said blades () of said main rotor () is equal to a setpoint collective pitch, so that the longitudinal cyclic pitch of said blades () of said main rotor () is equal to a setpoint longitudinal cyclic pitch, and so that the lateral cyclic pitch of said blades () of said main rotor () is equal to a setpoint lateral cyclic pitch during a stabilized stage of flight. 1. A method of controlling a high speed rotary wing aircraft , the aircraft comprising:a fuselage;at least one main rotor having a plurality of blades;at least one variable pitch propulsive propeller;at least two half-wings positioned on either side of said fuselage;at least one horizontal stabilizer positioned at one end of said aircraft, said horizontal stabilizer having at least one movable surface; andat least one power plant driving said main rotor and each propulsive propeller in rotation;the method comprising the following steps:determining a setpoint collective pitch and a setpoint longitudinal cyclic pitch for causing said aircraft to converge on an optimized operating point for said main rotor during a stabilized stage of flight, while conserving a constant vertical behavior target such as a constant vertical speed or a constant angle of incidence, and a constant longitudinal attitude target corresponding to said stabilized stage of flight; andadjusting the lift of said half-wings by acting on aerodynamic control means of said aircraft so that the ...

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Номер записи: 63
27-03-2014 дата публикации

Method of controlling the wing flaps and horizontal stabilizer of a hybrid helicopter

Номер: US20140084106A1
Автор: Paul Eglin
Принадлежит: Eurocopter SA

A method of controlling a high-speed rotary wing aircraft ( 1 ) comprising a fuselage ( 2 ), at least one main rotor ( 3 ), at least one variable-pitch propulsive propeller ( 4 ), at least two half-wings ( 11, 11 ′) positioned on either side of said fuselage ( 2 ), at least one horizontal stabilizer ( 20 ) provided with a movable surface ( 21, 21 ′), and at least one power plant driving said main rotor ( 3 ) and said propulsive propeller ( 4 ) in rotation. Said method serves to adjust the lift of said half-wings ( 11, 11 ′) and the lift of the horizontal stabilizer ( 20 ) so that said lift of said half-wings ( 11, 11 ′) represents a predetermined percentage of the total lift of said aircraft ( 1 ) and so that the power consumed by said main rotor ( 3 ) is equal to a setpoint power during a stage of stabilized flight.

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Номер записи: 64
27-03-2014 дата публикации

FLIGHT CONTROL USING DISTRIBUTED MICRO-THRUSTERS

Номер: US20140084115A1
Автор: Garbuz Piotr A., Sanchez Jason D., Zonenberg Andrew D.
Принадлежит: GAME CHANGERS, LLC

A method and apparatus to control movement of a vehicle using a plurality of thrust-producing devices formed in at least one control surface is disclosed. A supply of power to the plurality of thrust-producing devices that are configured to propel gas through the control surface to produce thrust is controlled such that a physical displacement of the control surface is generated. The physical displacement is in accordance with the supply of power to the plurality of thrust-producing devices and controls the movement of the vehicle. 1. A method of controlling movement of a vehicle using a plurality of thrust-producing devices , comprising:controlling a supply of power to the plurality of thrust-producing devices formed in at least one control surface that are configured to propel gas through the control surface to produce thrust; andgenerating a physical displacement of the at least one control surface in accordance with the supply of power to the plurality of thrust-producing devices to control movement of the vehicle.2. The method of claim 1 , wherein:the at least one control surface includes a plurality of control surfaces, andthe controlling of the supply of power to the plurality of thrust-producing devices includes controlling the supply of power to first thrust-producing devices formed on a first control surface and second thrust-producing devices formed on a second control surface such that the vehicle moves in a desired path.3. The method of claim 1 , further comprising forming the at least one control surface using NMSET elements as the plurality of thrust-producing devices.4. The method of claim 3 , wherein the forming of the at least one control surface includes integrally forming said control surface into said vehicle.5. The method of claim 3 , wherein the forming of the at least one control surface includes integrating the NMSET elements into the at least one control surface.6. The method of claim 1 , wherein the generation of the physical displacement ...

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Номер записи: 65
27-03-2014 дата публикации

Systems and methods providing a fuel-efficient rta implementation with uncertain winds

Номер: US20140088799A1
Автор: Clayton Patrick Tino, John-Paul Barrington Clarke
Принадлежит: Georgia Tech Research Corp

Flight management systems and control methods for meeting a required time of arrival (RTA) with reduced fuel burn. The method can account for probabilistic wind forecast uncertainty in RTA calculations by reformulating the speed and thrust profile problem as a multi-stage stochastic program, using a wind forecast uncertainty model to generate scenario sets for the fuel optimization problem. The method can iteratively calculate a fuel-efficient advised air speed for achieving an RTA over a flight path with an arbitrary number of recourse points. Methods for creating wind forecast uncertainty models applicable to a variety of routes through a given airspace, and for use with the flight management systems and control methods. An example wind forecast uncertainty model can be position-specific, data-driven and based on a Markov chain representing error values between historical wind speed data and forecasted wind speed data long a planned flight route or between an origin-destination pair.

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Номер записи: 66
03-04-2014 дата публикации

ALTITUDE AND ACCELERATION COMMAND ALTITUDE HOLD ALGORITHM FOR ROTORCRAFT WITH LARGE CENTER OF GRAVITY RANGE

Номер: US20140095001A1
Автор: Cherepinsky Igor
Принадлежит: SIKORSKY AIRCRAFT CORPORATION

A flight control system includes an Acceleration and Attitude Command/Velocity Hold mode (AACVH) algorithm which blends attitude commands with acceleration commands This blending determines a trim attitude for a given rotorcraft flight condition. 1. An Attitude and Acceleration Command/Velocity Hold algorithm for a rotary wing rotorcraft flight control system comprising:an attitude command model logic which generates an attitude command model logic output;an attitude model logic in communication with said attitude command model logic output, said attitude model logic generates an attitude model logic output;an acceleration model logic in communication with said attitude command model logic output, said acceleration model logic generates an acceleration model logic output; anda model following controller in communication with said attitude model logic output and said acceleration model logic output, said model following controller generates an rotorcraft command to determine a trim attitude for a given rotorcraft flight condition.2. The algorithm as recited in claim 1 , further comprising a velocity model logic in communication with said acceleration model logic output claim 1 , said velocity model logic generates a velocity model logic output in communication with said model following controller.3. The algorithm as recited in claim 2 , further comprising a measured rotorcraft velocity and acceleration in communication with said velocity model logic output and said acceleration model logic output at junction to provide a summed result as a velocity and acceleration error signal output in communication with said model following controller.4. The algorithm as recited in claim 3 , further comprising a measured rotorcraft attitude in communication with said attitude model logic output at junction to provide a summed result as an attitude error signal output in communication with said model following controller.5. The algorithm as recited in claim 1 , further comprising a ...

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Номер записи: 67
10-04-2014 дата публикации

HOVER HOLD AID SYSTEM FOR A HELICOPTER

Номер: US20140097291A1
Автор: Aymeric Bruno, Hourlier Sylvain, LE ROUX Yannick
Принадлежит:

The general area of the invention is that of hover hold aid systems for helicopters. The system comprises navigation means; a helmet-mounted visualization system containing a helmet-mounted display incorporated in the pilot's helmet and means for generating symbols in said helmet-mounted display at fixed positions in relation to a terrestrial frame of reference, said symbols being displayed in the angular field of display of the helmet-mounted display. When the helicopter has to home or stay in the vicinity of a predetermined position, the symbol generation means calculate a first and a second representation containing a first target and a second target referenced in said terrestrial frame of reference, the first target located in the direction of the homing course to the predetermined position, the second target located in a direction perpendicular to this same course. 1. Hover hold aid system for a helicopter , said system comprising at least:navigation means enabling the determination of the current position of the helicopter in flight in relation to a terrestrial frame of reference;a helmet-mounted visualization system containing a helmet posture detection device, a helmet-mounted display incorporated in the helmet of the pilot of said helicopter and means for generating symbols in said helmet-mounted display at fixed virtual positions in relation to said terrestrial frame of reference, said symbols being displayed when the latter are situated in the angular field of display of the helmet-mounted display;wherein, when the helicopter has to home or be held in the vicinity of a predetermined position in said terrestrial frame of reference, the symbol generation means calculate a first representation containing a first target and a second representation containing a second target, said targets being referenced in said terrestrial frame of reference, the first target located in the direction of the homing course to the predetermined position, the second target ...

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Номер записи: 68
10-04-2014 дата публикации

FLIGHT CONTROL SYSTEM USING SIMPLEX COMPUTERS AND AIRCRAFT COMPRISING SAME

Номер: US20140100718A1
Автор: BROT Patrice, Devineau Sylvain
Принадлежит:

A system for computing flight commands, which comprises simplex computers coupled to form virtual command/monitor pairs. These virtual pairs send the commands computed to actuators whose controller implements an election of the pair whose command will be taken into account by the actuator. 1. A computer for computing flight commands within a flight control system , comprising:at least one item of software for computing flight commands according to at least one flight law on the basis of at least one command received from at least one piloting member;means of communication with at least two other associated computers of the same type;means for computing a first flight order, intended for a remote controller of an airfoil actuator, in command mode within a first virtual command/monitor pair comprising said computer and one of the two associated computers acting in monitor mode on behalf of said first virtual command/monitor pair;means for computing a second flight order, intended for a remote controller of an airfoil actuator, in monitor mode within a second virtual command/monitor pair comprising said computer and of the other associated computer acting in command mode on behalf of said second virtual command/monitor pair.2. The computer according to claim 1 , further comprising means for verifying the validity of the virtual command/monitor pairs according to the following criteria:the commands computed by the two computers of the pair are available and computed according to the same flight law; andthe difference in absolute value between the two commands computed is less than a given tolerance threshold.3. The computer according to claim 2 , wherein the means for verifying the validity of the virtual command/monitor pairs furthermore:that the two computers implement a different item of software for the computation of the commands.4. The computer according to claim 1 , characterized in that it furthermore comprising means for transmitting to all the other computers ...

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Номер записи: 69
02-01-2020 дата публикации

METHOD AND APPARATUS FOR PROXIMITY CONTROL BETWEEN ROTATING AND NON-ROTATING AIRCRAFT COMPONENTS

Номер: US20200001979A1
Автор: ATKINS Brady Garrett, BAILEY Karl, COOK Stuart Benjamin, Cravener Kyle Thomas, JAGNEAUX Corrine, MAUGA Maika Lopati, VARGAS CALVET Joaquin, WHITE Andrew Michael
Принадлежит: Bell Helicopter Textron Inc.

The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor. 1. An aircraft rotor-proximity detection system comprising:a rotor having a plurality of rotor blades;a first proximity sensor disposed in a non-rotating aircraft component and configured to detect a proximity of a rotor blade of the plurality of rotor blades to the non-rotating component; anda flight control computer in communication with the first proximity sensor.2. The aircraft rotor-proximity detection system of claim 1 , wherein the first proximity sensor is configured to emit ultrasonic sound waves toward the plurality of rotor blades.3. The aircraft rotor-proximity detection system of claim 1 , wherein the first proximity sensor is configured to measure air pressure.4. The aircraft rotor-proximity detection system of claim 1 , wherein the first proximity sensor is configured to emit light waves toward the plurality of rotor blades.5. The aircraft rotor-proximity detection system of claim 4 , wherein the first proximity sensor is oriented at an acute angle relative to an axis parallel to a mast of the rotor.6. The aircraft rotor-proximity detection system of claim 1 , wherein the first proximity sensor comprises a light source and a receiver that form a first tripwire therebetween.7. The aircraft rotor-proximity detection system of claim 6 , wherein the flight control computer is configured to issue a warning responsive to the first tripwire being tripped by the plurality of rotor blades.8. The aircraft rotor-proximity detection system of claim 6 , comprising:a second proximity sensor disposed in the non-rotating aircraft component;wherein the second proximity sensor comprises a light source and a receiver that form a second tripwire ...

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Номер записи: 70
04-01-2018 дата публикации

SYSTEM, A METHOD AND A COMPUTER PROGRAM PRODUCT FOR MANEUVERING OF AN AIR VEHICLE WITH TILTABLE PROPULSION UNIT

Номер: US20180002004A1
Автор: Dekel Guy, Efraty Yoav, VOLOVICK Avner, Wolff Amit, Zivan Lior
Принадлежит:

A control system configured to control a deceleration process of an air vehicle which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle. 138-. (canceled)39. A system comprising:a control system configured to control a deceleration process of an air vehicle, which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle; the air vehicle further comprises a wing configured to provide lift to the air vehicle; the wing being in a fixed position during flight of the air vehicle, the control system comprising:at least one input for receiving information indicative of monitored airspeed of the air vehicle and of monitored altitude of the air vehicle; anda control unit, configured to issue controlling commands to controllers of aerodynamic systems of the air vehicle, the aerodynamic systems comprising the at least one tiltable propulsion unit; wherein the control unit is configured issue the controlling commands for:controlling, during a descent of the air vehicle, a descending course of the air vehicle based on at least monitored airspeed and monitored altitude of the air vehicle, at least by controlling in a first part of the descent, an operation of the at least one tiltable propulsion unit to provide thrust in the general longitudinal thrust vector direction for propelling the air vehicle; and following a tilting of the at least one tiltable propulsion unit, controlling in a second part of the descent an operation of the at least one tiltable propulsion unit to provide thrust in ...

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Номер записи: 71
04-01-2018 дата публикации

Aircraft lighting system

Номер: US20180002034A1
Автор: Khawam Maurice A.
Принадлежит:

The present invention is an aircraft lighting system. In particular, the present invention is directed to an aircraft lighting system with light that is directed toward an aircraft's engines to deter bird strikes. The lighting system for a jet-powered aircraft has at least one light mounted on an aircraft fuselage aimed at an engine inlet of an engine nacelle of the aircraft. The illumination from the light comprises ultraviolet light between 300 and 400 nm in wavelength and the light flashes at a pre-determined frequency preferably between 1 and 3 Hz. Additional lights can be mounted on the engine nacelles to illuminate outer engine nacelles. Preferably, the engine of the aircraft also has blades coated in fluorescent or iridescent paint to increase the reflectivity of the blades to further illuminate the blades of the engine. The lighting system preferably automatically illuminates the engine inlets during take-off and descent. 1. An aircraft lighting system for a jet powered aircraft where the aircraft has a fuselage and an engine nacelle with an engine inlet , the lighting system comprising:at least one light mounted on the fuselage aimed at the engine inlet of the engine nacelle, where illumination from the light comprises ultraviolet light and the at least one light flashes at a pre-determined frequency.2. The aircraft lighting system of where the ultraviolet light is between 300 and 400 nm in wavelength.3. The aircraft lighting system of where the pre-determined frequency is between 1 and 3 Hz.4. The aircraft lighting system of where the engine nacelle further comprises engine blades or cones or engine inlet inner surfaces coated in fluorescent or iridescent paint.5. The aircraft lighting system of where the aircraft further comprises an outer engine nacelle and where the lighting system further comprises at least one nacelle light mounted on the engine nacelle aimed at the outer engine nacelle.6. The aircraft lighting system of where the lighting system ...

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Номер записи: 72
01-01-2015 дата публикации

SECURE AIRCRAFT-BASED MOBILE DEVICE CONNECTIVITY SYSTEMS AND METHODS

Номер: US20150005989A1
Автор: Beltrand Francois
Принадлежит:

An aircraft-based mobile device connectivity system generally includes a housing, an avionic systems interface integrated into the housing, a wireless interface integrated into the housing, and a data security module. The avionic system interface is configured to be communicatively coupled to an avionics system external to the housing. The wireless interface is configured to provide wireless communication with one or more mobile devices. The data security module is configured to receive commands from the mobile devices, securely process the commands, receive avionics data from the avionics system via the avionic systems interface and the avionics module, and securely transmit the avionics data to the mobile devices. 1. An aircraft-based mobile device connectivity system comprising:a housing;an avionic systems interface integrated into the housing, the avionic system interface configured to be communicatively coupled to an avionics system external to the housing;a wireless interface integrated into the housing, the wireless interface configured to provide wireless communication with one or more mobile devices;at least one avionics module integrated into the housing; anda data security module located within the housing, the data security module configured to receive commands from the one or more mobile devices, securely process the commands, receive avionics data from the avionics system via the avionic systems interface and the at least one avionics module, and securely transmit the avionics data to the one or more mobile devices.2. The system of claim 1 , further including a wired interface integrated into the housing claim 1 , the wired interface configured to be communicatively coupled to at least one storage device external to the housing.3. The system of claim 1 , further including a WACS interface integrated into the housing claim 1 , the WACS interface configured to be communicatively coupled to a WACS communication module external to the housing.4. The system ...

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Номер записи: 73
01-01-2015 дата публикации

DETERMINISTIC ETHERNET FOR AN AEROSPACE DISTRIBUTED CONTROL SYSTEM

Номер: US20150005991A1
Автор: Willoughby Adrian C., Zeller Robert J.
Принадлежит: Rolls-Royce Corporation

A control system for an aircraft may include a master node and a plurality of slave nodes in communication with each other. The master node and the plurality of slave nodes may each have a processor. The control system may also include at least one data bus connection that enables the communication between the master node and the plurality of slave nodes. The data bus may be governed by any data bus protocol, including, but not limited to, Ethernet. The control system generally may be deterministic in operation. 1. A control system for an aircraft comprising:a master node and a plurality of slave nodes in communication with each other, the master node and the plurality of slave nodes each having a processor; andat least one data bus connection that enables the communication between the master node and the plurality of slave nodes;wherein the control system is deterministic.2. The control system of wherein the data bus is governed by an Ethernet data bus protocol.3. The control system of further comprising a graphic user interface (GUI) in communication with the master node.4. The control system of wherein the master processor and the at least one control processor are in direct5. The control system of wherein the master processor node is mounted on the aircraft.6. The control system of wherein the master node and the plurality of slave nodes each further comprises a clock and a software scheduler claim 1 , the clocks being synchronized and the software schedulers being configured to enable signals to be transmitted and received within a predetermined time frame.7. The control system of wherein the master node and the plurality of slave nodes each further comprise a clock synchronization and software scheduling modules configured to enable the clock synchronization and the software scheduling.8. The control system of wherein the master node and the plurality of slave nodes are connected by the at least one data bus in a ring configuration.9. An aircraft comprising:an ...

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Номер записи: 74
03-01-2019 дата публикации

FLIGHT MODES AND PROTECTION ENVELOPES BASED ON INERTIAL ATTITUDE ESTIMATES FOR RADIO-CONTROLLED AIRPLANES

Номер: US20190004511A1
Автор: Burch Joseph, Ribbe David
Принадлежит:

The present disclosure describes flight training systems and methods for radio-controlled (RC) airplanes that rely on inertial attitude estimates. Preferred embodiments include an RC airplane with one or more control processors configured to (i) estimate an inertial attitude of the RC airplane based on one or more measurements from an attitude sensor array and (ii) control the inertial attitude of the RC airplane based the inertial attitude estimate. In operation, controlling the attitude of the RC airplane may include both controlling the RC airplane to a specific inertial attitude and/or keeping the inertial attitude of the RC airplane within a predefined flight envelope. 1. A radio-controlled (RC) airplane comprising:a receiver configured to receive command data corresponding to one or more flight control commands from an RC controller associated with the RC airplane;an attitude sensor array comprising one or more accelerometers and one more gyroscopes;a plurality of servomotors configured to adjust one or more control surfaces of the RC airplane; andone or more processors configured to (i) estimate an inertial attitude of the RC airplane based on data received from the attitude sensor array, (ii) determine whether the estimated inertial attitude exceeds at least one of a first inertial pitch range or a first inertial roll range corresponding to a first flight envelope of a first flight mode, (iii) in response to determining that the estimated inertial attitude exceeds at least one of the first inertial pitch range or the first inertial roll range, generate at least one control signal for application to at least one of the plurality of servomotors to adjust one or more of the control surfaces; and (iv) in response to receiving command data comprising at least one control stick input, adjusting at least one of a throttle and/or one or more control surfaces of the RC airplane based on an inertial attitude corresponding to the at least one control stick input, ...

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Номер записи: 75
08-01-2015 дата публикации

Air Vehicle Flight Mechanism and Control Method

Номер: US20150008279A1
Автор: Andryukov Alexander, Hibbs Bart Dean, Keennon Matthew Todd, Klingebiel Karl Robert, Zwaan John Peter
Принадлежит: AeroVironment, Inc.

Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension. 1. A method of air vehicle control , comprising:flapping first and second control surfaces; andhovering the first and second control surfaces in response to the flapping without the benefit of an additional control surface.2. An air vehicle apparatus , comprising:first and second flapping control surfaces;wherein the first and second flapping control surfaces are capable of providing hovering and control moments without the benefit of additional control surfaces.3. A method of air vehicle control , comprising:flapping first and second wings horizontally about a fuselage, the first and second wings having a first and second variable differential sweep angles of deflection, respectively; andproviding vertical and horizontal vehicle orientation control in response to the horizontal flapping.4. The method of claim 3 , further comprising:generating a roll moment in response to the first sweep angle being larger than the second sweep angle.5. The method of claim 3 , further comprising: deflecting the first wing less than deflection of the second wing during a majority of a back stroke of the flapping; and', 'deflecting the second wing less than deflection of the first wing during a majority of the forward stroke of the flapping., 'inducing a left yaw moment in the air vehicle in response to6. The method of claim 3 , further comprising: deflecting the first wing more than deflection of the second wing during a majority of a back stroke of the flapping; and', 'deflecting the second wing more than deflection of the first wing during a majority of the forward stroke of the flapping., 'inducing a right yaw moment in the air vehicle in response to7. The method of claim 3 , further comprising: ' ...

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Номер записи: 76
14-01-2021 дата публикации

HIGH LIFT SYSTEMS FOR AIRCRAFT AND RELATED METHODS

Номер: US20210009257A1
Автор: Dickey Eric David, Shmilovich Arvin
Принадлежит:

High-lift systems and related methods are described. An example apparatus includes a fixed wing and a Krueger flap movably coupled to the fixed wing between a stowed position and a deployed position. The Krueger flap includes a first flap portion movably coupled to the fixed wing and a second flap portion movable coupled to the first flap portion. The first flap portion moves relative to the second flap portion between a retracted position and an extended position. The first flap is to move to the retracted position in response to the Krueger flap moving to the stowed position. The first flap is to move to the extended position to define an aerodynamic surface in response to the Krueger flap moving to the deployed position. 1. An apparatus , comprising:a fixed wing; and a first flap portion movably coupled to the fixed wing; and', 'a second flap portion movable coupled to the first flap portion, the first flap portion moves relative to the second flap portion between a retracted position and an extended position, the first flap to move to the retracted position in response to the Krueger flap moving to the stowed position, and the first flap to move to the extended position to define an aerodynamic surface in response to the Krueger flap moving to the deployed position., 'a Krueger flap movably coupled to the fixed wing between a stowed position and a deployed position, the Krueger flap including2. The apparatus of claim 1 , wherein an end of the second flap portion overlaps ends of the first flap portion when the second flap portion is in the retracted position.3. The apparatus of claim 2 , wherein the end of the second flap portion matably engages the ends of the first flap portion when the second flap portion is in the extended position.4. The apparatus of claim 2 , wherein the end of the second flap portion does not overlap the ends of the first flap portion when the second flap portion is in the extended position.5. The apparatus of claim 1 , wherein the second ...

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Номер записи: 77
09-01-2020 дата публикации

CONTEXT-BASED FLIGHT MODE SELECTION

Номер: US20200010194A1
Автор: HU XIAO, Liu Ang, Pan Xuyang, ZHOU Guyue
Принадлежит:

A system for controlling an unmanned aerial vehicle (UAV) to switch between different flight modes during operation. The system includes one or more processors configured to determine, based on sensor data received from one or more sensors carried by the UAV, a change in environment of the UAV from a first environment type to a second environment type. In response to determining the change in environment, the one or more processors configured to switch a flight mode of the UAV from a first flight mode to a second flight mode, and effect operation of the UAV in accordance with a second set of operating rules for operating in the second environment type. 1. A system for controlling an unmanned aerial vehicle (UAV) to switch between different flight modes during operation , the system comprising: determine, based on sensor data received from one or more sensors carried by the UAV, a change in environment of the UAV from a first environment type to a second environment type, the first environment type and the second environment type being selected from a plurality of different environment types;', 'in response to determining the change in environment, switch a flight mode of the UAV from a first flight mode to a second flight mode, the first flight mode and the second flight mode being selected from a plurality of different flight modes, the first flight mode being associated with a first set of operating rules for the UAV to operate in the first environment type, and the second flight mode being associated with a second set of operating rules for the UAV to operate in the second environment type; and', 'effect operation of the UAV in the second environment type in accordance with the second set of operating rules associated with the second flight mode., 'one or more processors configured to2. The system of claim 1 , wherein the one or more sensors comprise a GPS sensor claim 1 , an inertial sensor claim 1 , a vision sensor claim 1 , a lidar sensor claim 1 , an ...

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Номер записи: 78
11-01-2018 дата публикации

NAVIGATION AIDS FOR UNMANNED AERIAL SYSTEMS IN A GPS-DENIED ENVIRONMENT

Номер: US20180010914A1
Автор: Bushnell Glenn Scott, Gallo Eduardo, Hardt Michael W., Navarro Francisco A.
Принадлежит:

Example navigation aids for increasing the accuracy of a navigation system are disclosed herein. An example method disclosed herein identifying, with an aircraft intent description language (AIDL) aid, an AIDL instruction as associated with a first dynamic activity level of a plurality of dynamic activity levels and determining, with the AIDL aid, an aircraft state to be affected by the AIDL instruction. The example method also includes changing, with a navigation filter, a weighting scheme for a measurement of the aircraft state obtained by an inertial navigation system (INS) of the aircraft and estimating, with the navigation filter, a trajectory of the aircraft based on the weighting scheme and the measurement. 1. A method comprising:identifying, with an aircraft intent description language (AIDL) aid, an AIDL instruction as associated with a first dynamic activity level of a plurality of dynamic activity levels;determining, with the AIDL aid, an aircraft state to be affected by the AIDL instruction;changing, with a navigation filter, a weighting scheme for a measurement of the aircraft state obtained by an inertial navigation system (INS) of the aircraft; andestimating, with the navigation filter, a trajectory of the aircraft based on the weighting scheme and the measurement.2. The method of claim 1 , wherein the plurality of dynamic activity levels include the first dynamic activity level and a second dynamic activity level claim 1 , the first dynamic activity level associated with a high dynamic activity and the second dynamic activity level associated with a low dynamic activity.3. The method of claim 2 , wherein changing the weighting scheme for the measurement includes assigning a lower weight to the measurement.4. The method of claim 1 , wherein the navigation filter includes an Extended Kalman Filter (EKF) claim 1 , and wherein changing the weighting scheme for the measurement includes increasing or decreasing a covariance factor of the measurement in at ...

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Номер записи: 79
11-01-2018 дата публикации

PASSIVE OPTICAL DETECTION METHOD AND SYSTEM FOR VEHICLES

Номер: US20180012461A1
Автор: Brown Robert A., Flom Zachary, Hill Richard Andrew, Matlin Erik Frank, Nashold Karen Marie
Принадлежит:

A system, method, and apparatus are discussed for a passive optical camera-based system to detect a presence of one or more vehicles with one or more cameras. A detection algorithm is applied to recognize of the presence of the one or more vehicles using one or more imaging processors and the one or more cameras to detect fluctuations in light intensity from scattered light and/or reflections off of that vehicle. Those scattered light and/or reflections are captured in images contained in a set of frames from the one or more cameras. 1. A system , comprising:a passive optical camera-based system configured to detect a presence of one or more vehicles with one or more cameras, where the passive optical camera-based system is configured to apply a detection algorithm to recognize the presence of the one or more vehicles using one or more imaging processors and the one or more cameras to detect fluctuations in light intensity from scattered light and/or reflections off of that vehicle, where those scattered light and/or reflections are captured in images contained in a set of frames from the one or more cameras, which are processed by the detection algorithm and imaging processors, where any portions of the detection algorithm implemented in software is stored in an executable format in a memory and is executed by one or more processors.2. The system of claim 1 , where the detection algorithm is configured to identify and characterize the presence of the vehicles by directly measuring fluctuations in light intensity from the i) reflections off of; ii) emissions from claim 1 , iii) blocking of background light by and/or iv) scattering of light from claim 1 , a) the vehicle's rotor or b) other moving or vibrating parts of the vehicle; and thus claim 1 , the detection algorithm is configured to find pixels in each frame 1) with the fluctuations in light intensity greater than a noise band as well as 2) these pixels are part of group of connected two or more pixels with ...

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Номер записи: 80
15-01-2015 дата публикации

WING FOLD CONTROLLER

Номер: US20150014478A1
Автор: Good Mark Steven, Lassen Matthew August
Принадлежит:

Illustrative embodiments may provide for an apparatus and method of controlling the folding of a wing. The apparatus may include a sensor, an actuator, and a wing fold controller. The method may include receiving a status of at least one of an aircraft and a wing fold system of the aircraft by the wing fold controller of the wing fold system. The method may also include receiving an automated command by the wing fold controller in response to receiving the status. The method may also include operating the wing fold system by the wing fold controller based on the automated command and the status. The method may also include transitioning a wingtip of a wing of the aircraft to one of a flight position and an on-ground position by an actuator of the wing fold system in response to commands from the wing fold controller. 1. A method of controlling an angular free play of an unfixed portion of a wing relative to a fixed portion of the wing while transitioning a lock in a latch , the method comprising:regulating a force on the unfixed portion and holding an unfixed lug against a stop device, the unfixed portion comprising the unfixed lug.2. The method of claim 1 , further comprising the latch comprising the unfixed lug.3. The method of claim 1 , further comprising holding the unfixed lug against the stop device via a control module regulating a power supply to a power drive unit connected to a wing fold actuator.4. The method of claim 3 , further comprising regulating the power supply to the power drive unit via a differential between a first power supplied to a first line and a second power supplied to a second line claim 3 , each line connecting the control module to the power drive unit.5. The method of claim 4 , further comprising the first power supplied to the first line moving the unfixed portion toward a flight position claim 4 , and the second power supplied to the second line moving the unfixed portion toward an on-ground position.6. The method of claim 1 , ...

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Номер записи: 81
03-02-2022 дата публикации

Gravity simulation system

Номер: US20220033102A1
Автор: Kipling Martin
Принадлежит: Individual

A gravity simulation system, including a computing system running a program thereon to receive input for a gravity environment and calculate the gravity environment based on a predetermined gravity algorithm, and a gravity simulation aircraft connected to the computing system to simulate the gravity environment received from the computing system based on at least one of a flight setting and a gravity setting.

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Номер записи: 82
19-01-2017 дата публикации

Aircraft with fire suppression control system

Номер: US20170014655A1
Автор: Josephine G. GATSONIDES, Paul A. Rennie, Stuart M. Smith
Принадлежит: Kidde Graviner Ltd

An aircraft has a fire suppression control system for a plurality of enclosures within the aircraft. The aircraft comprises a directional valve for each enclosure, sensors provided for each enclosure, for monitoring variables of the enclosure, one or more fire suppression agent bottles and a control unit for regulating the discharge of the fire suppression agent. The sensors are operatively linked by the control unit to a warning system in a cockpit of the aircraft.

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Номер записи: 83
19-01-2017 дата публикации

FIRE SUPPRESSION CONTROL SYSTEM FOR AN AIRCRAFT

Номер: US20170014656A1
Автор: Gatsonides Josephine G., Rennie Paul A., Smith Stuart M.
Принадлежит:

A directional valve for a fire suppression system comprises a valve member for controlling the discharge of fire suppression agent. The valve member comprises: a blocking portion to provide a closed setting for the fire suppression agent; a first orifice to provide a fully open setting for the fire suppression agent; and a second orifice to provide a restricted opening setting in which discharge of fire suppression agent is restricted. The valve member is configured so that during activation of the directional valve from a closed setting, the first orifice follows the blocking portion and precedes the second orifice in order to provide a fully open setting followed by a restricted opening setting. 1. A directional valve for a fire suppression system , comprising a valve member for controlling the discharge of fire suppression agent , wherein the valve member comprises:a blocking portion to provide a closed setting for the fire suppression agent;a first orifice to provide a fully open setting for the fire suppression agent; anda second orifice to provide a restricted opening setting in which flow of fire suppression agent is restricted,wherein the valve member is configured so that during opening of the directional valve from a closed setting, the first orifice follows the blocking portion and precedes the second orifice in order to provide a fully open setting followed by a restricted opening setting.2. A directional valve as claimed in claim 1 , wherein the valve member comprises a plate or a rotational element claim 1 , which has the blocking portion claim 1 , the first orifice and the second orifice in a sequence corresponding to the different settings.3. A fire suppression system for an aircraft having a plurality of enclosures claim 1 , the fire suppression system comprising a plurality of directional valves as described in claim 1 , each provided in an agent discharge line to an enclosure for controlling the discharge of fire suppression agent to the enclosure ...

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Номер записи: 84
19-01-2017 дата публикации

METHODS AND CONTROL SYSTEMS FOR CONTROLLING A DRIVE SYSTEM OF AN AIRCRAFT

Номер: US20170015410A1
Автор: COLOSIMO Antonio, Guery Xavier, SZNAJDER Lukasz
Принадлежит:

A method of controlling a drive system of an aircraft. The drive system comprised a drive motor arranged to drive at least one wheel of an aircraft landing gear. A power signal indicative of a power level for the drive motor and a speed signal indicative of a rotation speed of the drive motor are received. A torque level for the drive motor is determined using the power signal and the speed signal. The drive motor is then driven such that the torque generated by the drive motor is at the determined torque level. 1. A method of controlling a drive system of an aircraft , wherein the drive system comprises a drive motor arranged to drive at least one wheel of the aircraft landing gear , the method comprising the steps of:receiving a power signal indicative of a power level for the drive motor;receiving a speed signal indicative of a rotation speed of the drive motor;determining a torque level for the drive motor using the power signal and the speed signal;driving the drive motor such that the torque generated by the drive motor is at the determined torque level.2. A method as claimed in claim 1 , wherein the torque level is determined by dividing the power level indicated by the power signal by the rotation speed indicated by the speed signal.3. A method as claimed in claim 1 , wherein the torque level is at most a predefined maximum torque level.4. A method as claimed in claim 1 , wherein the torque level is claim 1 , if non-zero claim 1 , at least a predefined minimum torque level.5. A method as claimed in claim 1 , wherein the torque level is increased over time by at most a predefined maximum torque rate.6. A method as claimed in claim 1 , wherein if the rotation speed indicated by the speed signal is below a predefined minimum rotation speed claim 1 , the torque level is determined using the predefined minimum rotation speed.7. A method as claimed in claim 1 , wherein the power level indicated by the power signal is a percentage of a predefined maximum power ...

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Номер записи: 85
15-01-2015 дата публикации

DISPLAY SYSTEMS AND METHODS FOR PROVIDING DISPLAYS HAVING AN INTEGRATED AUTOPILOT FUNCTIONALITY

Номер: US20150019047A1
Автор: Chandrashekarappa Mohan Gowda, Shambulingappa Babitha Jajur
Принадлежит:

A method for providing a display to a flight crew of an aircraft includes providing a horizontal navigation display that includes data regarding the movement of the aircraft in a horizontal direction and an aircraft icon indicating a position of the aircraft in the horizontal direction. The method further includes providing a vertical navigation display that includes data regarding the movement of the aircraft in a vertical direction and an aircraft icon indicating a position of the aircraft in the vertical direction. The horizontal and vertical navigation displays are disposed adjacent to one another on a single display device. The method further includes receiving a first input to the display device indicating a selection of the horizontal navigation display aircraft icon, and, in response to the selection of the horizontal navigation display aircraft icon, engaging a horizontal navigation control feature of an autopilot system of the aircraft. 1. A method for providing a display to a flight crew of an aircraft comprising the steps of: data regarding the movement of the aircraft in a horizontal direction;', 'a virtual compass comprising an aircraft heading indicator indicating a current heading of the aircraft and an autopilot heading selector; and', 'an aircraft icon indicating a position of the aircraft in the horizontal direction;, 'providing a horizontal navigation display comprising data regarding the movement of the aircraft in a vertical direction;', 'an altitude target indicator line; and', 'an aircraft icon indicating a position of the aircraft in the vertical direction,', 'wherein the horizontal and vertical navigation displays are disposed adjacent to one another on a single display device;, 'providing a vertical navigation display comprisingreceiving a first input to the display device indicating a selection of the horizontal navigation display aircraft icon;in response to the selection of the horizontal navigation display aircraft icon, engaging a ...

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Номер записи: 86
22-01-2015 дата публикации

REDUNDANT CURRENT-SUM FEEDBACK ACTUATOR

Номер: US20150021441A1
Автор: Matsui Gen
Принадлежит:

A system and methods for redundant current-sum feedback control of an actuator system is presented. An actuator comprises actuation coils configured to actuate the actuator, and an actuation coil current sensor senses a measured total coil current comprising a sum of coil currents of each of the actuation coils. Actuator coil controllers control the actuation coils based on a commanded total coil current and the measured total coil current. 1. A redundant current-sum feedback actuator system comprising:an actuator comprising a plurality of actuation coils configured to actuate the actuator;an actuation coil current sensor configured to sense a measured total coil current comprising a sum of coil currents of each of the actuation coils; anda plurality of actuator coil controllers configured to control the actuation coils based on a current-sum difference between a commanded total coil current and the measured total coil current.2. The system of claim 1 , further comprising an actuation coil current sensor configured to sense the measured total coil current claim 1 , and comprising:a plurality of sensor coils configured to receive an actuator current that actuates one of the actuation coils respectively;a magnetic core configured to receive a magnetic flux from the sensor coils; andat least one sensor coupled to the magnetic core and configured to measure the measured total coil current.3. The system of claim 1 , further comprising an outer feedback control loop comprising a plurality of electrically independent outer control loops each configured to:receive a desired actuator position and a measured actuator position; andgenerate the commanded total coil current based on the desired actuator position and the measured actuator position.4. The system of claim 1 , wherein the actuation coils comprise a common actuation power.5. A method for suppressing non-optimality in an actuator control system claim 1 , the method comprising:sensing a measured total coil current ...

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Номер записи: 87
16-01-2020 дата публикации

METHOD OF MANAGING AN AUTOPILOT SYSTEM FITTED TO AN AIRCRAFT

Номер: US20200019188A1
Автор: ABDELLI Kamel
Принадлежит: AIRBUS HELICOPTERS

A management method for managing an autopilot system fitted to an aircraft, the management method being adapted to manage at least one error in at least one succession of steps serving to generate at least one autopilot setpoint for the aircraft, the autopilot system comprising at least one computer serving to implement a plurality of successions of steps generating different autopilot setpoints for the aircraft. Such a method comprises an identification step serving to identify the at least one error, a calculation step for determining a total number of occurrences of the at least one error, a stop step serving to stop the at least one succession of steps, a reinitialization step for reinitializing the at least one succession of steps, and a relaunch step for relaunching the at least one succession of steps. 1. A management method for managing an autopilot system fitted to an aircraft , the management method being adapted to manage at least one error in at least one succession of steps serving to generate at least one autopilot setpoint for the aircraft , the autopilot system comprising at least one computer serving to implement a plurality of successions of steps generating different autopilot setpoints for the aircraft ,wherein the method comprises at least:an identification step serving to identify the at least one error, the identification step serving to identify at least one occurrence of the at least one error over a predetermined period of use of the aircraft;a calculation step for determining a total number of occurrences of the at least one error over the predetermined period of use of the aircraft;a stop step serving to stop the at least one succession of steps over a first cycle of steps considered as being faulty when the total number of occurrences of the at least one error is greater than or equal to a predetermined threshold value;a reinitialization step for reinitializing the at least one succession of steps; anda relaunch step for relaunching the ...

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Номер записи: 88
28-01-2016 дата публикации

WATER VEHICLES

Номер: US20160023725A1
Автор: Hine Derek L., Hine Roger G.
Принадлежит: Liquid Robotics, Inc.

Equipment and methods that combine the use of wave powered vehicles and unmanned aerial vehicles (UAVs or drones). A UAV can be launched from a wave-powered vehicle, observe another vessel, and report the results of its observation to the wave-powered vehicle, and the wave-powered vehicle can report the results of the observation to a remote location. The UAV can land on water and can then be recovered by the wave-powered vehicle. 1. A float which comprises means for launching an unmanned aerial vehicle (UAV).2. A wave-powered vehicle (WPV) as hereinbefore defined which comprises a float according to .3. A wave-powered vehicle (WPV) which comprises means for recovering an unmanned aerial vehicle (UAV) which is floating in the water.4. A float which comprises means for recovering an unmanned aerial vehicle (UAV) which is floating in the water.5. A method claim 1 , performed by a wave-powered vehicle (WPV) having communications equipment claim 1 , of monitoring vessels which are floating in water claim 1 , the method comprising:receiving communications from an unmanned aerial vehicle (UAV) on the communications equipment of the WPV; andtransmitting corresponding communications to a receiving station at a remote location.6. A method of monitoring a vessel which is floating in water claim 1 , the method comprising:correlating signals received by a plurality of WPVs to identify the location of the vessel; and{'claim-ref': {'@idref': 'CLM-00002', 'claim 2'}, 'launching a UAV from a WPV according to .'}7. An unmanned aerial vehicle (UAV) which claim 1 , when it lands on water claim 1 , sinks below the surface of water except for a recovery means which remains above the surface of the water.8. An unmanned aerial vehicle (UAV) which can be converted between (1) a collapsed form in which it can be stowed in a tube and (2) an unfolded form which can operate as a UAV and which the UAV adopts automatically when it is released from the tube.9. A float comprising:a hull;{'claim- ...

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Номер записи: 89
25-01-2018 дата публикации

SYSTEMS AND PROCESSES FOR CALIBRATING UNMANNED AERIAL VEHICLES

Номер: US20180024571A1
Автор: Peasgood Michael
Принадлежит:

An unmanned aerial vehicle and process for automatically calibrating the unmanned aerial vehicle having at least one magnetic sensor is described. The calibration process involves receiving an internal or external control command to initiate a take-off process by the unmanned aerial vehicle. A hover mode maintains the unmanned aerial vehicle at hover position, and a calibration rotation sequence rotates the unmanned aerial vehicle. The calibration process further involves receiving measurement data from sensors of the unmanned aerial vehicle during the calibration rotation sequence and calculating calibration parameters using the measurement data. The calibration process may implement corrections using the calibration parameters. 1. An unmanned aerial vehicle comprising:a frame;an operations control to control operation of the unmanned aerial vehicle;a calibration control to initiate automatic calibration of the unmanned aerial vehicle by a hover mode for maintaining the unmanned aerial vehicle at hover position, and a calibration rotation sequence for rotating the unmanned aerial vehicle around at least one axis of the frame;flight control and navigation control for controlling motion of the unmanned aerial vehicle to implement the hover mode and the calibration rotation sequence;sensors to obtain measurement data during the calibration rotation sequence, wherein the sensors include at least one magnetic sensor for calibration;a calibration calculator to calculate calibration parameters using the measurement data obtained during the calibration rotation sequence.2. The unmanned aerial vehicle of wherein the calibration control updates or corrects measurement or compensation values of the magnetic sensor or other instrument using the calibration parameters.3. The unmanned aerial vehicle of wherein the calibration parameters comprise a bias factor and a scale factor.4. The unmanned aerial vehicle of further comprising a communication device to transmit the ...

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Номер записи: 90
28-01-2021 дата публикации

INTEGRATED LANDING GEAR FIRE DETECTION & FATIGUE MONITORING SYSTEM

Номер: US20210024200A1
Автор: Rogers Aaron Stanley
Принадлежит:

A system for an aircraft that includes a plurality of zones including: a first fiber optic cable routed through a zone of the plurality of zones. The first fiber optic cable is attached to a landing gear of the aircraft in the zone of the plurality of zones; and a first controller configured to provide a first optical signal to the first fiber optic cable and obtain a first optical response signal from the first fiber optic cable. The first controller is further configured to determine at least one temperature within the zone of the plurality of zones based on the first optical response signal, the first optical signal, and coherent optical frequency domain reflectometry (COFDR). 1. A system for an aircraft that includes a plurality of zones , the system comprising:a first fiber optic cable routed through a zone of the plurality of zones, wherein the first fiber optic cable is attached to a landing gear of the aircraft in the zone of the plurality of zones; anda first controller configured to provide a first optical signal to the first fiber optic cable and obtain a first optical response signal from the first fiber optic cable;wherein the first controller is further configured to determine at least one temperature within the zone of the plurality of zones based on the first optical response signal, the first optical signal, and coherent optical frequency domain reflectometry (COFDR).2. The system of claim 1 , wherein the first controller is further configured to provide an indication that the at least one temperature is greater than a threshold temperature value within the zone of the plurality of zones.3. The system of claim 1 , wherein the first controller is further configured to determine at least one strain within the zone of the plurality of zones based on the first optical response signal claim 1 , the first optical signal claim 1 , and COFDR.4. The system of claim 3 , wherein the first controller is further configured to provide an indication that the at ...

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Номер записи: 91
29-01-2015 дата публикации

Helicopter rotor load reduction and tip clearance control

Номер: US20150028152A1
Автор: Erez Eller, John Knag
Принадлежит: Sikorsky Aircraft Corp

A method of controlling a helicopter having a rotor with blades is provided. The method includes receiving, by a computing device comprising a processor, at least one input associated with the helicopter; generating, by the computing device, control signals configured to counteract blade bending associated with the rotors based on the received at least one input; measuring, by the computing device, blade signals using sensors for the blades; extracting, by the computing device, harmonic loads from the measured blade signals; adapting, by the computing device, the control signals based on the harmonic loads; and controlling, by the computing device, servos connected to the blades to adjust the blades according to the adapted control signals to reduce vibratory loads on the blades.

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Номер записи: 92
28-01-2021 дата публикации

SYSTEM AND METHOD FOR AUTONOMOUSLY MONITORING HIGHLY AUTOMATED VEHICLE OPERATIONS

Номер: US20210026354A1
Автор: ALVES Erin Elizabeth, FERN Lisa
Принадлежит:

Systems and methods are disclosed for monitoring operations of an autonomous vehicle. For instance, a monitoring device receives sub-system data from one or more sub-systems of the autonomous vehicle. The device receives contextual data of the vehicle that comprises one or more situational circumstances of the vehicle during operation. The device receives control data from a control system of the vehicle and analyzes the sub-system data, the contextual data, and the control data to determine a control result. The device provides an assessment to a management system of the overall control status of the vehicle. 1. A method for monitoring operations of an autonomous vehicle , the method comprising:at a monitoring device, receiving sub-system data from one or more sub-systems of the autonomous vehicle;receiving contextual data of the vehicle, wherein the contextual data comprises data of one or more situational circumstances of the vehicle during operation;receiving control data from a control system of the vehicle;analyzing the sub-system data, the contextual data, and the control data to determine a control result; andproviding an assessment to a management system of an overall control status of the vehicle.2. The method of claim 1 , further comprising providing one or more suggestions to the management system to instruct a modification of one or more control operations of the vehicle.3. The method of claim 2 , further comprising sending a display message to a display device for an operator of the vehicle claim 2 , wherein the display message comprises information about the assessment and the suggestions to modify the control operations.4. The method of claim 1 , wherein the vehicle is an autonomous flight vehicle.5. The method of claim 1 , wherein receiving the contextual data comprises receiving claim 1 , as the contextual data claim 1 , environmental data from sensors of the vehicle and external data of the operation of the vehicle.6. The method of claim 5 , ...

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Номер записи: 93
28-01-2021 дата публикации

System for Identifying Objects by Means of Distributed Neural Networks

Номер: US20210027059A1
Автор: Michael Feigenbutz
Принадлежит: Rockwell Collins Deutschland GmbH

In a system for identifying objects by means of distributed neural networks a resource-intensive proportion of the neural network is provided at a base station (on the ground), whereas a less resource-intensive proportion of the neural network, in particular the remaining proportion of the neural network, is provided at a front end (for example remote-controlled vehicle). The technical complexity for the front-end side and for the transmission of data between the base station and front end can thus be reduced.

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Номер записи: 94
29-01-2015 дата публикации

System, Method, and Apparatus for Smoke Mitigation

Номер: US20150031277A1
Автор: Khera Jagtar S.
Принадлежит:

A smoke mitigation system for an aircraft includes an exhaust shutter in an upper region of a fuselage of the aircraft. The exhaust shutter has a closed position in which the exhaust shutter does not exchange air from outside of the fuselage with air inside of a passenger cabin that is within the fuselage and an open position in which the exhaust shutter exchanges air from outside of the fuselage and inside of the passenger cabin, thereby enabling escape of smoke from the passenger cabin. The system includes one or more devices for opening the exhaust shutter and a device for initiating opening of the exhaust shutter. The device for initiating opening of the exhaust shutter includes mechanisms for determining that it is safe to open the exhaust shutter. 1. A smoke mitigation system for an aircraft , the smoke mitigation system comprising:an exhaust shutter in an upper region of a fuselage of the aircraft, the upper region being one an opposite side of the fuselage than a landing gear, the exhaust shutter having a closed position in which the exhaust shutter does not allow an exchange of air from outside of the fuselage with air inside of a passenger cabin within the fuselage, and the exhaust shutter having an open position in which the exhaust shutter allows the exchange air from the outside of the fuselage with the air/smoke from inside of the passenger cabin, thereby enabling escape of the smoke from the passenger cabin;means for opening the exhaust shutter; andmeans for initiating opening of the exhaust shutter.2. The smoke mitigation system of claim 1 , wherein the means for opening and closing the exhaust shutter comprises a resilient member coupled to the exhaust shutter claim 1 , the resilient members urging the exhaust shutter into the open position claim 1 , the exhaust shutter held in the closed position by an electrically controlled lock whereas release of the electrically controlled lock allows the resilient member to move the exhaust shutter to the open ...

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Номер записи: 95
24-04-2014 дата публикации

Yaw Damping System And Method For Aircraft

Номер: US20140114505A1
Автор: Hagerott Steven G., Klausmeyer Steven, Mendoza Gonzalo E.
Принадлежит: Textron Innovations Inc.

An alternative system for damping the dutch roll mode in an aircraft is provided using roll control surfaces. Classical yaw dampers for the dutch roll mode utilize the yaw control surfaces such as a rudder to dampen the dutch roll mode oscillations. An alternative damper is described that utilizes roll control surfaces such as spoilers or ailerons to dampen the dutch roll mode. 1. A method for damping the dutch roll mode in an aircraft having a roll control surface , comprising the steps of:measuring at least one parameter of the motion of the aircraft;applying a washout filter to the at least one parameter of motion to remove low frequency signals from the measured parameter of motion of the aircraft;calculating a damping signal that is proportional to the at least one parameter of the motion of the aircraft as modified by the washout filter; andactuating the roll control surface in proportion to the damping signal.2. The method of wherein the at least one parameter of motion of the aircraft is selected from the group consisting of a body axis yaw rate claim 1 , a lateral acceleration and a roll rate.3. The method of wherein the step of calculating a damping signal further comprises the steps of calculating a sideslip rate estimate utilizing a measured body axis yaw rate claim 1 , a measured lateral acceleration of the aircraft and a measured airspeed of the aircraft and assuming that an angle of attack of the aircraft is zero.4. The method of wherein the step of calculating a damping signal further comprises the step of calculating a sideslip estimate utilizing the measured lateral acceleration of the aircraft and assuming that a rudder deflection of the aircraft is zero.5. The method of wherein the step of calculating a damping signal further comprises the steps of calculating a derivative function of the at least one parameter of motion; multiplying the derivative function by a proportional gain; and adding the result to the damping signal.6. The method of ...

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Номер записи: 96
29-01-2015 дата публикации

VISUAL LOCALIZATION OF UNMANNED AERIAL VEHICLES BASED ON MARKER DETECTION AND PROCESSING

Номер: US20150032295A1
Автор: Stark James Alexander, Wong Clifford
Принадлежит: Disney Enterprises, Inc.

A method for locating markers in an image captured by a mobile device moving about an operating space. The method includes preprocessing an image to generate a set of image data, locating fixed features of markers by tracing edges of the fixed features, and extracting variable data payloads of each of the markers associated with the located fixed features. The fixed features of each of the markers may include a pair of parallel lines extending along opposite sides of a data area containing the variable data payload, and each of the lines extends a distance beyond each exposed end of the data area to avoid missing data when markers are not arranged orthogonally to the scan direction. The preprocessing involves rotating or skewing the image to provide rotated or skewed versions of the image to facilitate locating markers regardless of their angular orientation in the image. 1. A localization marker adapted for identification with a single scan direction , comprising:a body with an exposed surface; and a fixed pattern; and', 'a data area comprising a variable pattern, wherein the fixed pattern comprises a pair of parallel, linear features that are spaced apart a predefined distance, wherein the data area is sandwiched between the pair of linear features, and wherein each of the linear features has a length greater than a maximum length of components of the variable pattern., 'a marker pattern provided on the exposed surface, the marker pattern including2. The localization marker of claim 1 , wherein the linear features comprise elongated bars with a width of at least 1 pixel.3. The localization marker of claim 1 , wherein a width of the linear features is at least 20 percent greater than the maximum length of the components.4. The localization marker of claim 1 , wherein each of the linear features is positioned on the exposed surface to extend a distance beyond opposite ends of the components of the variable pattern.5. The localization marker of claim 1 , wherein the ...

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Номер записи: 97
17-02-2022 дата публикации

UNIVERSAL VEHICLE WITH IMPROVED STABILITY FOR SAFE OPERATION IN AIR, WATER AND TERRAIN ENVIRONMENTS

Номер: US20220048620A1
Автор: Valente Eduardo Gurgel Do Amaral, Valente Evandro Gurgel do Amaral, Wereley Norman M.
Принадлежит:

The universal vehicle system is designed with a lifting body which is composed of a plurality of interconnected modules which are configured to form an aerodynamically viable contour of the lifting body which including a front central module, a rear module, and thrust vectoring modules displaceably connected to the front central module and operatively coupled to respective propulsive mechanisms. The thrust vectoring modules are controlled for dynamical displacement relative to the lifting body (in tilting and/or translating fashion) to direct and actuate the propulsive mechanism(s) as needed for safe and stable operation in various modes of operation and transitioning therebetween in air, water and terrain environments. 1. A universal vehicle for uncompromised and balanced air , water and terrain travel in various modes of operation and safe transitioning therebetween , comprising:a lifting body composed of a plurality of cooperating modules, configured to form said lifting body with a substantially aerodynamical contour, wherein at least two of said plurality of the lifting body modules are displaceably secured each to the other,said plurality of lifting body modules including at least one thrust vectoring module and at least one propulsive mechanism operatively coupled to said at least one trust vectoring module, wherein said at least one thrust vectoring module is dynamically controlled to affect positioning and actuation of said at least one propulsive mechanism to attain a desired positioning of the vehicle and at least one of a plurality of modes of operation thereof.2. The universal vehicle of claim 1 , wherein said at least one thrust vectoring module includes a nacelle module carrying said at least one propulsive mechanism thereon and rotatively displaceable about an axis extending sidewise said lifting body.3. The universal vehicle of claim 2 , wherein said lifting body further includes a central front module and a rear module coupled to said central front ...

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Номер записи: 98
01-05-2014 дата публикации

METHOD OF MANAGING AN ENGINE FAILURE ON A MULTI-ENGINED AIRCRAFT HAVING A HYBRID POWER PLANT

Номер: US20140117148A1
Автор: Cezard Joris, Connaulte Matthieu, Dyrla Nadine
Принадлежит: EUROCOPTER

A method of managing an engine failure on a rotary wing aircraft () having a hybrid power plant () with at least two fuel-burning engines (′), at least one electric machine (), and a main gearbox (). Said aircraft () also has electrical energy storage means () and a main rotor () mechanically connected to said hybrid power plant (). In said method, during each flight, the operation of said engines (′) is monitored in order to detect a failure of any one of them, and then once a failure of one of said engines (′) has been detected, said electric machine () is controlled, if necessary, to deliver auxiliary power Win order to avoid a deficit appearing in the total power Wof said hybrid power plant (), thereby enabling the pilot of said aircraft () to fly said aircraft () safely without degrading said hybrid power plant (). 1. A method of managing an engine failure on a rotary wing aircraft , said aircraft comprising:{'sub': 'T', 'a hybrid power plant having at least two fuel-burning engines, at least one electric machine, a main gearbox “MGB”, and at least one electronic engine control unit “EECU”, each EECU being connected to a respective engine, each engine being capable of delivering at least a maximum continuous power MCP rating and OEI 30″, OEI 2′, and OEI Cont power ratings, said hybrid power plant delivering total driving power Wto said MGB;'}at least one electrical energy storage means; and{'sub': 'r', 'at least one main rotor that is driven in flight at an instantaneous speed of rotation Nby said hybrid power plant;'} a checking step, in which the operation of each engine is checked during each flight by means of said EECU in order to detect a failure, if any, of at least one engine, an engine being considered as having failed when at least one other engine delivers said OEI power rating;', {'sub': T', 'T', 'T', 'P, 'a monitoring step during which a monitoring value is determined relating to at least one monitoring parameter of said aircraft and a detection ...

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Номер записи: 99
30-01-2020 дата публикации

METHOD AND A DEVICE FOR MANAGING THE ENERGY OF A HYBRID POWER PLANT OF A MULTI-ROTOR AIRCRAFT

Номер: US20200031481A1
Автор: FAURE Bernard, GAZZINO Marc
Принадлежит: AIRBUS HELICOPTERS

A method and to a device for managing energy of a hybrid power plant of a multi-rotor aircraft during a flight. The hybrid power plant comprises a thermal engine, an electricity generator, and a plurality of electric motors, together with a plurality of electrical energy storage devices. The aircraft has a plurality of rotors driven in rotation by respective electric motors. The flight of the aircraft comprises a takeoff stage, a cruising stage, and a landing stage, the takeoff stage and the landing stage being performed solely while consuming electrical energy. The method enables an electrification ratio Rof the flight to be calculated as a function of the amounts of electrical and thermal energy that are consumed during the takeoff, landing, and cruising stages, thereby limiting the use of the thermal engine to the least possible amount during the cruising stage, and consequently reducing the associated nuisance. 5. The method according to claim 1 , wherein an operational energy reserve Eis deducted from the total available electrical energy E.8. The method according to claim 7 , wherein in the event of an emergency and/or danger claim 7 , the normal utilization coefficient k1 is replaced by an emergency coefficient k2 that is strictly greater than k1 and strictly less than 1.9. The method according to claim 1 , wherein the thermal energy source comprises at least one thermal engine claim 1 , and the hybrid power plant includes a main power transmission gearbox (MGB) driving the rotors in rotation claim 1 , the thermal engine(s) and the electrical machine(s) driving the MGB in rotation.10. The method according to claim 9 , wherein the hybrid power plant includes an electricity generator driven in rotation by the MGB or else directly by at least one thermal engine.11. The method according to claim 1 , wherein the thermal energy source comprises at least one thermal engine claim 1 , and the hybrid power plant comprises an electricity generator and as many electric ...

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Номер записи: 100