Поиск патентов

Настройки

Глубина выборки

Укажите год

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

Подробнее

Мониторинг СМИ

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

Подробнее

Форма поиска

Ключевые слова. Может быть несколько по одной на строку

Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка

Автор

Ведите корректный номера.

Владелец

Ведите корректный номера.

Классы IPC

Ведите корректный номера.

Классы CPC

Ведите корректный номера.

Начиная с года

Укажите год

Заканчивая годом

Укажите год

Применить Всего найдено 15181. Отображено 100.

05-01-2012 дата публикации

Wing of an aircraft and assembly of a wing comprising a device for influencing a flow

Номер: US20120001028A1

Автор: Burkhard Goelling, Heinz Hansen, Juergen Frey, Klaus-Peter Neitzke, Veit Hildebrand

Принадлежит: AIRBUS OPERATIONS GMBH

A wing of an aircraft is described, having: a main wing, at least one high lift flap which can be moved between a retracted and an extended position, and a spoiler. The main wing has ejection openings, arranged side-by-side along the main wing spanwise direction, and in the main wing chordwise direction, and which are connected via an air conduit with the outlet device of a flow delivery driver device on the main wing or on the spoiler. The spoiler has inlet openings for the intake of air, which are connected via an air conduit with the inlet device of the flow delivery driver device. The flow delivery driver device has a receiver device for the reception of command signals for purposes of adjustment of the flow delivery driver device. An arrangement of a wing with a device for purposes of flow control with such a wing is also described.

Подробнее

Номер записи: 1

23-02-2012 дата публикации

High-lift flap, arrangement of a high-lift flap together with a device for influencing the flow on the same and aircraft comprising said arrangement

Номер: US20120043428A1

Автор: Burkhard Goelling, Christoph Jensch, Heinz Hansen, Kai-Christoph Pfingsten, Klaus-Peter Neitzke, Rolf Radespiel

Принадлежит: AIRBUS OPERATIONS GMBH

An aerodynamic body of an aircraft with an air outlet opening and an air intake opening that communicates with the air outlet opening via an air conduit is described. A flow delivery driver device for influencing the flow within the air conduit is integrated into the air conduit. The surfaces of the aerodynamic body in the body chord direction include at least one air outlet opening in the front region of the aerodynamic body, and at least one air intake opening on the upper surface of the aerodynamic body and in the rear region of the aerodynamic body and/or on the upper surface of the aerodynamic body in the trailing edge region and/or on the lower surface of the aerodynamic body in the trailing edge region. Arrangements of a main wing and an adjustable flap, and an aircraft with such an aerodynamic body are also described.

Подробнее

Номер записи: 2

22-03-2012 дата публикации

Active Aircraft Pylon Noise Control System

Номер: US20120068011A1

Автор: Alaa A. Elmiliqui, Michael J. Czech, Russell H. Thomas

Принадлежит: National Aeronautics and Space Administration NASA

An active pylon noise control system for an aircraft includes a pylon structure connecting an engine system with an airframe surface of the aircraft and having at least one aperture to supply a gas or fluid therethrough, an intake portion attached to the pylon structure to intake a gas or fluid, a regulator connected with the intake portion via a plurality of pipes, to regulate a pressure of the gas or fluid, a plenum chamber formed within the pylon structure and connected with the regulator, and configured to receive the gas or fluid as regulated by the regulator, and a plurality of injectors in communication with the plenum chamber to actively inject the gas or fluid through the plurality of apertures of the pylon structure.

Подробнее

Номер записи: 3

24-05-2012 дата публикации

Floor for an aircraft cargo compartment and method for the assembly thereof

Номер: US20120126057A1

Автор: Andreas Patzlsperger, Richard Holzner, Thomas Huber

Принадлежит: Telair International GmbH

In conventional aircraft cargo compartments panels or similar flat floor elements are fastened to floor beams or similar supporting elements that are installed in the body of the aircraft. Subsequently functional units such as roller elements, latches or PDUs are mounted and connected to one another by way of appropriate control conductors. It is proposed to fasten the floor elements permanently to the supporting beams so as to form prefabricated floor modules and to install these floor modules in the aircraft.

Подробнее

Номер записи: 4

14-06-2012 дата публикации

Pylon for fixing an aircraft engine having unducted pusher propellers

Номер: US20120145824A1

Автор: Gaetan Jean Mabboux, Jean Bertucchi, Stephane Emmanuel Daniel Bensilum

Принадлежит: SNECMA SAS

A pylon for fixing an aircraft engine having unducted pusher propellers, the pylon ensuring the fixation of a propulsive system on the boattail of the aircraft, the pylon having a trailing edge, with an upper face and a lower face, for an airflow encountered by the pylon, wherein at least one of the two faces of the upper face and the lower face of the trailing edge is inclinable, at least in part.

Подробнее

Номер записи: 5

04-10-2012 дата публикации

Plasma Actuated Vortex Generators

Номер: US20120248072A1

Автор: Dennis B. Finley, Paul D. McClure, Sergey Macheret

Принадлежит: Lockheed Martin Corp

A plasma-actuated vortex generator arrangement includes a plurality of spaced-apart vortex generators, and a plasma actuator distributed amongst the plurality of vortex generators.

Подробнее

Номер записи: 6

31-01-2013 дата публикации

Flow body, in particular for aircraft

Номер: US20130025727A1

Автор: Geza Schrauf, Martin Gerber

Принадлежит: AIRBUS OPERATIONS GMBH

A flow body is disclosed, particularly for aircraft. The flow body includes an outer side impinged on in a predetermined manner by a fluid in a direction of impinging flow, the flow body having on its outer side at least one flow control device including micro-perforations arranged in at least one segment of the outer side, at least one connecting passage communicated with the micro-perforations via at least one suction chamber so fluid flowing through the micro-perforations flows via the suction chamber into the connecting passage, at least one suction device having a first inlet communicated with the connecting passage, a second inlet communicated with at least one ram fluid feed line, wherein the ram fluid feed line is in a region of the flow body opposite to the direction of impinging flow of the flow body, and an outlet device for discharging the fluid.

Подробнее

Номер записи: 7

31-01-2013 дата публикации

Aerodynamic surface with improved properties

Номер: US20130028744A1

Автор: Göte Strindberg, Pontus Nordin

Принадлежит: SAAB AB

An article including an outer surface that serves as an aerodynamic surface when the article is subjected for an air stream. A resin matrix made of a polymeric composite laminate of at least one ply includes the outer surface. The at least one ply includes a nano structure embedded therein such that nano filaments of the nano structure in the ply essentially have the same angular orientation relative the plane of the outer surface. The outer ply is a ply of a laminate including at least two plies. Each ply includes large fibers having an orientation different from or identical to the orientation of large fibers of an adjacent ply.

Подробнее

Номер записи: 8

14-03-2013 дата публикации

Surface entity for the reduction of the air resistance of an aviation vehicle

Номер: US20130062469A1

Автор: Freerk Syassen, Metin Cengiz

Принадлежит: AIRBUS OPERATIONS GMBH

The invention concerns a surface entity for the reduction of the air resistance of an aviation vehicle, in particular an aircraft. In accordance with the invention the surface entity is formed with at least one metal wire arrangement, in particular with a metal mesh and/or a composite mesh, which can be arranged in at least some sections in the region of at least one surface of the aviation vehicle immersed in the flow, in particular can be adhesively bonded and/or clamped onto the latter, wherein the metal wire arrangement has a ribbed structure with a multiplicity of ribs running essentially parallel to one another. As a consequence of the multiplicity of ribs running parallel to the flow direction, the arrangement of which can be compared with the structure of the sharkskin of known art, there ensues a reduction of the flow resistance of the surface on or over which the air flows of between 3% and 10%, as a result of which a significant fuel saving potential ensues in flight operations. In comparison to polymer films of prior known art with a surface structure similar to that of the sharkskin a significantly higher resistance to erosion ensues. The metal wire arrangement can be formed with a metal mesh and/or with a composite mesh thermally joined at the crossing points.

Подробнее

Номер записи: 9

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.

Подробнее

Номер записи: 10

07-01-2021 дата публикации

INTEGRATED SYSTEM FOR CONTROLLING, DETECTING, MONITORING, EVALUATING AND TREATING CROP PESTS

Номер: US20210000097A1

Автор: BOLLATI Luciana V., CHIAPERO Ezequiel Manavela, MARCHESINI Gerardo R., SEQUEIROS Walter Daniel

Принадлежит:

An automated system for monitoring and treating pests in a crop field, comprising at least one trap for monitoring and identifying pests, at least one UA V containing at least one chemical or biological products; a home base for parking or storing said at least one UA V when they are not operating; at least one database server; and equipment for communicating with said at least one trap, said at least one home base, said at least one UA V and said at least one database server. 1. An automated system for monitoring and treating pests in a crop field; said system comprising: i. a pest attraction component;', 'ii. an adhesive pad configured for immobilizing attracted pests;', 'iii. a sensor arrangement for locating and identifying said attracted pests;, 'a. at least one trap for monitoring and identifying pests; said at least one trap having known coordinates; said at least one trap comprising i. means for carrying and dispensing at least one chemical;', 'ii. a positioning unit for tracking coordinates of said at least one UAV at all times;, 'b. at least one UAV comprisingc. a home base for parking or storing said at least one spraying UAV;d. at least one database server;e. a communication unit interconnecting said at least one trap, said at least one home base, said at least one UAV and said at least one database server;f. software configured for creating and maintaining a map of said pests detected and identified by said at least one trap having known coordinates in said crop field and cultivated plants therewithin; said software configured for determining desirable pest control measures applicable to said crop field and cultivated plants therewithin by means of said at least one UAV carrying and dispensing at least one chemical;g. a flight controller for controlling said at least one UAV according to pest control measures by determined by said software.2. The system according to claim 1 , wherein said sensor arrangement comprising a sensor configured for locating ...

Подробнее

Номер записи: 11

04-01-2018 дата публикации

UNMANNED AERIAL VEHICLE-BASED SYSTEM FOR LIVESTOCK PARASITE AMELIORATION

Номер: US20180000575A1

Автор: Fobi Simone, PICKOVER Clifford A., Weldemariam Komminist Sisai

Принадлежит:

Parasites are detected and ameliorative actions taken using unmanned aerial vehicles equipped with sensors and equipment for dispensing treatment materials. Physical characteristic data obtained by the sensors is supplemented using a risk management module that increases the confidence level that the diagnosis of a particular parasite on an animal is correct. The risk management module may further be used to assess additional factors, such as the potential harm in applying a selected treatment, in the decision of whether or not to take ameliorative action. 1. (canceled)2. (canceled)3. The method of claim 6 , wherein the one or more sensors include an acoustic sensor.4. The method of claim 6 , wherein the plurality of factors include animal presence in a risk area and weather.5. (canceled)6. A method for addressing potential parasite infestations claim 6 , comprising:obtaining a first unmanned aerial vehicle including one or more sensors for detecting physical characteristics of an animal and/or parasites afflicting the animal;launching the first unmanned aerial vehicle;locating the first unmanned aerial vehicle in proximity to an animal;obtaining physical characteristic data by sensing one or more physical characteristics of the animal and/or a parasite using the one or more sensors;accessing a risk management module configured for assessing a plurality of factors that contribute to parasite infestation of animals;assessing the plurality of factors that contribute to parasite infestation using the risk management module in combination with the physical characteristic data to identify a particular parasite, andbased on the assessed plurality of factors and the physical characteristic data, causing an ameliorative action addressing a parasitic infection of the animal by the particular parasite to be administered by one or more unmanned aerial vehicles,wherein the one or more sensors include a visual image sensor,wherein the risk management module is further configured ...

Подробнее

Номер записи: 12

06-01-2022 дата публикации

AIRCRAFT ROTOR PROTECTION

Номер: US20220001977A1

Автор: Netzer Yoav

Принадлежит:

Embodiments of the disclosure are directed to a convertible rotor aircraft CRA able to convert between airplane and helicopter flight modes during flight, comprising a tillable proprotor assembly TPA comprising a proprotor. Optionally, the CRA comprises a flight control module FCM configured to control the TPA to reverse direction of thrust generated by the proprotor relative to the TPA when the TPA transitions between a first orientation for helicopter flight and a second orientation for airplane flight. Optionally, the CRA comprises a deployable guard for the proprotors, configured to have a stowed state and a deployed state, wherein: the guard in the deployed state is controlled to be configured as a partially air-permeable barrier. 110-. (canceled)11. An aircraft comprising: the rotor guard in the deployed state is controlled to be configured as a partially air-permeable barrier and positioned so that thrust produced by a rotor is directed towards the partially air-permeable barrier; and', 'the rotor guard in the stowed state is controlled to be configured to reduce impedance of the thrust compared to the deployed state., 'at least one deployable rotor guard configured to have a stowed state and a deployed state, wherein12. The aircraft of claim 11 , wherein the partially air-permeable barrier comprises a plurality of slats pivotably connected to a portion of the aircraft.13. The aircraft of claim 12 , wherein the partially air-permeable barrier comprises the plurality of slats claim 12 , which are arranged substantially along a common plane with gaps between adjacent slats.14. The aircraft of claim 11 , wherein the partially air-permeable barrier comprises a partially air-permeable panel pivotably connected to a portion of the aircraft.15. The aircraft of claim 14 , wherein partially air-permeable panel comprises a selection from: an array of intersecting or parallel slats claim 14 , an array of intersecting or parallel wires claim 14 , and a wire mesh.16. The ...

Подробнее

Номер записи: 13

06-01-2022 дата публикации

GROUP CONFIGURATIONS FOR A MODULAR DRONE SYSTEM

Номер: US20220001980A1

Автор: Davis Eric Alan, Gerard Michael Dwight, McKeehan David Williams, Nehrkorn Craig Alan

Принадлежит:

A modular flat-packable drone kit includes a plurality of components that can be assembled into a drone. Components of the drone kit include elements that may be cut from a flat sheet of material, thereby enabling low cost manufacturing and compact packaging and may be assembled without specialized tools. A set of drones may operate in a standalone mode or may be coupled together and operated in a group configuration. 1. A drone system comprising:a set of drones each configurable between respective standalone configurations and a group configuration, wherein the set of drones are detached from each other and configurable to execute independent flights when configured in the standalone configuration and wherein the set of drones are coupled together and execute a group flight when configured in the group configuration;a connector system to connect the set of drones together when configured in the group configuration;a set of flight controllers each configurable between at least a standalone flight controller mode and a master flight controller mode, wherein a first flight controller of the set of flight controllers is configured to control the flight of a first drone of the set of drones when configured in the standalone flight controller mode and is configured to control the group flight of the group configuration when configured in the master flight controller mode.2. The drone system of claim 1 , wherein the set of flight controllers are further configurable in an auxiliary controller mode claim 1 , wherein at least a second flight controller of the set of flight controllers is configured to control an auxiliary function of the group configuration when the second flight controller is configured in the auxiliary controller mode.3. The drone system of claim 1 , wherein the auxiliary function comprises at least one of:controlling a camera;performing image processing of data from the camera;processing auxiliary sensor data;controlling a projectile device;controlling a ...

Подробнее

Номер записи: 14

06-01-2022 дата публикации

PRECISION DELIVERY VEHICLE

Номер: US20220001983A1

Автор: Groen David

Принадлежит:

A precision delivery vehicle having a vehicle body assembly, a fixed wing system, a rotor system and a guidance system. The vehicle body assembly can retain a payload. The fixed wing system includes first and second wings coupled to the vehicle body for fixed wing flight. The rotor system includes a mast structure, a rotor hub rotatable about the mast structure and at least two rotor blades coupled to the rotor hub and rotatable with the rotor hub relative to the mast structure. The at least two rotor blades are movable between a collapsed configuration and a deployed configuration. In the collapsed configuration, the precision delivery vehicle is in fixed wing flight. Upon placement of the at least two rotor blades into the deployed configuration, the precision delivery vehicle is placed into rotative flight. The guidance system is structurally configured to direct the precision delivery vehicle to a target. 19.-. (canceled)10. A precision delivery vehicle comprising:a vehicle body assembly having a central elongated fuselage, a nose portion at a first end of the central elongated fuselage and a tail portion at a second end of the central elongated fuselage, the vehicle body assembly configured to retain a payload;a fixed wing stabilizer system positioned at the second end of the central elongated fuselage; a first foldable wing;', 'a second foldable wing; and', 'a pivot structure configured to direct the first and second foldable wings between a collapsed configuration and a deployed configuration;, 'a fixed wing system positioned between the first end and the second end of the central elongated fuselage, the fixed wing system including a mast structure attached to the vehicle body assembly;', 'a rotor hub rotatably coupled to the mast structure;', 'a first blade having a root portion coupled to the rotor hub, and an elongated blade portion hingedly coupled to the root portion; and', 'a second blade having a root portion coupled to the rotor hub, and an elongated ...

Подробнее

Номер записи: 15

06-01-2022 дата публикации

Fixed-Wing VTOL Aerial Vehicle

Номер: US20220001996A1

Автор: TIAN YU

Принадлежит:

A long-distance drone is disclosed having a canard wing configuration with a cabin attached to a left main wing and a right main wing. There is a left forewing and a right forewing connected together to form a single-piece forewing. There is a left linear support connecting the left forewing to the left main wing, and a right linear support connecting the right forewing to the right main wing. A plurality of propellers is disposed on the left and the right linear supports. 1. A hybrid VTOL fixed-wing drone comprising:a cabin;a left main wing and a right main wing coupled to the cabin;a left linear alignment of propellers having a first propeller, a second propeller, and a third propeller all of which are disposed on said left linear support;a right linear alignment of propellers having a fourth propeller, a fifth propeller, and a sixth propeller all of which are disposed on said right linear support;wherein the left linear support is parallel to the right linear support;a left forewing disposed on a front end of the left linear support;a right forewing disposed on a front end of the right linear support;wherein the left forewing is directly connected to the right forewing;wherein the left forewing and the right forewing are not directly connected to the cabin.2. The hybrid VTOL fixed-wing drone as recited in claim 1 , wherein the left main wing and the right main wing forms a dihedral configuration.3. The hybrid VTOL fixed-wing drone as recited in claim 2 , wherein the left main wing and the right main wing each has a proximal portion disposed entirely within a space between the left and the right linear supports claim 2 , wherein the proximal portions of the left and the right main wings forms a dihedral configuration.4. The hybrid VTOL fixed-wing drone as recited in claim 2 , wherein the left main wing and the right main wing each has a distal portion claim 2 , wherein the distal portions of the left and the right main wings forms a dihedral configuration.5. The ...

Подробнее

Номер записи: 16

07-01-2021 дата публикации

RECONFIGURABLE BATTERY-OPERATED VEHICLE SYSTEM

Номер: US20210001700A1

Автор: Belik Pavel, Fisher Christopher E., McAllister Justin B., Schmalzel Marc L., Tokumaru Phillip T., Torres Gabriel E., Tyler Jeremy D., Zwaan John Peter

Принадлежит: AeroVironment, Inc.

A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached. 1. An unmanned vehicle configured for a range of missions , comprising:a battery module having battery capacity adequate to provide motive force for the vehicle over the range of missions, the battery module having a plurality of electronic connection ports;a control module including a control system configured to control the operation of the vehicle over the range of missions, the control module being directly and removably structurally carried by the battery module, and the control module being directly and removably electronically connected to the battery module via a first connection port of the plurality of connection ports; anda first propulsion module including a motor configured to provide propulsive force to move the vehicle through one or more missions of the range of missions, the first propulsion module being directly and removably structurally connected to the battery module via a second connection port of the plurality of connection ports.2. The vehicle of claim 1 , and further comprising a second propulsion module including a motor configured to provide propulsive force to move the vehicle through the one or more missions of the range of missions claim 1 , the second propulsion module being directly and removably structurally connected to the battery module via a ...

Подробнее

Номер записи: 17

03-01-2019 дата публикации

AIRBORNE MATERIAL SPREADING ASSEMBLY AND METHOD FOR SPREADING MATERIAL

Номер: US20190001352A1

Автор: Guérin Johnny, Roy Antoine, Turcotte Samuel

Принадлежит:

A spreading assembly is provided. The spreading assembly comprises a spreadable material container, a spreading mechanism, and a motor. The spreading mechanism is rotatably mounted to a bottom section of the material container and can disperse the spreadable material 360° around the spreading assembly. The motor is operatively connected to the spreading mechanism to engage same in rotation. The spreading assembly comprises a coupling assembly to engage the spreading assembly with an unmanned aerial vehicle (UAV) configured to transport the spreading assembly while it operates. 1. A spreading assembly for dispersing spreadable material , the spreading assembly comprising:a spreadable material container defining a container interior volume and having at least one material outlet opening in material communication with the container interior volume and through which the spreadable material contained in the container interior volume can exit;a spreading mechanism rotatably mounted to the spreading container and including a dispersion tube having at least a section extending outwardly of the spreadable material container, the dispersion tube having at least one inlet aperture being in material communication with the container interior volume to allow a flow of the spreadable material between the container interior volume and the dispersion tube, the dispersion tube having at least one outlet aperture through which the spreadable material can exit the dispersion tube and be dispersed in an area surrounding the spreading assembly; anda motor operatively connected to the dispersion tube of the spreading mechanism to engage the dispersion tube in rotation.2. The spreading assembly according to claim 1 , wherein the spreadable material container comprises a coupling assembly engageable with an unmanned aerial vehicle (“UAV”).3. The spreading assembly according to claim 2 , wherein the coupling assembly comprises a spreader attachment secured to the spreading assembly claim 2 , ...

Подробнее

Номер записи: 18

06-01-2022 дата публикации

Aerial Delivery Systems using Unmanned Aircraft

Номер: US20220004204A1

Автор: McCullough John Richard, Oldroyd Paul K.

Принадлежит: Textron Innovations Inc.

A package delivery system uses unmanned aircraft operable to transition between thrust-borne lift in a VTOL configuration and wing-borne lift in a forward flight configuration. Each of the aircraft includes an airframe having at least one wing with a distributed thrust array coupled to the airframe. The distributed thrust array includes a plurality of propulsion assemblies configured to provide vertical thrust in the VTOL configuration and a plurality of propulsion assemblies configured to provide forward thrust in the forward flight configuration. A package delivery module is coupled to the airframe. A control system is operably associated with the distributed thrust array and the package delivery module. The control system is configured to individually control each of the propulsion assemblies and control package release operations of the package delivery module. The system includes a ground station configured to remotely communicate with the control systems of the aircraft during package delivery missions. 1. An aerial delivery system comprising:a plurality of unmanned aircraft operable to transition between thrust-borne lift in a VTOL configuration and wing-borne lift in a forward flight configuration, each aircraft including:an airframe having at least one wing;a distributed thrust array coupled to the airframe, the distributed thrust array including a first plurality of propulsion assemblies configured to provide vertical thrust in the VTOL configuration of the aircraft and a second plurality of propulsion assemblies configured to provide forward thrust in the forward flight configuration of the aircraft;a package delivery module coupled to the airframe; anda control system operably associated with the distributed thrust array and the package delivery module, the control system configured to individually control each of the propulsion assemblies and the control system configured to control package release operations of the package delivery module; anda ground ...

Подробнее

Номер записи: 19

07-01-2021 дата публикации

DRONE ROTOR CAGE

Номер: US20210001977A1

Автор: Oberndorfer Fabian

Принадлежит:

Disclosed is a drone rotor cage. The drone rotor cage may include a motor housing, a plurality of spars, and a plurality of ribs. The plurality of spars may extend from the motor housing. Each of the plurality of spars may have a spar height and a spar thickness. The spar height may be greater than the spar thickness. Each of the ribs may extend from a respective one of the plurality of spars. Each of the plurality of ribs may have a rib height and a rib thickness. The rib height may be greater than the rib thickness. The plurality of spars and the plurality of ribs may define a space sized to allow a rotor to spin freely when the rotor cage is attached to a drone. 1. (canceled)2. A drone propeller cage comprising:a motor housing;a rotor arm connector;a plurality of ribs extending from the motor housing, the plurality of ribs including at least a first rib and a second rib; anda plurality of spars including at least a first spar and a second spar, the first spar located above the rotor arm connector, each of the plurality of ribs coupled to at least one of the plurality of spars, and each of the first and second spars having a spar height and a spar thickness, the spar height being greater than the spar thickness;the plurality of ribs and the plurality of spars arranged to define a space that is sized to allow a propeller to spin freely when the propeller cage is mounted to a drone.3. The drone propeller cage of claim 2 , each of the first and second ribs having a rib height and a rib thickness claim 2 , wherein the rib height is greater than the rib thickness.4. The drone propeller cage of claim 2 , wherein the spar height and a rib thickness of at least one respective spar and rib are equal.5. The drone propeller cage of claim 2 , wherein the spar height is at least twice the spar thickness.6. The drone propeller cage of ; the plurality of spars further including a third spar positioned between the first spar and the second spar.7. The drone propeller cage of ...

Подробнее

Номер записи: 20

07-01-2021 дата публикации

POSITION DETERMINATION OF MOBILE OBJECTS

Номер: US20210001981A1

Автор: IHALAINEN Tero Johannes, KOLMONEN Veli-Matti, Li Zexian, MOISIO Martti Johannes, Uusitalo Mikko Aleksi

Принадлежит:

An apparatus, method and computer program is described comprising: determining that a first mobile object requires positioning assistance based on one or more predetermined criteria, wherein the predetermined criteria includes whether one or more properties of a planned or predicted future position of the first mobile object have been identified as insufficient, or are predicted as being insufficient, for determining the position of the first mobile object with a required level of accuracy; and responsive to said determination, causing deployment of one or more movable devices (e.g. UAVs) to a target position for providing the required positioning assistance to said first mobile object. 1. An apparatus comprising: at least one processor; and at least one memory including computer program code which , when executed by the at least one processor , causes the apparatus:to determine that a first mobile object requires positioning assistance based on one or more predetermined criteria, wherein the predetermined criteria comprises whether one or more properties of a planned or predicted future position of the first mobile object have been identified as insufficient, or are predicted as being insufficient, for determining the position of the first mobile object with a required level of accuracy;responsive to said determination, to cause deployment of one or more movable devices to a target position for providing the required positioning assistance to said first mobile object.2. The apparatus of claim 1 , wherein one or more of the one or more movable devices is/are unmanned aerial vehicles.3. The apparatus of claim 1 , further comprising:to determine a required level of accuracy of the first mobile object based on its type or its current application.4. The apparatus of claim 1 , wherein the planned or predicted future position of the first mobile object is determined based on the current position of the first mobile object and one or more prior locations of the first ...

Подробнее

Номер записи: 21

07-01-2021 дата публикации

AUTONOMOUS MULTI-ROTOR AIRPLANE

Номер: US20210001983A1

Автор: Fredsted Thomas Vestergaard

Принадлежит: Broelstaerk ApS

An autonomous multi-rotor airplane comprises a body frame with a chamber. The chamber is configured to provide space for one or more skydivers or jumpers, a lifting platform having an onboard computer and an avionic system. The airplane comprises one or more propulsion systems operably coupled to the lifting platform. The airplane is configured to find and execute the optimal flight path based on given information by the operator. The airplane comprises one or more user interfaces securely positioned inside the chamber. The user interfaces are configured to enable the skydiver to view the location and the optimal flight path, and adjust the angle of the autonomous multi-rotor airplane against the wind direction. The user interface is configured to enable the skydiver to operate and land the autonomous multi-rotor airplane at a landing zone. 1. An autonomous multi-rotor airplane comprising a body frame having a chamber , wherein the chamber is configured to provide space for one or more skydivers or jumpers , a lifting platform having an onboard computer and an avionic system , wherein the lifting platform is configured to securely affixed to a top portion of the body frame via a plurality of supporters , and one or more propulsion systems operably coupled to the lifting platform via a plurality of supporting arms , wherein the propulsion systems are configured to lift the autonomous multi-rotor airplane , thereby flying and climbing to desired altitudes with the skydivers for a freefall using a parachute via an optimal flight path based on a control input given by an operator via the onboard computer positioned in the lifting platform , characterized by:the airplane is configured to find and execute the optimal flight path based on given information by the operator, wherein the information includes wind direction, wind speed, and desired altitudes, confirmation of take-off position and landing position, and confirmation of the skydiver's exit point/drop zone and ...

Подробнее

Номер записи: 22

07-01-2021 дата публикации

Optical path length adjustment

Номер: US20210002000A1

Автор: Zisheng Cao

Принадлежит: SZ DJI Technology Co Ltd

A system for adjusting an optical path length includes: a camera body; an image sensor coupled to the camera body; a first optical device coupled to the camera body; and a second optical device coupled to the camera body. At least one of the first and the second optical devices are movable relative to the camera body. The optical path length between the image sensor and the camera body opening is continuously adjusted by movement of the at least one of the first and the second optical devices relative to the image sensor. As the at least one of the first and the second optical devices move relative to the image sensor, the first optical device is in continuous contact with the second optical device.

Подробнее

Номер записи: 23

07-01-2016 дата публикации

VERTICAL TAKE-OFF AND LANDING AERIAL VEHICLE

Номер: US20160001875A1

Автор: Briod Adrien, Daler Ludovic, Garnier Arnaud

Принадлежит: ECOLE POLYTECHNIQUE FEDERALE DE LAUSANNE (EPFL)

A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The VTOL may also include a decoupling mechanism having either a linear or non-linear beam coupled to a ring. The beam may optionally include sliders at ends thereof that provide an additional rotation freedom to the inner frame. 1. A vertical take-off and landing (VTOL) aerial vehicle , comprising:an outer frame; and, 'an inner frame connected to the outer frame by the decoupling mechanism, the inner frame comprising a propulsion system configured to generate a lift force;', 'a decoupling mechanism; and'}the decoupling mechanism comprising a beam coupled to the inner frame and forming a first rotation axis, and the beam being coupled to a second rotation axis substantially orthogonally disposed with respect to the first rotation axis.2. The VTOL aerial vehicle of claim 1 , wherein the inner frame has a center of mass substantially in line with each rotation axis.3. The VTOL aerial vehicle of claim 1 , wherein the first rotation axis is substantially vertical.4. The VTOL aerial vehicle of claim 1 , wherein the beam is non-linear.5. The VTOL aerial vehicle of claim 1 , wherein the propulsion system comprises four propellers claim 1 , at least portions of two of the propellers overlapping.6. The VTOL aerial vehicle of claim 1 , wherein the propulsion system comprises four propellers claim 1 , at least portions of two of the propellers overlapping.7. The VTOL aerial vehicle of claim 1 , wherein the beam is comprised of two parallel portions claim 1 , one of the parallel portions being in axial alignment with a center of mass of the VTOL aerial vehicle.8. The VTOL aerial vehicle of claim 1 , further comprising a ring coupled to the beam and the ring coupled to the outer frame in a third rotation axis claim 1 , the second ...

Подробнее

Номер записи: 24

07-01-2016 дата публикации

EASY LANDING DRONE

Номер: US20160001878A1

Автор: LEE Ki-Seong

Принадлежит:

Disclosed is an easy landing drone. The drone includes: a propeller changing direction; a propeller tower supporting the propeller; a body connected to the propeller tower; a main wing arranged left-right symmetrically with respect to a horizontal axis of the body and having a pair of holes around a center of gravity of the body; a pair of auxiliary wings disposed in the pair of holes, respectively; and an actuator connected to a base shaft fixed to the main wing through the pair of auxiliary wings and controlling angles of the pair of auxiliary wings. 1. An easy landing drone comprising:a propeller changing direction;a propeller tower supporting the propeller;a body connected to the propeller tower;a main wing arranged left-right symmetrically with respect to a horizontal axis of the body and having a pair of holes around a center of gravity of the body;a pair of auxiliary wings disposed in the pair of holes, respectively; andan actuator connected to a base shaft fixed to the main wing through the pair of auxiliary wings and controlling angles of the pair of auxiliary wings,wherein the actuator includes a first actuator and a second actuator,the pair of auxiliary wings includes a first auxiliary wing and a second auxiliary wing,an angle of the first auxiliary wing is controlled by the first actuator,an angle of the second auxiliary wing is controlled by the second actuator, andthe propeller looks forward in flight and looks upward in landing.2. The drone of claim 1 , wherein the propeller includes a plurality of blades converting engine torque into thrust claim 1 , a housing combined with the blades claim 1 , and a turning neck connecting the housing and the propeller tower to each other claim 1 , andthe thrust is 40 to 60% of weight of the drone.3. The drone of claim 2 , wherein in the propeller claim 2 , the blades and the housing look forward when the drone is flying claim 2 , and the blades and the housing are turned upward by the turning neck when the drone is ...

Подробнее

Номер записи: 25

07-01-2016 дата публикации

METHOD FOR OPERATING A RADIO-CONTROLLED FLYING HOVERCRAFT

Номер: US20160001882A1

Автор: Pedersen Brad, Spirov Peter

Принадлежит:

A homeostatic flying hovercraft preferably utilizes at least two pairs of counter-rotating ducted fans to generate lift like a hovercraft and utilizes a homeostatic hover control system to create a flying craft that is easily controlled. The homeostatic hover control system provides true homeostasis of the craft with a true fly-by-wire flight control and control-by-wire system control. 1providing an RC flying hovercraft having a set of generally downwardly directed thrusters, each thruster including at least one blade driven by a battery powered motor to provide aerodynamic lift for the RC flying hovercraft under control of a control system in the RC flying hovercraft that is responsive to radio frequency (RF) communications from the RC controller;causing an RF receiver in the control system in the RC flying hovercraft to receive communications from the RC controller, the communications including a desired orientation of the RC flying hovercraft, wherein the desired orientation communicated by the RC controller is determined based on a handheld structure housing a sensor system in the RC controller that senses at least a two dimensional, two-axis sensed orientation of the handheld structure as a result of a user remote from the RC flying hovercraft selectively orienting the handheld structure;causing a sensor system in the control system of the RC flying hovercraft to dynamically determine an actual orientation of the RC flying hovercraft, the sensor system including at least a three-dimensional, three-axis sensor; andcausing the control system in the RC flying hovercraft to automatically and dynamically control a thrust produced by each of said thrusters to achieve and selectively maintain the actual orientation of the RC flying hovercraft in response to the desired orientation communicated to the RC flying hovercraft by the RC controller and the actual orientation determined by the sensor system in the RC flying hovercraft without any additional communications ...

Подробнее

Номер записи: 26

07-01-2016 дата публикации

UNMANNED AERIAL VEHICLE LANDING INTERFACE

Номер: US20160001883A1

Автор: Miller Samuel Giles, Noorani Jonathan Shyaun, Sanz Christian, Sirang Behrooze

Принадлежит:

The present disclosure is directed toward systems and methods for autonomously landing an unmanned aerial vehicle (UAV). In particular, systems and methods described herein enable a UAV to land within and interface with a UAV ground station (UAVGS). In particular, one or more embodiments described herein include systems and methods that enable a UAV to conveniently interface with and land within a UAV ground station (UAVGS). For example, one or more embodiments include a UAV that includes a landing base and landing frame that interfaces with a landing housing of a UAVGS. 1. A system comprising:a ground station comprising a conically-shaped landing housing; and a main body;', 'a plurality of rotors coupled to the main body; and', 'a landing base coupled to the main body, the landing base having a shape complementary to the conically-shaped landing housing of the ground station such that when the UAV enters the conically-shaped landing housing of the ground station, contact between the landing base and the conically-shaped landing housing of the ground station causes the UAV to self-align within the conically-shaped landing housing of the ground station., 'an unmanned aerial vehicle (UAV) comprising2. The system as recited in claim 1 , wherein the landing base further comprises a landing pad and a plurality of charging contacts on the landing pad.3. The system as recited in claim 2 , wherein the ground station comprises one or more UAVGS charging contacts that couple to at least one of the plurality of charging contacts on the landing pad of the landing base when the UAV lands within the conically-shaped landing housing of the ground station.4. The system as recited in claim 2 , wherein the plurality of charging contacts on the UAV are positioned around a perimeter of the landing pad of the landing base based on corresponding positions of a plurality of UAVGS charging contacts within the conically-shaped landing housing of the ground station.5. The system as recited ...

Подробнее

Номер записи: 27

07-01-2016 дата публикации

Methods and Systems for Alerting and Aiding an Emergency Situation

Номер: US20160001884A1

Автор: Fleck Mathias Samuel

Принадлежит:

Embodiments described herein may relate to systems and methods for navigating to an emergency situation. An alert device may be controlled to issue alerts to draw the attention of bystanders to associated supplies for a situation. An illustrative method involves (a) receiving, by a computing system, a transmission indicating a situation at a designated location; (b) the computing system determining an approximate target area associated with the designated location; (c) the computing system making a determination that an alert device is located within the approximate target area; and (d) in response to the determination that the alert device is located within the approximate target area, the computing system executing instructions to activate at least one alert on the alert device indicating the situation and the designated location of the situation. 1. An unmanned aerial vehicle (UAV) comprising:a navigation module that provides a navigation process to generate flight-control signals for the UAV;one or more emergency supplies positioned on the UAV;an alert device associated with the one or more emergency supplies, wherein the alert device, when activated, emits at least one of an audio and a visual signal to draw attention to the emergency supplies; and receive a transmission indicating an emergency situation at a designated location;', 'determine an approximate target area associated with the designated location;', 'in response to the determination that the one or more emergency supplies are applicable to the emergency situation, navigate from a launch site to the approximate target area associated with the designated location;', 'in response to a determination that the UAV is located within the approximate target area, deliver the one or more emergency supplies to a ground level location within the approximate target area; and', 'in response to a determination that the one or more emergency supplies are positioned at the ground level location, activate at least ...

Подробнее

Номер записи: 28

02-01-2020 дата публикации

MONITORING SYSTEM, BASE STATION AND CONTROL METHOD OF A DRONE

Номер: US20200001735A1

Автор: CHEN Ying-Chieh, Cheng Hsu-Chih, Hsieh Chi-Tong, Yang I-Ta

Принадлежит: Coretronic Intelligent Robotics Corporation

This disclosure provides a monitoring system, a base station, and a control method of drones. The drone includes a battery that supplies electric power for the drone and that connects with a charging connector. The base station includes a charging device, and the charging device includes a power supply connector, a power supply, and a power controller. The power supply connector is used for connecting to the charging connector. The power supply provides electric power. The power controller is coupled to the power supply and the power supply connector. The power controller is used to determine the battery specification of the battery and charge the battery from the power supply according to the battery specification. Thereby, the charging efficiency can be improved and the charging abnormality can be avoided. 1. A monitoring system , comprising:a drone, comprising a battery, wherein the battery is used for supplying electric power for the drone, and the battery is adapted to connect with a charging connector; and a power supply connector, adapted to connect to the charging connector;', 'a power supply, adapted to provide electric power; and', 'a power controller, coupled to the power supply and the power supply connector, wherein the power controller is used to determine a battery specification of the battery and charge the battery from the power supply according to the battery specification., 'a charging device, comprising, 'a base station, comprising2. The monitoring system of claim 1 , wherein the power controller is used to determine a capacity of the battery and adjust a power characteristic of the power supply to charge the battery according to the capacity and the battery specification.3. The monitoring system of claim 1 , wherein the power controller is used to determine a polarity of the charging connector and switch a charging polarity of the power supply connector according to the polarity of the charging connector claim 1 , so that the polarity of the ...

Подробнее

Номер записи: 29

02-01-2020 дата публикации

STACKABLE BATTERY APPARATUSES AND METHODS OF USE

Номер: US20200001738A1

Автор: Sohmshetty Raj, VanNieulande Kevin

Принадлежит: FORD GLOBAL TECHNOLOGIES, LLC

Landing apparatuses for unmanned aerial vehicles are provided herein. An example battery assembly can include a housing having a top surface, and a bottom surface, wherein the bottom surface of the housing having a receiving interface that receives a first protruding adapter of an associated object. The top surface of the housing having a second protruding adapter that mates with the receiving interface of a second battery assembly, an energy storage unit disposed within the housing, a locking mechanism disposed within the housing, a biasing member that places the locking mechanism in a locked configuration, and a controller having a processor and memory for storing instructions, the processor being configured to execute the instructions to cause the locking mechanism to move into an unlocked configuration. 1. A battery assembly , comprising:a housing having a first surface and a second surface, wherein the second surface of the housing comprises a receiving interface that mates with a first protruding adapter of an associated object, further wherein the first surface of the housing comprises a second protruding adapter that is configured to mate with the receiving interface of a second battery assembly;an energy storage unit disposed within the housing;a locking mechanism disposed within the housing; anda controller having a processor and memory for storing instructions, the processor is configured to execute the instructions to cause the locking mechanism to disengage from the first protruding adapter so as to unlock the battery assembly from the associated object.2. The battery assembly according to claim 1 , wherein the first protruding adapter comprises a sidewall with a groove.3. The battery assembly according to claim 2 , wherein the locking mechanism of the first protruding adapter comprises a locking element that slides into the groove.4. The battery assembly according to claim 2 , wherein the locking mechanism comprises a plurality of locking elements ...

Подробнее

Номер записи: 30

05-01-2017 дата публикации

System for Embedded Removable Aperture

Номер: US20170001701A1

Автор: Osvog Andrew J.

Принадлежит:

A system includes a septum sleeve, an aperture fitting, and a removable aperture. The septum sleeve is substantially hollow and is configured to be positioned at least partially within a core of an assembly of an aircraft. The aperture fitting is configured to provide an interface to mechanically fasten the removable aperture. The removable aperture is configured to contain one or more electronic components and to be removably positioned at least partially within the septum sleeve. 1. A system , comprising:a substantially hollow septum sleeve that is configured to be positioned at least partially within a core of an aircraft assembly, the core being configured to be positioned at least partially within a skin of the aircraft assembly;a removable aperture that is configured to contain one or more electronic components and to be removably positioned at least partially within the septum sleeve;an aperture fitting configured to be coupled to the septum sleeve and the core, the aperture fitting comprising one or more threaded inserts for mechanically fastening the removable aperture;a spar configured to be coupled to the aperture fitting and the removable aperture; andone or more fasteners configured to removably fasten the removable aperture to the aperture fitting.2. The system of claim 1 , wherein:the spar comprises a first lip;the removable aperture comprises a second lip;the second lip is configured to be in contact with the first lip of the spar;the system further comprises a systems plate, the systems plate comprising a third lip;the third lip of the systems plate is configured to be in contact with the second lip of the removable aperture; andthe one or more fasteners are configured to removably fasten the systems plate and removable aperture to the aperture fitting.3. The system of claim 2 , wherein at least one of the one or more fasteners is configured to pass through an opening in the third lip of the systems plate claim 2 , through an opening in the second ...

Подробнее

Номер записи: 31

05-01-2017 дата публикации

TILE ASSEMBLY

Номер: US20170001715A1

Автор: MIRZA Nisar Ahmed, WARSOP Clyde

Принадлежит:

A tile assembly () which, in use, is fitted to a base structure to form at least part of a fluid washed surface. The tile assembly comprises a housing () with at least one plenum () being provided within the housing (). A wall () of the housing () is provided with a plurality of flow passages () which extend from the plenum side of the wall () to an outer surface () of the wall. Flow passage closures () are provided which are operable to open and close at least some of the flow passages (). 1. A tile assembly which , in use , is fitted to a base structure to form at least part of a fluid washed surface; the tile assembly comprising:a housing;at least one plenum being provided within an interior of the housing;a wall of the housing provided with a plurality of flow passages extending from an interior, plenum side of the wall to an outer surface of the wall, said wall forming at least part of the fluid washed surface; anda plurality of flow passage closures operable to open and close at least some of the flow passages.2. A tile assembly as claimed in wherein the housing is provided with a mechanical fixing for cooperation with a complementary fixing on the base structure to thereby lock the tile assembly to the base structure.3. A tile assembly as claimed in wherein the mechanical fixing is configured to be dis-engagable claim 2 , such that the tile assembly may be removed from the base structure.4. A tile assembly as claimed in claim 1 , wherein the tile assembly further comprises a dedicated fluid supply configured to deliver a fluid to the plenum.5. A tile assembly as claimed in claim 1 , further comprising a duct located in a wall of the housing and configured for delivery of a fluid to the plenum. Preliminary Amendment6. A tile assembly as claimed in claim 5 , wherein the duct comprises a fluid coupling configured for engagement with a complementary fluid coupling provided on the base structure.7. A tile assembly as claimed in claim 1 , wherein the housing is ...

Подробнее

Номер записи: 32

05-01-2017 дата публикации

Coupling Assembly for a Removable Propeller

Номер: US20170001721A1

Автор: Saika Noriaki, Tolbert William H., Yazdani Reza

Принадлежит:

Disclosed is an aerial vehicle. The aerial vehicle may include a removable battery. Various embodiments of removable battery assemblies include a pull-bar battery assembly, a latch battery assembly, and a lever battery assembly. The aerial vehicle may also include a propeller locking mechanism to which propellers may be removably coupled. The propeller locking mechanism may obviate the need for tools for coupling or decoupling propellers to the aerial vehicle. Vents in the arm of the aerial vehicle may provide an air pathway, providing convective cooling for the electronics aerial vehicle. 1. A propeller coupling assembly comprising: a shaft, the shaft coupled to a rotor;', 'a plate, the plate including an opening to receive the shaft;', 'a spring, the spring encircling the shaft, wherein the spring is coupled to the shaft at a first end and the spring is coupled to the plate at a second end; and', 'one or more pins, the pins extending from the shaft; and, 'a propeller locking mechanism, the propeller locking mechanism comprising an aperture formed by a first opening at a first end of the propeller hub, a second opening at a second end of the propeller hub, and an internal surface of the propeller hub connecting the first opening to the second opening;', 'one or more grooves, each groove formed on the internal surface of the propeller hub, wherein each groove includes a first opening at the first end of the propeller hub and a second opening at the second end of the propeller hub; and', 'one or more slots, each slot formed on the first end of the propeller hub., 'a propeller hub structured to couple to the propeller locking mechanism, the propeller hub having2. The propeller coupling assembly of claim 1 , wherein the plate of the propeller locking mechanism has a toothed surface.3. The propeller coupling assembly of further comprising a plurality of teeth extending from the second end of the propeller hub claim 2 , wherein the plurality of teeth reciprocally couple ...

Подробнее

Номер записи: 33

05-01-2017 дата публикации

SITE MANAGEMENT SYSTEM, IN-FLIGHT DETECTION METHOD, AND NON-TRANSITORY COMPUTER READABLE MEDIUM STORING PROGRAM OF SITE MANAGEMENT SYSTEM

Номер: US20170001723A1

Автор: Tanahashi Atsushi

Принадлежит: KABUSHIKI KAISHA TOPCON

A site management system includes an unmanned airplane being switchable between an airplane mode for high speed flight and a VTOL mode for low speed flight, a working vehicle working in a civil construction site, a shape detection sensor provided in the unmanned airplane to detect a shape of the civil construction site, and an external control apparatus that controls flight of the unmanned airplane, driving of the working vehicle, and driving of the shape detection sensor. The external control apparatus moves the unmanned airplane to an observation area by performing the high speed flight. Further, the external control apparatus detects a shape of the observation area by driving the shape detection sensor while performing the high speed flight or by driving the shape detection sensor while performing low speed flight by switching from the airplane mode to the VTOL mode. 1. A site management system comprising:an unmanned airplane being switchable between an airplane mode for high speed flight and a VTOL mode for low speed flight;a working vehicle working in a civil construction site;a shape detection sensor provided in the unmanned airplane, the shape detection sensor being driven to detect a shape of the civil construction site; andan external control apparatus that controls flight of the unmanned airplane, driving of the working vehicle, and driving of the shape detection sensor,wherein the external control apparatus moves the unmanned airplane to an observation area in the civil construction site by performing the high speed flight of the unmanned airplane in the airplane mode, andthe external control apparatus detects a shape of the observation area by driving the shape detection sensor while performing the high speed flight of the unmanned airplane in the airplane mode or by driving the shape detection sensor while performing low speed flight of the unmanned airplane by switching from the airplane mode to the VTOL mode.2. The site management system according to ...

Подробнее

Номер записи: 34

05-01-2017 дата публикации

UNMANNED SUPPLY DELIVERY AIRCRAFT

Номер: US20170001724A1

Автор: YATES William M.

Принадлежит:

A heavy payload, autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV can be equipped with a movable wing system. The UAV can include a removable storage box. The UAV can be equipped with a drogue parachute for deploying the wings upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously. The UAV can include canard wings. The canard wings and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expandable UAV. The UAV's wings can be configured to automatically separate from the UAV during the landing sequence. 1. An unmanned delivery aircraft comprising:a fuselage cargo container;the fuselage cargo container comprising a lid and a bottom portion;a first pivoting wing system connected to the lid;a second pivoting wing system connected to the lid;a guidance control system; andone or more flight controls operable by the guidance control system;wherein each of the first and second pivoting wing systems can pivot from a stowed position to a deployed position.2. The unmanned delivery aircraft of claim 1 , wherein the first pivoting wing system comprises a single pivoting wing.3. The unmanned delivery aircraft of claim 1 , wherein the first pivoting wing system comprises two pivoting wings.4. The unmanned delivery aircraft of claim 1 , wherein the second pivoting wing system comprises two pivoting wings.5. The unmanned delivery aircraft of claim 1 , wherein the first and second pivoting wing systems have the same design.6. The unmanned delivery aircraft of claim 1 , wherein the first pivoting wing system comprise main wings and the second pivoting wing system comprise canard wings.7. The unmanned delivery aircraft of claim 1 , wherein the lid is detachably connected to the bottom portion.8. The unmanned delivery aircraft of claim 8 , further comprising at least one latch securing the lid to the bottom ...

Подробнее

Номер записи: 35

07-01-2021 дата публикации

CARGO LOADING /UNLOADING DEVICE FOR DRONES

Номер: US20210002107A1

Автор: Zhang Aaron

Принадлежит:

A drone loading/unloading device includes an electric reel selectively movable for releasing/winding a cable adapted to be wound around the electric reel. A driver is operably connected to the electric reel to selectively drive the electric reel to reciprocally move from a locked position and an unlocked position and a buffer is mounted between the driver and the electric reel such that buffering effect is provided to the electric reel when moved from an unlocked position to a locked position. 1. A drone loading/unloading device comprising:a reel selectively movable for releasing/winding a cable adapted to be wound around the reel;a driver operably connected to the reel to selectively drive the reel to reciprocally move from a locked position and an unlocked position; anda buffer mounted between the driver and the reel to provide buffering effect to the reel when moved from an unlocked position to a locked position.2. The device as claimed in further comprising a first rotation axle extending through the electric reel claim 1 , a first driver operably connected to the first rotation axle to selectively drive the first rotation axle as well as the reel to rotate and a first locking element mounted between a free end of the first rotation axle and a side of the driver to selectively prevent the reel from rotation.3. The device as claimed in claim 2 , wherein a sleeve is provided to surround the first locking element and has a guiding passage defined therein to guide engagement between two halves of teeth of the first locking element.4. The device as claimed in further comprising a second rotation axle operably connected to the driver and the first rotation axle via the buffer.5. The device as claimed in further comprising a stability bracket mounted on the first rotation axle and the second rotation axle to provide stability to the rotation of both the first rotation axle and the second rotation axle.6. The device as claimed in claim 5 , wherein a second locking ...

Подробнее

Номер записи: 36

06-01-2022 дата публикации

Information processing apparatus, information processing method, and non-transitory storage medium

Номер: US20220004736A1

Автор: Ai Miyata, Kenichi Yamada, Ryuichi Kamaga, Satoshi Komamine, Shintaro MATSUTANI, Yu Nagata, Yurika Tanaka

Принадлежит: Toyota Motor Corp

A controller is provided that is configured to perform: obtaining information about a condition for an image that is provided to a user, and that corresponds to a preference of the user; specifying at least one predetermined position at which an image satisfying the condition can be taken; and generating a command for a moving object to move to the predetermined position and to take an image, and transmitting the command to the moving object.

Подробнее

Номер записи: 37

04-01-2018 дата публикации

Omnidirectional frangible joint

Номер: US20180001990A1

Автор: Bradley Yeomans, Chad Stuart Kossar, Matthew Grubb

Принадлежит: Insitu Inc

A reusable frangible joint includes a first part having a hemispherical convex surface, and a second part defined by a reversely identical mating hemispherical concave surface. The convex and concave surfaces of the joint are secured and held together in compression until a predetermined applied load causes the joint to fail. The joint includes at least one replaceable fastener that rigidly secures and holds the respective concave and convex surfaces together. The fastener, designed to be the only part of the joint configured to fail, is sheared apart under the predetermined load, which results in separation of the concave and convex parts from one another irrespective of from which direction or to which part the impact load is applied. The failed fastener can then be replaced, wherein the frangible joint becomes immediately reusable, as having incurred no other damage by the impact load.

Подробнее

Номер записи: 38

02-01-2020 дата публикации

CHORD-WISE VARIABLE VORTEX GENERATOR

Номер: US20200001973A1

Автор: Bushmire Troy Thomas

Принадлежит:

One embodiment is an apparatus including an airfoil-shaped body; and a chordwise variable vortex generation system associated with the airfoil-shaped body, the chordwise variable vortex generation system controlling a deployment of at least one vortex generator on a surface of the airfoil-shaped body, wherein the deployment of the at least one vortex generator is dependent on a current angle of attack of the airfoil-shaped body. In some embodiments, the chordwise variable vortex generation system includes an actuator for controlling a location of the deployment of the at least one vortex generator responsive to a control signal indicative of the current angle of attack of the airfoil-shaped body. In certain embodiments, the surface of the airfoil-shaped body is a top surface of the airfoil-shaped body. In some embodiments, the airfoil-shaped body is an aircraft wing. 1. An apparatus comprising:an airfoil-shaped body; anda chordwise variable vortex generation system associated with the airfoil-shaped body, the chordwise variable vortex generation system controlling a deployment of at least one vortex generator on a surface of the airfoil-shaped body, wherein the deployment of the at least one vortex generator is dependent on a current angle of attack of the airfoil-shaped body.2. The apparatus of claim 1 , wherein the chordwise variable vortex generation system comprises an actuator for controlling a location of the deployment of the at least one vortex generator responsive to a control signal indicative of the current angle of attack of the airfoil-shaped body.3. The apparatus of claim 1 , wherein the surface of the airfoil-shaped body comprises a top surface of the airfoil-shaped body.4. The apparatus of claim 1 , wherein the airfoil-shaped body comprises an aircraft wing.5. The apparatus of claim 1 , wherein the chordwise variable vortex generation system comprises a track disposed along the surface of the airfoil-shaped body between a leading edge of the airfoil- ...

Подробнее

Номер записи: 39

02-01-2020 дата публикации

AIRCRAFT GENERATING LARGER THRUST AND LIFT BY FLUID CONTINUITY

Номер: US20200001980A1

Автор: ZHU Xiaoyi

Принадлежит:

The invention discloses an aircraft generating a larger thrust and lift by fluid continuity. First open channels used to extend fluid paths are formed in front parts and/or middle parts of windward sides of wings of the aircraft and extend from sides, close to the fuselage, of the wings to sides, away from the fuselage, of the wings, and the first open channels are concave channels or convex channels, so that a pressure difference in a direction identical with a moving direction is generated from back to front due to different flow speeds of fluid flowing over the windward sides of the wings in a lengthwise direction and a widthwise direction to reduce fluid resistance, and a larger pressure difference and lift are generated due to different flow speeds on the windward sides and leeward sides of the wings. 1. An aircraft , comprising a fuselage and wings , wherein first open channels used to extend fluid paths are formed in windward sides of the wings and extend from roots of sides , close to the fuselage , of the wings to tails of sides , away from the fuselage , of the wings , and the first open channels are concave channels or convex channels , so that a larger lift is generated due to different flow speeds of fluid flowing over the windward sides of the wings in a lengthwise direction and flowing over leeward sides of the wings in a widthwise direction.2. The aircraft according to claim 1 , wherein the first open channels are formed in front parts of the windward sides of the wings claim 1 , or the first open channels are formed in the front parts and middle parts of the windward sides of the wings claim 1 , so that a pressure difference-based thrust in a direction identical with a moving direction is generated from back to front due to different flow speeds of the fluid flowing through the front parts or middle parts of the wings and flowing through rear parts of the windward sides of the wings.3. The aircraft according to claim 1 , wherein the first open ...

Подробнее

Номер записи: 40

02-01-2020 дата публикации

JET FLOW CONTROL MECHANISM AND METHOD OF USE

Номер: US20200001981A1

Автор: Alhussan Khaled Abdullah

Принадлежит:

A transonic aircraft includes a frame body extending from a fuselage to a rear tail wing section; an engine placed between the fuselage and rear tail wing section, the engine is secured to the frame body; a wing section includes a wing body with an upper surface and a lower surface that extend from a leading edge to a trailing edge, the wing body is oriented at an angle relative to an elongated length of the frame body; and a flow separation control device secured to the wing section. The flow separation control device includes a plurality of openings on the upper surface of the wing body. 1. An aircraft , comprising:a frame body extending from a fuselage to a rear tail wing section;an engine placed between the fuselage and rear tail wing section, the engine is secured to the frame body;a wing section; anda flow separation control device secured to the wing section, the flow separation control device;wherein a portion of the airstream passing over the upper surface of the wing body is affected by the plurality of openings; andwherein the plurality of openings reduces a flow separation in the portion of the airstream passing over the upper surface of the body.2. The aircraft of claim 1 , the wing section comprising:a wing body with an upper surface and a lower surface that extend from a leading edge to a trailing edge, the wing body is oriented at an angle relative to an elongated length of the frame body.3. The aircraft of claim 2 , the flow separation device claim 2 , having:a plurality of openings on the upper surface of the wing body;4. The aircraft of claim 3 , wherein the flow separation device extends the longitudinal length of the wing body.5. The aircraft of claim 3 , wherein the plurality of openings extend from a ⅓ chord length to a ⅔ chord length of the wing section.6. The aircraft of claim 1 , wherein the plurality of openings extend from a ⅓ chord length to a ⅔ chord length of the wing section.7. The aircraft of claim 1 , wherein the plurality of ...

Подробнее

Номер записи: 41

02-01-2020 дата публикации

AIRCRAFT WITH UMBRELLA STRUCTURE

Номер: US20200001989A1

Автор: KAN Luc

Принадлежит:

An aircraft with an umbrella structure is provided, which includes a main body, a base and a plurality of umbrella arms. The base is disposed on the main body. One end of each umbrella arm is installed on the base, and each umbrella arm includes an arm body, where the both sides of the arm body are provided with a first fixation element and a second fixation element respectively, and an umbrella cloth connected to the second fixation element is disposed inside the arm body. The umbrella arms are able to spread out to form a radiating arrangement, and the second fixation element of each umbrella arm is fixed on the first fixation element of the adjacent umbrella arm at one side thereof to pull out the umbrella cloth disposed therein, such that the umbrella arms can form the umbrella structure. 1. An aircraft with an umbrella structure , comprising:a main body;a base, disposed on the main body; anda plurality of umbrella arms, one end of each umbrella arm being installed on the base, and each umbrella arm comprising an arm body, a first fixation element, a second fixation element and an umbrella cloth, wherein the first fixation element and the second fixation element are disposed on both sides of the arm body respectively, and the umbrella cloth is connected to the second fixation element and disposed inside the arm body;wherein the umbrella arms are able to spread out to form a radiating arrangement, and the second fixation element of each umbrella arm is fixed on the first fixation element of the adjacent umbrella arm at one side thereof to pull out the umbrella cloth disposed therein, such that the umbrella arms form the umbrella structure.2. The aircraft with the umbrella structure of claim 1 , wherein one end of each umbrella arm is detachably installed on the base.3. The aircraft with the umbrella structure of claim 1 , wherein the first fixation elements and the second fixation elements are magnets.4. The aircraft with the umbrella structure of claim 1 , ...

Подробнее

Номер записи: 42

02-01-2020 дата публикации

AUTOMATICALLY AND RELEASABLY COUPLING UAV PROPELLERS TO PROPULSION MOTORS, AND ASSOCIATED SYSTEMS AND METHODS

Номер: US20200001990A1

Автор: Jiang Bin, Ren Guannan

Принадлежит:

A propulsion system for an unmanned aerial vehicle (UAV) includes a propulsion motor configured to drive a propeller and an apparatus configured to releasably couple the propeller to the propulsion motor. The apparatus includes an engagement member, at least a portion of which is positioned to move relative to the propulsion motor and/or the propeller along a rotational axis of the propulsion motor between an engaged position and a disengaged position different from the engaged position. When in the disengaged position, the engagement member couples the propeller to the propulsion motor. 1. A propulsion system for an unmanned aerial vehicle (UAV) , the propulsion system comprising:a propulsion motor configured to drive a propeller; andan apparatus configured to releasably couple the propeller to the propulsion motor, the apparatus comprising an engagement member, at least a portion of the engagement member being positioned to move relative to the propulsion motor and/or the propeller along a rotational axis of the propulsion motor between an engaged position in which the engagement member couples the propeller to the propulsion motor and a disengaged position different from the engaged position.2. The propulsion system of claim 1 , further comprising a driving mechanism operatively connected to the engagement member to cause the portion of the engagement member to move between the engaged position and the disengaged position.3. The propulsion system of claim 1 ,wherein the engagement member includes a first hook element pivotably connected to the propulsion motor;the propulsion system further comprising a second hook element pivotably connected to the propulsion motor.4. The propulsion system of claim 3 , wherein the first hook element is positioned to be:received in a recess in a hub portion of the propeller when the engagement member is in the engaged position, anddisengaged from the recess when the engagement member is in the disengaged position.5. The propulsion ...

Подробнее

Номер записи: 43

02-01-2020 дата публикации

AIRCRAFT AND METHODS OF PERFORMING TETHERED AND UNTETHERED FLIGHTS USING AIRCRAFT

Номер: US20200001993A1

Автор: Kirkbride David W.

Принадлежит: The Boeing Company

Disclosed are aircraft configured to perform tethered and untethered flights as well as methods of operating such aircraft. During a tethered flight, the aircraft is connected to a power line using its connecting module. While tethered, the aircraft can receive electrical energy from the power line and use this energy for propulsion and/or storage. The aircraft comprises a propulsion module for providing vertical and horizontal thrusts. In some examples, the aircraft comprises a transport module. The transport module may be removably attached to the propulsion module and be replaceable with another transportation module. During an untethered flight, the electrical energy is supplied to the propulsion module from a battery and/or a generator on board of the aircraft. The untethered flight capability can be used for landing and takeoff, flying away from power lines or when the power line is not operational, and other like examples. 1. An aircraft configured to perform a tethered flight and an untethered flight , the aircraft comprising:a propulsion module, comprising a vertical thruster configured to generate lift;a connecting module, coupled to the propulsion module and configured to form a power connection with a power line during the tethered flight to transmit electrical energy from the power line to the propulsion module; anda transport module, coupled to the propulsion module and configured to transport one or more of cargo and passengers.2. The aircraft of claim 1 , wherein the transport module is detachably coupled to the propulsion module.3. The aircraft of claim 1 , wherein the transport module is selected from the group consisting of a passenger transport module claim 1 , a container transport module claim 1 , and an ore transport module.4. The aircraft of claim 1 , further comprising a battery claim 1 , electrically coupled to the connecting module and the vertical thruster claim 1 , wherein the battery is configured to charge during the tethered flight ...

Подробнее

Номер записи: 44

02-01-2020 дата публикации

TELEPRESENCE DRONES AND TELEPRESENCE DRONE SYSTEMS

Номер: US20200001994A1

Автор: PROKHOROV Danil V.

Принадлежит: Toyota Motor Engineering & Manufacturing North America, Inc.

A telepresence drone that is configured to navigate through an environment includes a frame, a propulsion system comprising propellers and motors coupled to the frame, an electronic control unit in communication with the propulsion system, and a hull positioned outside of the frame and the propulsion system. The hull includes a plurality of openings through which the propulsion system acts on air to navigate through the environment. 1. A telepresence drone configured to navigate through an environment , the telepresence drone comprising:a frame;a propulsion system comprising propellers and motors coupled to the frame;an electronic control unit in communication with the propulsion system; anda hull positioned outside of the frame and the propulsion system, the hull comprising a plurality of openings through which the propulsion system acts on air to navigate through the environment.2. The telepresence drone of claim 1 , wherein the hull comprises ducted portions that direct air from the environment toward the propeller.3. The telepresence drone of claim 2 , wherein the ducted portions extend from a first side of the propeller to an outer surface of the hull and from a second side of the propeller to an outer surface of the hull.4. The telepresence drone of claim 1 , wherein the hull comprises a spherical shape.5. The telepresence drone of claim 1 , further comprising:a wireless data interface in communication with the electronic control unit; anda route planner detection instruction set stored in a memory, wherein when the route planner instruction set is executed by the electronic control unit, the electronic control unit evaluates location and orientation of a user and instructs the telepresence drone to navigate to a position in front of the user.6. The telepresence drone of claim 1 , wherein the telepresence drone further comprises a route planner instruction set that claim 1 , when executed by the electronic control unit:evaluates the position and orientation of ...

Подробнее

Номер записи: 45

02-01-2020 дата публикации

ROTORCRAFT

Номер: US20200001995A1

Автор: CHEN Ying-Chieh, Cheng Hsu-Chih, Hsieh Chi-Tong, Yang I-Ta

Принадлежит:

A rotorcraft includes a body and a plurality of rotary-wing parts. The body has a front-end portion, a rear-end portion, two side portions, and a reference plane passing through the front-end portion, the rear-end portion, and the two side portions. The plurality of rotary-wing parts are disposed to the body. Each of the rotary-wing parts includes at least one blade and a shaft coupled to the at least one blade. The at least one blade is rotated around an axis of the shaft. An angle between the axis of the shaft and a normal line of the reference plane is between 5 and 30 degrees. The rotorcraft can provide additional lift force, to help reduce the weight of the rotorcraft. 1. A rotorcraft , comprising a body and a plurality of rotary-wing parts , wherein:the body has a front-end portion, a rear-end portion, two side portions, and a reference plane passing through the front-end portion, the rear-end portion, and the two side portions; andthe plurality of rotary-wing parts are disposed to the body, wherein each of the rotary-wing part comprises at least one blade and a shaft coupled to the at least one blade, and the at least one blade is rotated around an axis of the shaft; andwherein an angle between the axis of the shaft and a normal line of the reference plane is between 5 and 30 degrees.2. The rotorcraft according to claim 1 , wherein the plurality of rotary-wing parts surround the body.3. The rotorcraft according to claim 1 , wherein the plurality of the at least one blade of the plurality of rotary-wing parts are located on a coplanar plane claim 1 , and the coplanar plane is not parallel to the reference plane.4. The rotorcraft according to claim 3 , wherein the body further has a top surface located between the front-end portion and the rear-end portion claim 3 , and the plurality of the at least one blade on the coplanar plane are all adjacent to the top surface.5. The rotorcraft according to claim 3 , wherein the plurality of the at least one blade on the ...

Подробнее

Номер записи: 46

02-01-2020 дата публикации

UAV CONFIGURATIONS AND BATTERY AUGMENTATION FOR UAV INTERNAL COMBUSTION ENGINES, AND ASSOCIATED SYSTEMS AND METHODS

Номер: US20200001996A1

Автор: McAdoo Gregory Leonard

Принадлежит:

UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed. 128-. (canceled)29. An unmanned aerial vehicle (UAV) , comprising:a fuselage;a first wing coupled to and pivotable relative to the fuselage;a second wing coupled to and pivotable relative to the fuselage; anda plurality of lift rotors carried by the fuselage.30. The UAV of claim 29 , further comprising:a first motor operatively coupled to the first wing to rotate the first wing relative to the fuselage; anda second motor operatively coupled to the second wing to rotate the second wing relative to the fuselage.31. The UAV of claim 29 , further comprising a tractor rotor carried by the fuselage toward a forward end of the fuselage.32. The UAV of claim 29 , further comprising a pusher rotor carried by the fuselage toward an aft end of the fuselage.33. The UAV of wherein the lift rotors have rotation axes that are fixed relative to the fuselage.34. The UAV of wherein the lift rotors have rotation axes that are movable relative to the fuselage.35. The system of wherein two of the lift rotors are carried by a first pod and two of the lift rotors are carried by a second pod claim 34 , and wherein each of the first and second pods is rotatable ...

Подробнее

Номер записи: 47

02-01-2020 дата публикации

BATTERY USED FOR UNMANNED AERIAL VEHICLE AND UNMANNED AERIAL VEHICLE

Номер: US20200001997A1

Автор: QIU Longxue, WU Xingwen

Принадлежит:

The present invention discloses an unmanned aerial vehicle including a main body, a plurality of arms, a propulsion assembly and a battery assembly, where each arm is coupled to the main body and the propulsion assembly is disposed on the each arm. The battery assembly is accommodated in a battery compartment of the main body. The battery assembly includes a shell, a battery body substantially disposed in the shell, a clamp button, and a restorable elastic piece. An end of the clamp button is mounted or connects to the shell, and the other end of the clamp button is detachably coupled to the main body. An end of the restorable elastic piece is disposed on the shell or connect to the shell, and the other end of the restorable elastic piece contacts the clamp button. 1. A multi-rotor unmanned aerial vehicle , comprising:a main body comprising a battery compartment;a plurality of arms, wherein each arm is coupled to the main body and extends laterally from the main body;a propulsion assembly disposed on the each arm, wherein the propulsion assembly comprises a propeller;a battery assembly comprising a shell and a battery body disposed in the shell, wherein the battery assembly is configured to be accommodated in the battery compartment;a clamp button configured to detachably attach the battery assembly to the main body; anda restorable elastic piece connecting to the clamp button or contacting the clamp button, wherein the restorable elastic piece is configured to reset the clamp button to a position, the restorable elastic piece and the clamp button being two different separate components.2. The multi-rotor unmanned aerial vehicle according to claim 1 , wherein a first end of the restorable elastic piece is disposed on the shell or connects directly or indirectly to the shell.3. The multi-rotor unmanned aerial vehicle according to claim 2 , wherein the first end of the restorable elastic piece is stuck in the shell or fixed with the shell.4. The multi-rotor unmanned ...

Подробнее

Номер записи: 48

02-01-2020 дата публикации

MOVABLE PLATFORM CONTROL METHOD AND MOVABLE PLATFORM

Номер: US20200001998A1

Автор: Gong Ming, LIN Xingsen, RAO Xiongbin, WANG Naibo

Принадлежит:

A method is provided for controlling a movable platform. The method includes determining whether the movable platform is capable of broadcasting information indicating a relevant parameter of the movable platform. The method also includes restricting a movement of the movable platform based on a determination that the movable platform is not capable of broadcasting the information. 1. A method for controlling a movable platform , comprising:determining whether the movable platform is capable of broadcasting information indicating a relevant parameter of the movable platform; andrestricting a movement of the movable platform based on a determination that the movable platform is not capable of broadcasting the information.2. The method of claim 1 , wherein the relevant parameter comprises at least location information of the movable platform.3. The method of claim 2 , wherein determining whether the movable platform is capable of broadcasting the information indicating the relevant parameter of the movable platform comprises:determining whether a positioning device is capable of operating normally; anddetermining that the movable platform is not capable of broadcasting the information based on a determination that the positioning device is not capable of operating normally.4. The method of claim 2 , wherein determining whether the movable platform is capable of broadcasting the information indicating the relevant parameter of the movable platform comprises:determining whether the location information output by a positioning device of the movable platform is effective; anddetermining that the movable platform is not capable of broadcasting the information based on a determination that the location information is ineffective.5. The method of claim 4 , wherein determining whether the location information output by the positioning device of the movable platform is effective comprises:determining a signal-to-noise ratio of the location information; anddetermining that the ...

Подробнее

Номер записи: 49

02-01-2020 дата публикации

Air-Transportable Device For Projecting Pressurised Liquid

Номер: US20200001999A1

Автор: Antoni Abellan SALMERON

Принадлежит: Individual

The invention relates to an air-transportable device (100) for projecting pressurized liquid over a surface, comprising a rotating washing head and an inspection system (11) with LED bulbs and cameras. The air-transportable device (100) is secured to an aircraft (200, 500) by the upper surface thereof or by means of straps and can be configured for different uses such as cleaning wind and photovoltaic facilities, extinguishing fires or cleaning insulators.

Подробнее

Номер записи: 50

02-01-2020 дата публикации

INDOOR AND OUTDOOR AERIAL VEHICLES FOR PAINTING AND RELATED APPLICATIONS

Номер: US20200002000A1

Автор: Dahlstrom Robert L.

Принадлежит:

An aerial operations system for performing various tasks such as painting is provided. The modular aerial operations system includes an aerial vehicle capable of vertically taking off and landing, hovering and precisely maneuvering near walls and other structures. The aerial vehicle may be a rotorcraft such as a multicopter. In an aspect, as aerial vehicle paints one or more designated surfaces using detachable arms and equipment. The system may paint the designated surface in one of several available techniques using paint provided in a container such as an attached reservoir, a base station, a paint can, or the like. The aerial operations system provided may also be configured to perform a variety of other tasks. 129.-. (canceled)30. An aerial operations system , comprising:an unmanned aerial vehicle (UAV);a plurality of accessories configured to be attached to the UAV, a respective one accessory configured to spray a sprayable material;at least one sensor on the UAV to sense a surface of structure and obstacles in a path of the UAV; anda command and control system, in response to inputs from the at least one sensor, to pilot the UAV to an attitude, altitude and a position along the path, relative to the sensed surface and the obstacles, for performing a current task on the surface with one or more attached accessories, to determine a position for the respective one attached accessory relative to the surface from a calculated distance being calculated based on environmental conditions and at least one of spray material viscosity and desired thickness of the sprayable material and wherein the command and control system to position and at least one of extend, adjust orientation of and retract the respective one attached accessory based on the determined position.31. The aerial operations system of claim 30 , wherein the UAV configured to have attached thereto two accessories simultaneously.32. The aerial operations system of claim 31 , wherein a respective second ...

Подробнее

Номер записи: 51

03-01-2019 дата публикации

PROCESS FOR SIGNALING AN ACCIDENT BY MEANS OF A SIGNALING DRONE

Номер: US20190001872A1

Автор: FORMENTIN Jonathan, MUBAMU MOMBO Dany Jonas, ZENG EYINDANGA Landry Stéphane

Принадлежит:

A process for signaling an accident by at least one drone, the process involving acquiring a location of the place of the accident; calculating the coordinates of at least one signaling position; signaling the accident in accordance with a combination of the location of the place of the accident and the calculated coordinates of the at least one position. 1. A process for signaling an accident by means of at least one drone , said process comprising:acquiring a location of the place of the accident,calculating coordinates of at least one signaling position, andsignaling the accident in accordance with a combination of the location of the place of the accident and the calculated coordinates of said at least one position.2. The process for signaling according to claim 1 , wherein the signaling of the accident is carried out by the deployment of at least one marking element.3. The process for signaling according to claim 1 , wherein the signaling of the accident is carried out by a light and/or sound signal emitted by said at least one drone.4. The process for signaling according to claim 1 , wherein the acquisition of the location of the place of the accident comprises a reception of location data via a terminal which transmits said location data to said drone.5. The process for signaling according to claim 1 , wherein the acquisition of the location of the place of the accident comprises a location of the emplacement in which an operator has positioned the drone claim 1 , said emplacement being assimilated with the place of the accident via the activation of an actuator of said drone.6. The process for signaling according to claim 1 , wherein the acquisition of the location of the place of the accident comprises recognition of the place of the accident by image analysis means of the drone.7. The process for signaling according to claim 1 , further comprising a road mapping of the geographic area in which the accident has occurred.8. The process for signaling ...

Подробнее

Номер записи: 52

02-01-2020 дата публикации

Energy Harvesting Micro Air Vehicle

Номер: US20200002015A1

Автор: Cousins Clifford G., Hiller Nathan D.

Принадлежит:

A method, apparatus, and system for charging an electrical storage system in a vehicle. The vehicle comprises a support frame, a propulsion, an electric storage system, an extendable structure, and a power management unit. The propulsion system, the electrical storage system, and the power management unit are physically coupled to the support frame. The electrical storage system supplies the electrical energy to the propulsion system. The group of thermoelectric modules physically is physically coupled to the extendable structure and generates a current in response to a heat being transferred through the group of modules. The power management unit is electrically coupled to the electrical storage system and the group of thermal thermoelectric modules and controls storing the electrical energy in the electrical storage system using the current from the group of thermoelectric modules and supplying the electrical energy to the propulsion system. 1. A vehicle comprising:a support frame;a propulsion system physically coupled to the support frame, wherein the propulsion system operates using an electrical energy;an electrical storage system physically coupled to the support frame, wherein the electrical storage system supplies the electrical energy to the propulsion system,an extendable structure;a group of thermoelectric modules physically coupled to the extendable structure, wherein the group of thermoelectric modules generates an electrical current in response to a heat being transferred through the group of thermoelectric modules in which a transfer of the heat is caused by a temperature differential; anda power management unit physically coupled to the support frame, wherein the power management unit is electrically coupled to the electrical storage system and the group of thermoelectric modules, and controls storing the electrical energy in the electrical storage system using the electrical current from the group of thermoelectric modules and supplying the ...

Подробнее

Номер записи: 53

04-01-2018 дата публикации

VERTICAL TAKE-OFF AND LANDING (VTOL) WINGED AIR VEHICLE WITH COMPLEMENTARY ANGLED ROTORS

Номер: US20180002003A1

Автор: Lindsey Quentin, Won Henry Thome

Принадлежит:

Systems, devices, and methods for an aircraft having a fuselage (); a wing () extending from both sides of the fuselage; a first pair of motors () disposed at a first end of the wing; and a second pair of motors () disposed at a second end of the wing; where each motor is angled () to provide a component of thrust by a propeller () attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers. 1. An aircraft comprising:a fuselage;a wing extending from both sides of the fuselage, the wing having a first side and a second side;a first pair of motors disposed at a first end of the wing distal from the fuselage, wherein one motor of the first pair of motors is on the first side of the wing, and wherein the other motor of the first pair of motors is on the second side of the wing;a second pair of motors disposed at a second end of the wing distal from the fuselage, wherein the second end of the wing is opposite the first end of the wing, wherein one motor of the second pair of motors is on the first side of the wing, and wherein the other motor of the second pair of motors is on the second side of the wing;wherein each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to a resulting torque created by rotating the propellers.2. The aircraft of claim 1 , wherein each motor is angled between 5 and 35 degrees from a longitudinal axis of the aircraft.3. The aircraft of claim 1 , wherein each propeller is disposed distal from the wing and the fuselage claim 1 , and wherein each propeller is in a clean air region away from turbulent air coming off the wing and the fuselage during horizontal flight.4. The aircraft of claim 1 , wherein each motor is angled within a first plane generally perpendicular to a planform of the wing.5. The aircraft of claim 1 , wherein each motor is angled within a ...

Подробнее

Номер записи: 54

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 ...

Подробнее

Номер записи: 55

04-01-2018 дата публикации

THRUST-GENERATING ROTOR ASSEMBLY

Номер: US20180002008A1

Автор: Hagh Sandberg Päl, Johnsrud Ivar, Marton Trygve Frederik, Muren Petter

Принадлежит:

The present invention discloses a rotor control system where rapid changes in rotor torque are transferred into moment forces acting about the blade pitch axis of a rotor blade in a thrust-generating rotor, to ultimately control the movements of a rotary wing aircraft. The moment forces acting on the rotor blade are transferred through a carefully adjusted damping member in order to allow rapid changes in rotor torque to create cyclic changes in blade pitch angle, while slow or permanent changes are cancelled out and affects the rotational speed and the thrust generated by the rotor, without permanently affecting the blade pitch angle of individual rotor blades. 1. A thrust-generating rotor assembly comprising:a rotor torque assembly rotationally connected to a rotor blade assembly comprising rotor blades configured to tilt about a rotor blade axis according to a blade pitch angle; and at least one spring member connected between the rotor torque assembly and the rotor blade assembly about its axis of rotation and configured to transfer changes in rotor torque into proportional changes in rotational offset between the rotor torque assembly and the rotor blade assembly without introducing tilting moments about the rotor blade axis, and', 'a rotating damping member comprising a first concentric part and a second concentric part adapted to fit together with a damper between the two parts and interact with a pitch arm to transfer the changes in rotational offset into substantial tilting moments about the rotor blade axis at rapid changes in rotor torque and to cancel or limit the tilting moments at slow or permanent changes in rotor torque, wherein the tilting moments act on at least one rotor blade to control the blade pitch angle., 'a cyclic pitch control system, comprising2. A thrust-generating rotor assembly according to claim 1 , wherein the damping member is configured to enable the tilting moments to predictably follow the rate of the changes of rotational offset ...

Подробнее

Номер записи: 56

04-01-2018 дата публикации

Aircraft Propulsion Assembly

Номер: US20180002009A1

Автор: John Richard McCULLOUGH, Paul K. Oldroyd

Принадлежит: BELL HELICOPTER TEXTRON INC

In some embodiments, a propulsion assembly for an aircraft includes a nacelle, at least one self-contained fuel tank disposed within the nacelle operable to contain a liquid fuel, an engine disposed within the nacelle operable to run on the liquid fuel, a drive system mechanically coupled to the engine and operable to rotate responsive to rotation of the engine, a rotor hub mechanically coupled to the drive system operable to rotate responsive to rotation of the drive system and a proprotor mechanically coupled to the rotor hub and operable to rotate therewith.

Подробнее

Номер записи: 57

04-01-2018 дата публикации

UNMANNED AERIAL VEHICLE INSPECTION SYSTEM

Номер: US20180002010A1

Автор: Bauer Mark Patrick, Bethke Brett Michael, Michini Bernard J.

Принадлежит:

Methods, systems, and apparatus, including computer programs encoded on computer storage media, for an unmanned aerial system inspection system. One of the methods is performed by a UAV and includes obtaining, from a user device, flight operation information describing an inspection of a vertical structure to be performed, the flight operation information including locations of one or more safe locations for vertical inspection. A location of the UAV is determined to correspond to a first safe location for vertical inspection. A first inspection of the structure is performed is performed at the first safe location, the first inspection including activating cameras. A second safe location is traveled to, and a second inspection of the structure is performed. Information associated with the inspection is provided to the user device. 1. A flight planning system comprising one or more computers and one or more computer storage media storing instructions that when executed by the one or more computers cause the one or more computers to perform operations comprising:receiving, via a user interface, a selection of a type of a vertical structure to be inspected;in response to receiving the selection of the type, presenting via the user interface, a representation corresponding to the type of selected vertical structure;receiving input via the user interface, the input indicating one or more portions of the vertical structure to be inspected by an unmanned aerial vehicle (UAV);presenting, via the user interface, an indication of the one or more portions of the vertical structure to be inspected; anddetermining a flight plan to perform an inspection of a real-world vertical structure that is associated with the representation of the vertical structure, the flight plan determined according to the indicated portions of the vertical structure to be inspected, wherein the flight plan causes the UAV to navigate and obtain sensor information of the real-world vertical structure.2. ...

Подробнее

Номер записи: 58

04-01-2018 дата публикации

Vision Based Calibration System For Unmanned Aerial Vehicles

Номер: US20180002017A1

Автор: Abeles Peter, Wyrobek Keenan

Принадлежит:

An unmanned aircraft system includes a testing and calibration system that enables automated testing of movable parts of an unmanned aircraft. The testing and calibration system uses a camera-based technique to determine the position and angle of movable parts, in order to establish whether or not those parts are moving in a manner consistent with correct function. 1. An automated calibration system , comprising:a camera configured to be positioned relative to a vehicle such that a base fiducial and a movable fiducial on the vehicle are visible within a field of view of the camera; and receive an image of the base fiducial and the movable fiducial from the camera, the image comprising image data;', 'determine a relative orientation between the base fiducial and the movable fiducial based on the image data;', 'determine a real position of a movable part of the vehicle based on the relative orientation between the base fiducial and the movable fiducial, and a position of a base surface of the vehicle;', 'compare the real position of the movable part to a reported position for the movable part; and', 'generate a notification if a difference between the real position and the reported position is greater than a threshold amount., 'and a testing and calibration computer configured to2. The system of claim 1 , wherein determining the relative orientation between the base fiducial and the movable fiducial based on the image data further comprises:determining a 2D orientation of the base fiducial and a 2D orientation of the movable fiducial based on the image data;determining a 3D orientation of the base fiducial and a 3D orientation of the movable fiducial based on the 2D orientations of the movable and base fiducials and a known set of intrinsic parameters for the camera; anddetermining the relative orientation between the base fiducial and the movable fiducial based on the 3D orientations of the fiducials.3. The system of claim 2 , wherein determining the 2D orientation ...

Подробнее

Номер записи: 59

04-01-2018 дата публикации

SYSTEMS AND METHODS FOR RELIABLE RELATIVE NAVIGATION AND AUTONOMOUS FOLLOWING BETWEEN UNMANNED AERIAL VEHICLE AND A TARGET OBJECT

Номер: US20180002018A1

Автор: Jourdan Damien Bruno

Принадлежит:

A method for navigating an airborne device relative to a target comprises detecting, at an optical detector on the airborne device, an optical signal generated by one or more LEDs on the target. The method also comprises comparing, by a processor on the airborne device, the detected optical signal with a previously-detected optical signal. The method further comprises determining, by the processor based on the comparison, a change in location of at least one of the airborne device or the target. The method also comprises adjusting a position of the airborne device based on the determined change in location. The method also comprises predicting, by the processor, a movement of the target based on information indicative of at least one of a position, a rotation, an orientation, an acceleration, a velocity, or an altitude of the target, wherein the position of the airborne device is adjusted based on the predicted movement of the target. The method also comprises detecting an obstacle in a flight path associated with the airborne device and adjusting a position of the airborne device is further based, at least in part, on detected obstacle information. 1. A method , comprising:causing an airborne vehicle to follow a flight path that positions the airborne vehicle at a perch position relative to a ground-based mobile target;detecting an obstacle in the flight path of the airborne vehicle;responsively adjusting the flight path of the airborne vehicle to cause the airborne vehicle to reduce altitude from the perch position to connect to an obstacle-free path traversed by the ground-based mobile target; andcausing the airborne vehicle to follow behind the ground-based mobile target on the obstacle-free path until the obstacle is no longer detected.2. The method of claim 1 , further comprising:determining that the obstacle is no longer detected; andresponsively adjusting the flight path of the airborne vehicle to cause the airborne vehicle to continue following the ground- ...

Подробнее

Номер записи: 60

04-01-2018 дата публикации

Cooling system for unmanned aerial vehicle

Номер: US20180002023A1

Автор: Jiang Wenyan, TIAN YU

Принадлежит:

The present invention disclosed a cooling system for unmanned aerial vehicle, which includes a main body, four arms disposed on the main body, two clockwise rotating propellers and two counterclockwise rotating propellers disposed on the arms respectively; wherein at least one air guide hole on each of the arms, which guide air to a middle of the main body; the two clockwise rotating propellers are disposed diagonally and the two counterclockwise rotating propellers are disposed diagonally; a clockwise rotating propeller is on a left-front arm; each of the clockwise and the counterclockwise rotating propellers rotates to generate an airstream which is configured to sweep towards the arm, the airstreams are configured to flow to an internal part of the main body by the air guide hole. The cooling system is able to cool down the whole unmanned aerial vehicle. 1. A cooling system for an unmanned aerial vehicle , comprising: a main body , four arms disposed on the main body , two clockwise rotating propellers and two counterclockwise rotating propellers disposed on the arms respectively; wherein at least one air guide hole is disposed on each of the arms , and configured to guide air to a middle part of the main body; the two clockwise rotating propellers are disposed diagonally and the two counterclockwise rotating propellers are disposed diagonally; one of the clockwise rotating propellers is on a left-front arm; each of the clockwise and the counterclockwise rotating propellers rotates to generate an airstream which is configured to sweep towards the arm , the airstreams are configured to flow to an internal part of the main body by the air guide hole.2. The cooling system for the unmanned aerial vehicle claim 1 , as recited in claim 1 , wherein the air guide hole on each of the arms is disposed near the main body and under an area formed by the rotating of a tail of each of the clockwise rotating propellers and counterclockwise rotating propellers.3. The cooling ...

Подробнее

Номер записи: 61

04-01-2018 дата публикации

Aircraft having a Versatile Propulsion System

Номер: US20180002026A1

Автор: McCullough John Richard, Oldroyd Paul K.

Принадлежит: Bell Helicopter Textron Inc.

An aircraft having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe and a versatile propulsion system attached to the airframe. The versatile propulsion system includes a plurality of propulsion assemblies. A flight control system is operable to independently control the propulsion assemblies. The propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source. 1. An aircraft having a vertical takeoff and landing fight mode and a forward flight mode , the aircraft comprising:an airframe;a versatile propulsion system attached to the airframe, the versatile propulsion system including a plurality of propulsion assemblies; anda flight control system operable to independently control the propulsion assemblies;wherein, the propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode;wherein, in the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel; andwherein, in the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source.2. The aircraft as recited in wherein each of the propulsion assemblies further comprises:a nacelle operable to be coupled to the airframe;an engine disposed within the nacelle;a rotor hub mechanically coupled to the engine and operable to rotate responsive to operation of the engine; anda proprotor mechanically coupled to the rotor hub and operable to rotate therewith.3. The aircraft as recited in wherein each of the propulsion assemblies further comprises at least one liquid fuel tank disposed within the ...

Подробнее

Номер записи: 62

04-01-2018 дата публикации

Aircraft having a Fault Tolerant Distributed Propulsion System

Номер: US20180002027A1

Автор: John Richard McCULLOUGH, Paul K. Oldroyd

Принадлежит: BELL HELICOPTER TEXTRON INC

In some embodiment, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flight control system is operable to independently control the propulsion assemblies. The flight control system is also operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.

Подробнее

Номер записи: 63

04-01-2018 дата публикации

Obstacle avoidance device

Номер: US20180002036A1

Автор: Jiang Wenyan, TIAN YU

Принадлежит:

An obstacle avoidance device for detecting surroundings of an unmanned mobile device is disclosed, which includes a stabilization platform connected with the unmanned mobile device, wherein the stabilization platform includes a stabilizer for ensuring stably bearing at least one platform camera; and an obstacle avoidance module fixed with the stabilization platform, so as to reduce interferences to detecting the surroundings by the obstacle avoidance module when the unmanned mobile device acts. The obstacle avoidance device of the present invention is able to keep a stable attitude while the unmanned mobile device is unstable and changes an attitude thereof, so as to effectively avoid obstacles. 1. An obstacle avoidance device for detecting surroundings of an unmanned mobile device , which comprises:a stabilization platform connected with the unmanned mobile device, which comprises a stabilizer for ensuring stably bearing at least one platform camera; andan obstacle avoidance module fixed with the stabilization platform, so as to reduce interferences to detecting the surroundings by the obstacle avoidance module when the unmanned mobile device acts.2. The obstacle avoidance device claim 1 , as recited in claim 1 , wherein the stabilization platform comprises a rotation shaft unit and a stabilization holder; the obstacle avoidance module is installed on the stabilization holder; the stabilization holder is movably connected with the unmanned mobile device through the rotation shaft unit claim 1 , so that the obstacle avoidance module moves relatively to the unmanned mobile device and maintains the attitude when the unmanned mobile device acts.3. The obstacle avoidance device claim 1 , as recited in claim 1 , wherein through the rotation shaft unit claim 1 , the stabilization holder rotates in three mutually perpendicular planes claim 1 , or two mutually perpendicular planes claim 1 , or in a single plane.4. The obstacle avoidance device claim 2 , as recited in claim ...

Подробнее

Номер записи: 64

03-01-2019 дата публикации

MODULAR LIFTING SURFACE

Номер: US20190002082A1

Автор: Gonzalez Gozalbo Alfonso, PIÑEYROA DE LA FUENTE Eugenio

Принадлежит:

A method for manufacturing a modular lifting surface from a standard lifting surface, the modular lifting surface includes a central support structure including an upper skin, a lower skin and at least a first spar. The method includes providing the upper skin and the lower skin which are suitable for any of various sizes of a modular lifting surface for the standard lifting surface, wherein the upper skin and lower skin correspond to a standard upper skin and the lower skin conforms to a standard lower skin. 1. A method for assembling a modular lifting surface from a standard lifting surface , the modular lifting surface comprising a central support structure including an upper skin , a lower skin and at least a first spar , the method comprising the following steps:a) providing the upper skin and the lower skin which are suitable for all of various sizes of the standard lifting surface, wherein the upper skin and lower skin correspond to a standard upper skin suitable for all of the various sizes of the standard lifting surface, and the lower skin conforms to a standard lower skin suitable for all of the various sizes for the standard lifting surface, wherein, across a cross section of all of the various sizes of the modular lifting surface, the upper skin has a standard cord length and the lower skin has a standard cord length;b) providing a first spar which conforms, at least in part, to a first standard spar design of the standard lifting surface;c) attaching the first spar to both the upper and lower skin so that the first spar is located between said upper and lower skins,d) providing a leading edge and a trailing edge,e) attaching the leading edge to the central support structure where the first spar, upper skin and lower skin are included in the central support structure, and attaching the trailing edge to the central support structure on a second end of the central support structure, wherein the second end is opposite to the first end, andf) forming the ...

Подробнее

Номер записи: 65

03-01-2019 дата публикации

Leading Edge High-Lift Device

Номер: US20190002084A1

Автор: Dickey Eric David, Elmer Kevin Robert, Kawai Ronald Tatsuji, Liebeck Robert Hauschild, Tompkins Daniel Michael

Принадлежит: The Boeing Company

A leading edge high-lift device, that may be deployable from a wing of an aircraft, may include a leading edge and a trailing edge. A lower surface and an upper surface may both extend between the leading edge and the trailing edge. A trailing edge region may be defined by the trailing edge and an adjacent region thereto. A shaping device may be disposed at the trailing edge region and may be movable between a non-activated position and an activated position. 1. A leading edge high-lift device deployable from a wing of an aircraft , the leading edge high-lift device comprising:a leading edge;a trailing edge;a lower surface and an upper surface both extending between the leading edge and the trailing edge;a trailing edge region being defined by the trailing edge and an adjacent region thereto;a shaping device disposed at the trailing edge region, the shaping device moveable between a non-activated position and an activated position, wherein, in the activated position of the shaping device, a channel is formed between a wing of an aircraft and the trailing edge of the leading edge high-lift device; andwherein at least one of the non-activated and the activated positions of the shaping device is caused by airflow through the channel.2. The leading edge high-lift device of claim 1 , wherein the shaping device includes a curved profile in the activated position.3. The leading edge high-lift device of claim 1 , wherein the leading edge high-lift device comprises a Krueger slat or a translating slat.4. The leading edge high-lift device of claim 3 , wherein the trailing edge includes a saw tooth profile.5. The leading edge high-lift device of claim 3 , wherein the trailing edge includes a serrated profile.6. The leading edge high-lift device of claim 1 , wherein the shaping device is hingedly coupled to the lower surface of the trailing edge.7. The leading edge high-lift device of claim 6 , wherein the shaping device engages a stop in the activated position.8. The leading ...

Подробнее

Номер записи: 66

03-01-2019 дата публикации

AIRCRAFT

Номер: US20190002093A1

Автор: ICHIMURA Shigenori, IYOBE Tatsuya, Matsumoto Hiroyuki, Muramatsu Fumio, TAKITA Mizuki, TOYAMA Masayuki

Принадлежит: Panasonic Intellectual Property Management Co., Ltd.

An aircraft includes: a plurality of rotor units each including propeller and motor that drives propeller; a shock absorber covering an entire vertical length of a lateral side of the plurality of rotor units; and a plurality of rudders each being disposed downstream of a corresponding one of the plurality of rotor units and rotating about axis of rotation that extends in a direction intersecting a flow direction of air current generated by the corresponding one of the plurality of rotor units. 112-. (canceled)13. An aircraft , comprising:N rotor units each including a propeller and a motor that drives the propeller, N being an integer greater than or equal to 3;a shock absorber covering a lateral side of the N rotor units; andN rudders each being disposed downstream of a corresponding one of the N rotor units and rotating about an axis of rotation that extends in a direction intersecting a flow direction of air current generated by the corresponding one of the N rotor units,wherein the N rotor units are disposed on a virtual circle at intervals of (360 degrees/N), the virtual circle being centered about a predetermined reference point of the aircraft in a top view.14. The aircraft according to claim 13 ,wherein N is 4.15. The aircraft according to claim 13 ,wherein the shock absorber defines N ventilation holes vertically passing through the shock absorber, andeach of the N rudders is disposed in a different one of the N ventilation holes, together with the corresponding one of the N rotor units.16. The aircraft according to claim 13 ,wherein the shock absorber comprises a balloon containing gas.17. The aircraft according to claim 13 ,wherein each of the N rudders is disposed in an orientation in which the axis of rotation of each of the N rudders intersects the virtual circle along a circumferential direction.18. The aircraft according to claim 17 ,wherein each of the N rudders is disposed in an orientation in which the axis of rotation of each of the N rudders is ...

Подробнее

Номер записи: 67

03-01-2019 дата публикации

UNMANNED AERIAL VEHICLE AND OPERATIONS THEREOF

Номер: US20190002094A1

Автор: Chen Shaojie, Ou Zhigang, WANG TAO, Zhao Tao

Принадлежит:

The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors. 1. (canceled)2. A multi-rotor unmanned aerial vehicle (UAV) having a weight , the UAV comprising:a housing forming a body of the UAV, the housing comprising an outer surface and an inner surface, the inner surface forming a cavity;one or more electrical components disposed within the cavity, the one or more electrical components selected from a group comprising a power source, flight control module, inertial measurement unit (IMU), and GPS receiver;a landing stand attached to and extending away from the housing to bear the weight of the UAV when the UAV is not airborne; anda magnetometer attached to the landing stand at a distance of at least about 3 cm from the one or more electrical components.3. The UAV of claim 2 , further comprising a carrier configured to support a payload device.4. The UAV of claim 3 , wherein the landing stand is one of two landing stands claim 3 , the two landing stands being attached to a lower body potion of the housing at corresponding attachment interfaces claim 3 , and wherein the carrier includes a gimbal claim 3 , and wherein the UAV further comprises the payload device claim 3 , the payload device including a camera claim 3 , with both the gimbal and the camera positioned between the two landing stands.5. The UAV of claim 2 , wherein the landing stand includes an attachment interface adjacent the housing claim 2 , the attachment interface having an opening claim 2 , and wherein the UAV further comprises a wire connected to the magnetometer and extending through the opening and into the cavity.6. The UAV of claim 2 , further comprising:multiple actuators ...

Подробнее

Номер записи: 68

03-01-2019 дата публикации

WING FLAPPING APPARATUS

Номер: US20190002097A1

Автор: HAMAMOTO Masaki, Kato Masanori, Miyake Tomoyuki, Nakamura Kazutaka

Принадлежит:

A wing flapping apparatus includes a motive power source; a power transmission mechanism; and a wing unit driven by the power transmission mechanism. The power transmission mechanism includes a rotation transmission member configured to rotate upon reception of motive power transmitted from the motive power source; a slider configured to linearly reciprocate in an X-axis direction upon reception of the motive power transmitted from the rotation transmission member and a rotating body configured to reciprocate in a rotation direction upon reception of the motive power transmitted from the slider. The wing unit is configured to swing such that its distal end moves approximately in the X-axis direction as the rotating body reciprocates in the rotation direction. The power transmission mechanism further includes a pair of crank arms each configured to connect the rotation transmission member and the slider. The pair of crank arms each has: one end rotatably connected to the rotation transmission member and the other end rotatably and slidably connected to the slider. 1. A wing flapping apparatus comprising:a frame body;a motive power source installed in the frame body;a wing unit; anda power transmission mechanism configured to transmit motive power generated in the motive power source to the wing unit;the wing unit being configured to be driven by the power transmission mechanism; a rotation transmission member rotatably supported by the frame body, the rotation transmission member being configured to rotate about a first rotation axis as a center of rotation upon reception of the motive power transmitted from the motive power source;', 'a slider movably supported by the frame body, the slider being configured to linearly reciprocate in a first direction upon reception of the motive power transmitted from the rotation transmission member; and', 'a rotating body rotatably supported by the frame body, the rotating body being configured to, upon reception of the motive ...

Подробнее

Номер записи: 69

03-01-2019 дата публикации

UNMANNED AERIAL VEHICLE-BASED EXTERNAL WALL SPRAY PRINTING SYSTEM AND SPRAYING METHOD THEREOF

Номер: US20190002100A1

Автор: ZHAO Zhihui

Принадлежит:

A UAV-based external wall spray printing system and a spraying method thereof, wherein a spray nozzle is disposed on the UAV. The method comprises: A. controlling a UAV to fly along edges of an external wall, and measure an area to be sprayed; B. calculating a spray trajectory for a pattern, before acquiring various positioning coordinates, establishing corresponding relationships between the coordinates and spray feature data; C. controlling the UAV to fly to positions of the area according to the respective coordinates of the spray trajectory, and calling the corresponding spray feature data to control the nozzle to spray a coating material, thus completing spraying the pattern. The spray printing system and method can rapidly spray and print an advertisement on a wall by using a UAV, thereby reducing the labor intensity and construction difficulty for construction workers. 1. A UAV-based external wall spraying method , wherein the UAV has a spray nozzle disposed , applied to spray painting a coating material , the method includes:A. controlling a UAV to fly along a plurality of edges of an external wall, before mapping an area to-be-sprayed according to a flight trajectory of the UAV;B. using a mapped area to-be-sprayed to calculate a spray trajectory for a pattern to-be-sprayed on the area to-be-sprayed, before acquiring various positioning coordinates on the spray trajectory, and establishing a corresponding relationship between the various positioning coordinates and a plurality of spray feature data based on the pattern to-be-sprayed;C. controlling the UAV to fly to a plurality of positions of the area to-be-sprayed in accordance with the positioning coordinates of the spray trajectory respectively and orderly, before calling the spray feature data corresponding to each of the positioning coordinates and controlling the nozzle to spray the coating material, thus completing spraying the pattern.2. The method according to claim 1 , wherein the UAV has a height ...

Подробнее

Номер записи: 70

06-01-2022 дата публикации

ENHANCED SYSTEMS, APPARATUS, AND METHODS FOR POSITIONING OF AN AIRBORNE RELOCATABLE COMMUNICATION HUB SUPPORTING A PLURALITY OF WIRELESS DEVICES

Номер: US20220004980A1

Автор: Burch, Doyle David A., Popp Brian D., V Reuben F.

Принадлежит:

Improved systems, apparatus, and methods for enhanced positioning of an airborne relocatable communication hub supporting wireless devices are described. Such a method begins with moving an aerial communication drone operating as the airborne relocatable communication hub to a first deployed airborne position, detecting a first signal broadcast by a first wireless device using a communication hub interface on the drone, and detecting a second signal broadcast by a second wireless device using the communication hub interface. The method has the drone comparing a first connection signal strength for the first signal and a second connection signal strength for the second signal, and repositioning the aerial communication drone to a second deployed airborne position based upon the comparison. Once repositioned at the second deployed airborne position, the method has the drone linking the first and second wireless devices using the communication hub interface on the aerial communication drone. 136-. (canceled)37. An improved method for enhanced positioning of an airborne relocatable communication hub supporting a plurality of wireless devices , the method comprising the steps of:moving an aerial communication drone operating as the airborne relocatable communication hub to a first airborne deployed position;detecting, by a directional antenna coupled to a communication hub interface on the aerial communication drone, a plurality of concentrations of the wireless devices, wherein each of the concentrations corresponding to one of a respective plurality of directions from the first deployed airborne position;relocating the aerial communication drone operating as the airborne relocatable communication hub to a second airborne deployed position based upon a highest of the concentrations of the wireless devices, the second airborne deployed position being in the one of the directions corresponding to the highest of the detected concentrations of the wireless devices; ...

Подробнее

Номер записи: 71

03-01-2019 дата публикации

SECURE WIRE-BASED SYSTEM FOR A DRONE

Номер: US20190002101A1

Автор: de Marliave Guilhem, Dubois Olivier, Penet Timothée

Принадлежит:

The invention relates to a secure wire-based system for a drone. Said system ensures suitable traction on the wire during normal control of the drone and automatically locks the wire to a maximum length predefined by the user. The locking is in one direction: it locks the unwinding of the wire without preventing the winding thereof. The drone thus moves within a half-sphere, the radius of which is the maximum length defined by the user. 11) Wire-based system (X) , connecting a drone to its base on the ground , comprising:{'b': '10', 'at least an electric wire () or a data transfer wire or a mechanical tension wire,'}{'b': '14', 'at least a drum () for winding the wire,'}{'b': '13', 'at least an electric motor () for driving the drum,'}at least a wire locking mechanism,Said system is characterized by the fact that it comprises both:an adjustment device allowing the user to define a maximum length of unwound wire;an automatic locking device at the maximum user-defined length, the locking device being unidirectional: it makes it impossible to exceed the maximum length, while the rewinding of the wire on its drum remains possible.22) System of wherein the unidirectional locking mechanism (X) is a ratchet wheel.331) System of wherein the locking mechanism is provided by one or more extra thickness layers () on the wire claim 1 , adjustable or not.48) System of wherein the locking system is a contact brake (X) depending on the length of the wire claim 1 , the unidirectional characteristic of the brake being provided by one of the following procedures:Procedure 1: (i) brake activation at a wire length less or equal to the user-defined length, (ii) adjustment of the traction motor torque to its maximum, (iii) progressive release of the brake until the drum rotates, (iv) detection of the drum rotation direction, (v) if the drum rotates in the winding direction of the wire, progressive release of the brake.{'b': '9', 'Procedure 2: (i) brake activation at the user-defined ...

Подробнее

Номер записи: 72

03-01-2019 дата публикации

TETHERED UNMANNED AERIAL VEHICLE SYSTEM

Номер: US20190002102A1

Автор: Hundemer Hank J.

Принадлежит:

In one aspect, an example system includes: (i) a base including a bottom surface and a first coupling-point; (ii) a vertically-oriented elongate structure comprising a lower end, an upper end, and an inner channel, wherein the inner channel comprises an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end; (iii) a deployable cushioning-device coupled to the elongate structure; and (iv) a tether comprising a first portion, a second portion, a third portion, and a fourth portion, wherein the first portion is coupled to the first coupling-point, the second portion is coupled to a second coupling-point of the UAV, the third portion extends through the inner channel, the fourth portion extends from the upper access-point to the second coupling-point, and the fourth portion has a length that is less than a distance between the upper access-point and the bottom surface. 1. A system comprising:a base comprising a bottom surface and a first coupling-point;a vertically-oriented elongate structure comprising a lower end, an upper end, and an inner channel, wherein the inner channel comprises an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end;an unmanned aerial vehicle (UAV) comprising a second coupling-point; anda tether extending through the inner channel of the vertically-oriented elongate structure, wherein a first end of the tether is coupled to the first coupling-point of the base and a second end of the tether is coupled to the second coupling-point of the UAV.2. The system of claim 1 , wherein the base comprises a vehicle.3. The system of claim 1 , wherein the base comprises a spooling mechanism configured for adjusting a length of the tether claim 1 , and wherein the first coupling-point is disposed on the spooling mechanism.4. The system of claim 1 , wherein the base comprises a power source claim 1 , and ...

Подробнее

Номер записи: 73

03-01-2019 дата публикации

UNMANNED AERIAL VEHICLES AND RELATED METHODS AND SYSTEMS

Номер: US20190002103A1

Автор: Aldana Lopez Rodrigo, de la Guardia Gonzalez Rafael, Gomez Gutierrez David, Parra Vilchis Jose I.

Принадлежит:

Unmanned aerial vehicles and related methods and systems are disclosed. An example apparatus includes a processor to determine whether a first location of an unmanned vehicle and a second location of a virtual event is within a threshold distance; and a game experience controller to: control the unmanned vehicle based on a first command associated with a non-augmented state of the unmanned vehicle in response to the first location of the unmanned vehicle and the second location of the virtual event being outside of the threshold distance; and in response to the first location of the unmanned vehicle and the second location of the virtual event being within the threshold distance, control the unmanned vehicle based on a second command associated with an augmented state of the unmanned vehicle to simulate the unmanned vehicle being affected by the virtual event. 1. An apparatus for use with an unmanned vehicle , comprising:a processor to determine whether a first location of an unmanned vehicle and a second location of a virtual event is within a threshold distance; and control the unmanned vehicle based on a first command associated with a non-augmented state of the unmanned vehicle in response to the first location of the unmanned vehicle and the second location of the virtual event being outside of the threshold distance; and', 'in response to the first location of the unmanned vehicle and the second location of the virtual event being within the threshold distance, control the unmanned vehicle based on a second command associated with an augmented state of the unmanned vehicle to simulate the unmanned vehicle being affected by the virtual event., 'a game experience controller to2. The apparatus of claim 1 , wherein the game experience controller is further to execute at least one of an audio command or a visual command that simulates the unmanned vehicle being affected by the virtual event in response to the first location of the unmanned vehicle and the second ...

Подробнее

Номер записи: 74

03-01-2019 дата публикации

UNMANNED AERIAL VEHICLE ESCAPE SYSTEM, UNMANNED AERIAL VEHICLE ESCAPE METHOD, AND PROGRAM

Номер: US20190002104A1

Автор: KAGEYAMA Takayuki, MUKAI Hideaki

Принадлежит:

To avoid interfering with a participant when information on a venue of a competition or an event is provided by using an unmanned aerial vehicle, participant position information acquisition means of an unmanned aerial vehicle escape system acquires participant position information on a position of the participant in the venue of the competition or the event. Movement instruction means instructs an unmanned aerial vehicle for providing information on the venue to move to a position defined based on the participant position information. Layout information acquisition means acquires layout information on a layout of the venue. Escape destination determination means determines an escape destination of the unmanned aerial vehicle based on the participant position information and the layout information. Escape means causes the unmanned aerial vehicle to escape to the escape destination determined by the escape destination determination means. 1. An unmanned aerial vehicle escape system , comprising at least one processor configured to:acquire participant position information on a position of a participant in a venue of a competition or an event;instruct an unmanned aerial vehicle to move to a position based on the participant position information;acquire layout information on a layout of the venue;determine a destination of the unmanned aerial vehicle based on the participant position information and the layout information; andcause the unmanned aerial vehicle to move to the destination.2. The unmanned aerial vehicle escape system according to claim 1 ,wherein the layout information associates each of a plurality of positions in the venue with a reference direction for determining the destination, andwherein the at least one processors is configured to determine the destination based on the reference direction associated with the position of the participant.3. The unmanned aerial vehicle escape system according to claim 2 ,wherein a competition in which the participant ...

Подробнее

Номер записи: 75

03-01-2019 дата публикации

Aerial vehicle image capturing systems

Номер: US20190002124A1

Автор: Kyle Garvin

Принадлежит: Individual

A method, system, apparatus, and/or device for capturing an image from an aerial vehicle. The method, system, apparatus, and/or device may include a boom, a motor, a propeller, a controller, a top plate, a bottom plate, and an image capturing device. The boom may be an arm that extends outwardly. The motor may be connected to an end of the boom. The propeller may be connected to the motor. The motor may be configured to rotate the propeller to lift the system, the apparatus, and/or the device into flight when the motor is engaged. The controller may be configured to control the motor. The top plate may be connected to a first end of the boom. The bottom plate may be connected to a second end of the boom. The image capturing device may be mounted to the top plate or the bottom plate.

Подробнее

Номер записи: 76

03-01-2019 дата публикации

AUTONOMOUS DOCKING STATION FOR DRONES

Номер: US20190002127A1

Автор: STRAUS Itai, TAL Yitzhak

Принадлежит:

A solution to the problem of short battery life of drones and operation in isolated or distant areas of service, by means of docking station/stations that allow for the autonomous landing/takeoff, storage, recharging and/or battery swapping for the drone/drones. The station is multi-cell station for drones with one or more landing/takeoff cells; at least two docking/storage cells; a transitioning closed-loop system configured for transporting the drones within the landing/takeoff cells and docking/storage cells; and control means configured for autonomous control, operation and management of the multi-cell station, where each one of the one or more landing/takeoff cells and at least two docking/storage cells shares at least two sides with neighbouring cells. Recharging mechanism for recharging the stored drones and transitioning mechanism for circulating the drones within the cells of the station are also provided. 1. A modular and scalable docking station for drones comprising:one or more landing/takeoff cells;one or more docking/storage cells;andcontrol means configured for autonomous control, operation and management of said modular and scalable docking station,wherein said landing/takeoff cells are configured as said docking/storage cells, said landing/takeoff cells comprising means for docking/storage of said drones, said means comprising a cone, said cone is accommodated in said landing/takeoff and docking/storage cells and configured in upside down position to harbour said drones,wherein said cone comprises wheels attached to its lower end, said wheels are in frictional communication with lower flat surface within said cells, andwherein said modular and scalable docking station comprising at least one landing/takeoff cell which is a docking/storage cell.2. The docking station according to claim 1 , further comprising recharging means for recharging batteries of said drones.3. The docking station according to claim 2 , wherein said recharging means comprises: ...

Подробнее

Номер записи: 77

03-01-2019 дата публикации

METHODS AND SYSTEMS OF ANCHORING AN UNMANNED AERIAL VEHICLE ON A GROUND STATION

Номер: US20190002128A1

Автор: BLONDER Sagi, Jaffe Jonathan, RAZ Raviv

Принадлежит:

An unmanned aerial vehicle (UAV) ground station, comprising: a landing surface having a perimeter and a center; a plurality of pushers held above the landing surface by a plurality of linear actuators; at least one electro-mechanical connector attached to one of the plurality of pushers, mechanically adapted to be electrically connected to a compatible electro-mechanical connector of a UAV; and a landing detection controller adapted to instruct the plurality of linear actuators to move the plurality of pushers simultaneously from the perimeter toward the center when a landing event related to the UAV is detected. 1. (canceled)2. The UAV ground station of claim 5 , wherein said plurality of pushers includes at least two horizontally disposed pushing rods and said plurality of linear actuators include a plurality of vertical rods claim 5 , each of said plurality of vertical rods is attached to an end of one of said at least two horizontally disposed pushing rods.3. The UAV ground station of claim 5 , wherein said plurality of pushers includes a first pair of pushing rods and a perpendicular second pair of pushing rods claim 5 , wherein said first pair of pushing rods is located above said second pair of pushing rods to allow simultaneous movement of said first and second pairs of pushing rods and toward said center.4. The UAV ground station of claim 3 , wherein said plurality of linear actuators move each of said first pair of pushing rods and said second pair of pushing rods simultaneously from said perimeter toward said center.5. An unmanned aerial vehicle (UAV) ground station claim 3 , comprising:a landing surface having a perimeter and a center;a plurality of pushers held above said landing surface by a plurality of linear actuators;at least one electro-mechanical connector attached to one of said plurality of pushers, mechanically adapted to be electrically connected to a compatible electro-mechanical connector of a UAV; anda landing detection controller adapted ...

Подробнее

Номер записи: 78

03-01-2019 дата публикации

Landing Pad For Unmanned Aerial Vehicle Delivery

Номер: US20190002129A1

Автор: Falesch Alex J., Walsh Ryan

Принадлежит:

A landing pad receives and stores packages delivered from an aerial vehicle are awaiting pickup from an aerial vehicle. The landing pad can be placed outside of a window and can contain a transmitter for sending out an identification signal via radio frequency to aid aerial vehicles in finding the landing pad. The landing pad contains a landing platform with a trapdoor that leads to a storage compartment. The trapdoor can be configured to only open when it receives a signal from an authorized aerial vehicle. The storage compartment can be accessed via a storage compartment door which can contain a locking mechanism. The storage compartment can be climate controlled. The landing pad can also have a transmitter that emits sounds to discourage animals from nesting on or near the landing pad. The landing pad can also include a solar power generator as a source of electrical energy. 1. A method of delivering a package via a drone capable of transmitting a first signal recognizable by a receiver associated with a landing pad , wherein said method comprises:(a) loading said drone with said package;(b) employing a global positioning system device to navigate said drone to said landing pad, wherein said landing pad comprises a landing platform with a trapdoor in a normally closed position and a storage compartment with a floor and a conveyor belt and a hydraulic system configured to tilt said floor;(c) opening said trapdoor of said landing platform upon receipt of said first signal by said receiver to expose an interior of said storage compartment; and(d) actuating a mechanism operatively associated with said drone to transfer said package into said storage compartment.2. The method of claim 1 , further comprising:(e) positioning said landing pad in a window of a residence.3. The method of claim 2 , further comprising:(f) configuring said landing pad to fold into said window when not interacting with said drone.4. The method of claim 1 , wherein said storage compartment ...

Подробнее

Номер записи: 79

06-01-2022 дата публикации

MOTOR CONTROL SYSTEM, UNMANNED AERIAL VEHICLE, MOVING VEHICLE, AND MOTOR CONTROL METHOD

Номер: US20220006418A1

Автор: SATO Daisuke

Принадлежит: Panasonic Intellectual Property Management Co., Ltd.

A motor control system includes a motor and a motor control device. The motor control device includes an acquisition unit, a. diagnosis unit, and a control unit. The acquisition unit acquires control data. The control data includes a command, transmitted from each of a plurality of controllers, with respect to the motor. The plurality of controllers are configured to communicate with the motor control device. The diagnosis unit makes a diagnosis of multiple sets of the control data provided by the plurality of controllers and acquired by the acquisition unit. The control unit controls the motor by using a single set of control data selected based on a result of the diagnosis made by the diagnosis unit from the multiple sets of the control data. 1. A motor control system comprising ,:a motor; anda motor control device provided for the motor,the motor control device including:an acquisition unit configured to acquire control data including a command, transmitted from each of a. plurality of controllers, with respect to the motor, the plurality of controllers being configured to communicate with the motor control device:a diagnosis unit configured to make a diagnosis of multiple sets of the control data provided dry the plurality of controllers and acquired by the acquisition unit; anda control unit configured to control the motor by using a single set of control data selected, based on a result of the diagnosis made by the diagnosis unit, from the multiple sets of the control data.2. The motor control system of claim 1 , whereinthe motor control device is configured to acquire a result of diagnosis made by the diagnosis unit of another motor control device3. The motor control system of claim 1 , whereinthe motor control device has the capability of transmitting the result of diagnosis made by the diagnosis unit.4. The motor control system of claim 1 , whereineach of the plurality of controllers is configured to generate the control data based on a result of detection ...

Подробнее

Номер записи: 80

05-01-2017 дата публикации

MOTOR MOUNTING STRUCTURE IN PAN-TILT DEVICE

Номер: US20170002975A1

Автор: SUN Hongtao, Yang Jianjun

Принадлежит: ZEROTECH (SHENZHEN) INTELLIGENCE ROBOT CO., LTD.

A gimbal includes a base and a first support rotatably provided on the base; the first support is in an L-shape and includes a first arm and a second arm constructing the L shape, the first arm is rotatably connecting with the base; and the second arm includes a first electric motor fixing structure. An unmanned aerial vehicle including the gimbal is also provided. 110-. (canceled)11. A gimbal , including a base and a first support rotatably provided on the base , wherein the first support is in an L-shape and includes a first arm and a second arm constructing the L shape ,the first arm is rotatably connecting with the base; andthe second arm includes a first electric motor fixing structure.12. The gimbal according to claim 11 , further including a base electric motor provided on the base claim 11 , wherein the first arm is rotatably connected with the base electric motor claim 11 , whereby the first arm is rotatably connected to the base; andthe first support is capable of being driven by the base electric motor to rotate about a first rotation axis.13. The gimbal according to claim 12 , further including a first electric motor claim 12 , wherein the first electric motor is fixed on the first support by the first electric motor fixing structure.14. The gimbal according to claim 13 , wherein the first electric motor fixing structure includes a mounting groove provided in an end of the second arm.15. The gimbal according to claim 14 , wherein the first electric motor includes a mounting plug claim 14 , and the mounting plug of the first electric motor is inserted in the mounting groove of the second arm.16. The gimbal according to claim 12 , further including a first electronic speed governor claim 12 , wherein the first electronic speed governor is fixed on the second arm.17. The gimbal according to claim 16 , wherein the second arm further includes a recess provided at its sidewall claim 16 , and the first electronic speed governor is provided in the recess of the ...

Подробнее

Номер записи: 81

05-01-2017 дата публикации

AMR SYSTEM WITH FLY-BY MODE

Номер: US20170003142A1

Автор: Allcorn Roger, Salser Floyd Stanley, Simmons William Monty

Принадлежит:

The disclosed inventions include and apparatus and method for providing a universal Automatic Meter Reading (AMR) system configured with fly-by functionality. Such system may be configured to work in a plurality of modes including a walk-bay, drive-by, fixed network, and fly-by mode without hardware modifications. The system is configured to automatically calibrate so that the water meter transmitter operates at a minimum transmitted signal power level. Additional features include automatic hardware self-healing features where the system continues to function after certain hardware failures occur. 1. An automatic meter reading (AMR) system configured to transfer data from a data source to a data user , said AMR system comprising:a plurality of data source modules disposed within a predefine area, each of said plurality of data source modules comprising (i) a power source configured for supplying power to said data source module and (ii) a processing device electrically associated with at least one of one of integral and external memory, said processing device further electrically associated with communication circuitry comprising a programmable transmitter electrically associate with an antenna;an airborne remote receiver configured to maneuver within a predefined area to position said remote receiver within communication range with each of said plurality of data source modules;wherein said remote receiver and each of said plurality of data source modules track the passage of time and wherein the time data for each of said plurality of data source modules is synchronized with the remote receiver time data; andwherein said processing device is configured to transmit a module-data-signal according to a predefined module schedule.2. An AMR system as in claim 1 , wherein at least one of said plurality of data source modules is a universal meter transmitter (UMT) electrically associate with a utility meter claim 1 , said power source is a battery and said airborne remote ...

Подробнее

Номер записи: 82

04-01-2018 дата публикации

UNMANNED AERIAL VEHICLE WIND TURBINE INSPECTION SYSTEMS AND METHODS

Номер: US20180003161A1

Автор: Blanc-Pâques Fabien, Michini Bernard J.

Принадлежит:

Methods, systems and apparatus, including computer programs encoded on computer storage media for an unmanned aerial vehicle (UAV) wind turbine inspection system. One of the methods includes obtaining first sensor information by an unmanned aerial vehicle (UAV), the first sensor information describing physical aspects of a wind turbine, including one or more blades of the wind turbine. An orientation of the blades of the wind turbine are determined based on the obtained first sensor information. A flight pattern for the UAV to inspect the blades of the wind turbine is determined, the flight pattern being based on the determined orientation of the blades. Each of the blades of the wind turbine is inspected by the UAV according to the determined flight pattern, the inspection including obtaining second sensor information describing the blades of the wind turbine. 1. A system comprising one or more processors and one or more computer storage media storing instructions that when executed by the one or more processors causes the one or more processors to perform operations comprising:obtaining first sensor information by an unmanned aerial vehicle (UAV), the first sensor information describing physical aspects of a wind turbine, including one or more blades of the wind turbine;determining an orientation of the blades of the wind turbine based on the obtained first sensor information;determining a flight pattern for the UAV to inspect the blades of the wind turbine, wherein the flight pattern is based on the determined orientation of the blades; andinspecting by the UAV, each of the blades of the wind turbine according to the determined flight pattern, wherein inspecting comprises obtaining second sensor information describing the blades of the wind turbine.2. The system of claim 1 , wherein the operation of determining an orientation of the blades comprises:activating a distance sensor that measures distance from the UAV to the wind turbine, and storing measurements ...

Подробнее

Номер записи: 83

05-01-2017 дата публикации

SYSTEM AND METHOD FOR CONTROLLING TAKEOFF AND LANDING OF DRONE

Номер: US20170003689A1

Автор: LEE Yong-Moo

Принадлежит:

Disclosed herein is a system and method for controlling the takeoff and landing of a drone. The system for controlling the takeoff and landing of a drone includes: a landing control device configured to vary the transmission range of Low Frequency (LF) landing control signals based on whether a response signal to a transmitted landing control signal in the transmission range is received, and to transmit a landing signal if the varied transmission range is less than a minimum radius; and a drone configured to fly in a control signal-based flight mode based on a landing control signal when receiving the landing control signal transmitted from the landing control device during GPS signal-based flight, and to land at a destination by flying in a landing mode when receiving a landing signal from the landing control device during flight in the control signal-based flight mode. 1. A system for controlling takeoff and landing of a drone , the system comprising:a landing control device configured to vary a transmission range of Low Frequency (LF) landing control signals based on whether a response signal to a transmitted landing control signal in the transmission range is received, and to transmit a landing signal if the varied transmission range is less than a minimum radius; anda drone configured to fly in a control signal-based flight mode based on a landing control signal when receiving the landing control signal transmitted from the landing control device during Global Positioning System (GPS) signal-based flight mode, and to land at a destination by flying in a landing mode when receiving a landing signal from the landing control device during flight in the control signal-based flight mode.2. The system of claim 1 , wherein the landing control device comprisesa transmission range setting unit configured to set a maximum transmission radius to be a transmission range in an initial state and to vary the transmission range based on whether a response signal to a landing ...

Подробнее

Номер записи: 84

07-01-2016 дата публикации

AERIAL VEHICLE ACQUISITION OF SEISMIC DATA

Номер: US20160003954A1

Автор: Brockman Chad, Broussard III Floyd L., Chen Duo, Graeber Ross, Kumar Vijay, Ludvigsen Hallgrim, Pupim Kano Daniel, Richardson Andrew, Whitley Stephen

Принадлежит:

Methods and apparatus that facilitate acquisition of seismic data. A plurality of acquisition locations within an area of interest may be determined and provided to aerial vehicles. Seismic data may be received from the aerial vehicle. In another example, an aerial vehicle includes a positioning system that determines location of the apparatus; a seismic sensor that senses seismic data; a memory that stores seismic data; and a transceiver that provides telemetric data and the seismic data to a controller device. In at least one example, a method for acquiring seismic data is provided including receiving location information at an aerial vehicle. The aerial vehicle may navigate to a location based on the location information and a seismic sensor may acquire seismic data. The aerial vehicle may be navigated to a controller device and the acquired seismic data may be provided to the controller device. 1. A method for acquiring seismic data , comprising:receiving location information at an aerial vehicle including a seismic sensor;navigating the aerial vehicle to a location based on the location information;engaging the seismic sensor;acquiring seismic data by the seismic sensor; andtransmitting the seismic data acquired at the seismic sensor to the controller device.2. The method of claim 1 , further comprising:detecting engagement of a seismic sensor of another aerial vehicle via the seismic sensor of the aerial vehicle; andtransmitting an indication of the engagement of the seismic sensor of the another aerial vehicle.3. The method of claim 1 , wherein engaging the seismic sensor comprises:releasing a holding mechanism holding the seismic sensor.4. The method of claim 1 , wherein engaging the seismic sensor comprises:reversing a thrust of a motor of the aerial vehicle.5. The method of claim 1 , further comprising:transmitting telemetric data to the controller device.6. The method of claim 5 , further comprising:receiving a navigation instruction from the controller ...

Подробнее

Номер записи: 85

04-01-2018 дата публикации

COGNITIVE TOUR GUIDE SYSTEM

Номер: US20180003509A1

Автор: Baughman Aaron Keith, Eggenberger Christian, JENZER Lars, Trim Craig Matthew

Принадлежит:

Methods, computer program products, and systems are presented. The methods include, for instance: providing a cognitive tour guide service to a group of participants for a tour with an initial route planned by participants registration information and environment information along the initial route. During the tour, real time sensory data on the participants and environment are collected by a cognitive agent accompanying the group to lead the tour are relayed to a cognitive tour guide engine, and real time multi-objective optimization is modeled and performed. The participants are regrouped responsive to their respective objectives of the tour as represented by respective levels of interest in certain stage of the tour as well as circumstances of the environment. Respective subgroups are formed from the participants per respective objectives, and respective new routes are selected from a set of optimal solutions for each subgroup. During the tour, the cognitive tour guide engine iteratively optimizes routes responsive to incoming real time sensory data, objectives of the tour, and participant feedback. 1. A computer implemented method for providing a cognitive tour guide service to a group of participants , comprising:collecting, by a cognitive tour guide engine running on a computer, sensory data on the participants and on environments of a tour in real time captured by two or more cognitive agents accompanying and leading the group for the tour with a present route such that the cognitive tour guide engine learns location of the group, respective pace of travel for the participants, and respective level of interest of the participants for a landmark in the present route;optimizing, by the cognitive tour guide engine, the present route according to at least two objectives of the tour in real time during the tour, wherein each of the at least two objectives of the tour is optimized based on the sensory data on the participants and on the environments of the tour ...

Подробнее

Номер записи: 86

02-01-2020 дата публикации

Missile for intercepting alien drones

Номер: US20200003530A1

Автор: Franco METZ, Manuel METZ

Принадлежит: RHEINMETALL AIR DEFENCE AG, Skysec GmbH

The invention relates to a missile (1) for intercepting alien drones (21), comprising a capturing net (9) and a parachute (18), wherein a plurality of weights (15) are connected to the capturing net (9), wherein the capturing net (9) can be ejected from the missile (1) and the weights (15) can be ejected from the missile (1). The capturing of the alien drone is improved by the fact that the capturing net (9) can be ejected by a first means and the weights (15) can be ejected by a second means, wherein the weights (15) and the capturing net (9) can be ejected at different times from the missile (1).

Подробнее

Номер записи: 87

03-01-2019 дата публикации

SYSTEMS AND METHODS FOR STARTING A TURBINE ENGINE

Номер: US20190003398A1

Автор: Binion Sean Christopher, Gibson Nathan Evan McCurdy, KROGER Christopher James, Waun Scott Douglas

Принадлежит:

Systems and methods for starting a powerplant are provided. In one exemplary aspect, a starting system of a powerplant includes one or more features that allow for the powerplant to be started electrically with a burst of electrical power and without deriving electrical power from an offboard power source or a relatively heavy onboard energy storage device. 1. A method for fast starting a powerplant for a vehicle , the powerplant comprising a starter and a capacitive accumulator in electrical communication with the starter , the powerplant further comprising a shaft , the starter operably coupled with the shaft , the method comprising:charging the capacitive accumulator to a predetermined charge with a power source disposed offboard of the vehicle;disconnecting the capacitive accumulator from the power source such that the capacitive accumulator and the power source are no longer in electrical communication; anddischarging at least a portion of the predetermined charge from the capacitive accumulator to deliver an amount of electrical power to the starter such that the starter drives the shaft to a predetermined rotational speed.2. The method of claim 1 , wherein after the capacitive accumulator is disconnected from the power source claim 1 , the starter draws electrical power only from the capacitive accumulator to start the powerplant.3. The method of claim 1 , wherein after discharging claim 1 , the method further comprises:detaching the capacitive accumulator from the powerplant such that the capacitive accumulator is no longer onboard the vehicle or powerplant.4. The method of claim 1 , wherein the starter is a starter generator claim 1 , and wherein after the starter drives the shaft to the predetermined rotational speed claim 1 , the method further comprises:switching the starter generator into an electric generator; andrecharging the capacitive accumulator to a predetermined charge.5. The method of claim 4 , wherein after recharging claim 4 , the method ...

Подробнее

Номер записи: 88

13-01-2022 дата публикации

Active Lift Control Device and Method

Номер: US20220009618A1

Автор: John A. Cooney, Jr., Neal E. Fine

Принадлежит: Arctura Inc

A lift control device actively controls the lift force on a lifting surface. The device has a protuberance near a trailing edge of its lifting surface, which causes flow to separate from the lifting surface, generating regions of low pressure and high pressure which combine to increase the lift force on the lifting surface. The device further includes a means to keep the flow attached around the protuberance or to modify the position of the protuberance in response to a command from a central controller, so as to provide an active control of the lift between a maximum value and a minimum value.

Подробнее

Номер записи: 89

03-01-2019 дата публикации

FRANGIBLE FASTENERS WITH FLEXIBLE CONNECTORS FOR UNMANNED AIRCRAFT, AND ASSOCIATED SYSTEMS AND METHODS

Номер: US20190003511A1

Автор: Leon Michael Matthew, Rubesh Kristian

Принадлежит:

Frangible fasteners with flexible connectors for unmanned aircraft, and associated systems and methods are disclosed. A representative aircraft includes a fuselage portion, a wing portion, a winglet carried by the wing portion, and a frangible fastener coupling the winglet portion to the wing portion. The frangible fastener can include an outer body with a first portion in contact with the wing portion, a second portion in contact with the winglet portion, and a frangible portion between the first and second portions. A flexible member is positioned at least partially within the outer body and is connected to the first portion so as to extend through and out of the second portion. A stop element is carried by the flexible member. 1. An unmanned aircraft , comprising:a fuselage portion;a wing portion;a winglet carried by the wing portion; and an outer body with a first portion in contact with the wing portion, a second portion in contact with the winglet portion, and a frangible portion between the first and second portions;', 'a flexible member positioned at least partially within the outer body, connected to the first portion, and extending through and out of the second portion; and', 'a stop element carried by the flexible member., 'a frangible fastener coupling the winglet portion to the wing portion, the frangible fastener including2. The aircraft of wherein the flexible member is crimped to the first portion.3. The aircraft of wherein the flexible member includes a cable.4. The aircraft of wherein the flexible member includes a solid wire.5. The aircraft of wherein the stop element is crimped to the flexible member.6. The aircraft of wherein the outer body has a hollow internal cavity with an opening toward one end of the outer body claim 1 , and wherein the flexible member includes a cable having a first end positioned within the hollow cavity and fixedly attached to the outer body claim 1 , the cable extending through the opening and away from the outer body ...

Подробнее

Номер записи: 90

07-01-2016 дата публикации

Ultra High Speed Navigation Magnetic Satellite and Unmanned Aircraft

Номер: US20160004250A1

Автор: Pan James

Принадлежит:

The present invention is about a new satellite or unmanned aircraft guided by earth's magnetic fields, instead of gravitational fields, as in the case of traditional satellites. This type of magnetic satellites can fly many times faster than traditional satellites, and sustain a much heavier load if necessary. In order to navigate in earth's magnetic fields, the magnetic satellite needs to be heavily charged. The charges, interacting with the magnetic field, induce a magnetic force, which replaces the gravitational force as the centripetal force for circular motion. 1. A magnetic satellite or unmanned aircraft consists of one or multiple dimensions of arrays of heavily charged regions , each of which is sandwiched by insulators or in vacuum , with wings and links connecting to other charged regions or a central commanding unit or main body of the satellite or unmanned aircraft.2. The magnetic satellite or unmanned aircraft of claim 1 , wherein the charged regions can be shielded by computer programmed or controlled metal panels or units claim 1 , in order to regular the amount of electric fields originating from the charges.3. The magnetic satellite or unmanned aircraft of claim 1 , wherein the magnetic claim 1 , gravitational claim 1 , and wind forces are sensed and regulated to guide the motions of the satellite or unmanned aircraft equipped with jet or missile engines.4. The magnetic satellite or unmanned aircraft of claim 1 , wherein the charged region or device is a spherical or other shaped conductor shell claim 1 , surrounded and sandwiched by insulators claim 1 , with a semiconductor region in the center core claim 1 , and a metal in contact with the outside insulator in order to regular the voltage for injecting electric charges into the conductor. The present invention relates generally to satellites or unmanned aircrafts, and more particularly, to magnetic satellites or unmanned aircrafts.The present invention describes a magnetic satellite or unmanned ...

Подробнее

Номер записи: 91

07-01-2021 дата публикации

Method and Device of Path Optimization for UAV, and Storage Medium thereof

Номер: US20210003412A1

Автор: Deng Chang, Feng Zhiyong, Gao Hui, Xu Wenjun, Zhang Ping, Zhang Zhi

Принадлежит:

Disclosed is a method of path optimization for an unmanned aerial vehicle (UAV). In the method, users and the positions of the users are obtained; the users are divided into K wireless multicast user groups; K initial hovering positions corresponding to the K wireless multicast user groups are determined; and a first shortest flying path connecting the K initial hovering positions is determined; and the initial hovering positions of the UAV are optimized to obtain K final hovering positions and a final flying path. The present disclosure also discloses a device of path optimization for a UAV and a computer readable storage medium. 1. A method of path optimization for an unmanned aerial vehicle (UAV) , comprising:determining a number of wireless multicast user groups according to a number of users, a position of each user and a size of one or more files to be transmitted;dividing the users into a plurality of wireless multicast user groups according to the number of the wireless multicast user groups determined;determining a hovering position of the UAV corresponding to each wireless multicast user group;determining a first shortest flying path connecting all hovering positions of the UAV;determining a first total energy consumption of the UAV according to the size of the one or more files to be transmitted, the hovering positions of the UAV and the first shortest flying path of the UAV;optimizing the hovering positions of the UAV one by one to obtain a plurality of optimized hovering positions;determining a second shortest flying path connecting the plurality of optimized hovering positions;determining a second total energy consumption of the UAV according to the size of the one or more files to be transmitted, the optimized hovering positions of the UAV and the second shortest flying path;comparing the first total energy consumption with the second total energy consumption;on condition that the absolute value of the difference between the first total energy ...

Подробнее

Номер записи: 92

02-01-2020 дата публикации

Lidar system and autonomous driving system using the same

Номер: US20200003902A1

Автор: Jejong LEE

Принадлежит: LG ELECTRONICS INC

A lidar system includes: light sources generating light of a linear light source type; a light emission unit including a diffractive optical element disposed ahead of the light sources and separating incident light from the light sources into point light sources, and a scanner moving the light separated by the diffractive optical element, and radiating light of a point light source to an object; and a reception sensor converting light received after reflection by the object into an electrical signal. Spectrum angles of point light sources that have passed through the diffractive optical element may be different according to a position of the diffractive optical element. According to the lidar system, an autonomous vehicle, AI device, and/or external device may be linked with an artificial intelligence module, drone ((Unmanned Aerial Vehicle, UAV), robot, AR (Augmented Reality) device, VR (Virtual Reality) device, a device associated with 5G services, etc.

Подробнее

Номер записи: 93

03-01-2019 дата публикации

MAP REGISTRATION POINT COLLECTION WITH MOBILE DRONE

Номер: US20190003840A1

Автор: Song Xiufeng

Принадлежит:

Certain embodiments are described that provide a method for obtaining a registration point for a map. A drone is equipped with a GPS receiver and is flown to, and lands on, a physical location corresponding to a designated point on the map. While the drone is at the physical location, it receives GPS data using the GPS receiver for a period of time sufficient to allow convergence of the GPS data to obtain a GPS coordinate. The GPS coordinate is then associated with the designated point on the map, to generate the registration point for the map. 1. A method for obtaining a registration point for a map , comprising:providing a drone equipped with a GPS receiver;landing the drone at a physical location corresponding to a designated point on the map;while the drone is at the physical location, receiving GPS data using the GPS receiver for a period of time sufficient to allow convergence of the GPS data to a predetermined accuracy, to obtain a GPS coordinate; andassociating the GPS coordinate with the designated point on the map, to generate the registration point for the map.2. The method of claim 1 , further comprising:providing a camera on the drone;capturing an image using the camera; andusing the image captured by the camera as a factor in selecting the physical location.3. The method of wherein the step of using the image captured by the camera to select the physical location comprises:comparing the captured image to a portion of a previously obtained aerial image associated with the map; andin response to detecting a match between (a) the captured image and (b) the portion of the previously obtained aerial image, selecting a present location of the drone as the physical location and initiating the landing of the drone at the physical location.4. The method of further comprising:providing a camera on the drone;capturing a drone image using the camera;obtaining a map;using image matching to match to the drone image to a portion of the map to locate the registration ...

Подробнее

Номер записи: 94

04-01-2018 дата публикации

Unmanned Aerial Vehicle Weapon System and Method of Operation

Номер: US20180004203A1

Автор: Ryabov Artem

Принадлежит:

An unmanned aerial vehicle weapon system and method of operation which includes an unmanned aerial vehicle having navigational and weapon aiming cameras, remote controlled flight controls and a rifle type of weapon mounted in the wing transversely to the axis of the fuselage where the aerial vehicle is directed to a general target area and controlled to fly in a circular trajectory above and around a specific target within the target area until acquiring the target with the aiming camera and adjusting the bank angle of the vehicle to direct the weapon to the specific target. 1. A method of acquiring and destroying a target comprising the steps of;remotely control a weapon carrying unmanned aerial vehicle to a target area,identify a target within the target area,acquire the distance to the target and compute a circular trajectory of the unmanned aerial vehicle around the target,execute the computed circular trajectory around the target,remotely control the unmanned aerial vehicle to aim the weapon at the identified target along a radius of the circular trajectory.2. The method of and further including the step of claim 1 ,controlling the unmanned aircraft autonomously to maintain the target on sight throughout the circular trajectory.3. The method of and further including the step of claim 2 ,remotely controlling the firing of the weapon radially of the circular trajectory.4. An unmanned aerial vehicle weapon system comprising claim 2 ,an unmanned aerial vehicle including a fuselage having a longitudinal axis, power plant, flight controls and at least one rigid lifting surface structure,a wide-angle video camera, having a rangefinder, carried by the at least one rigid lifting surface structure,a telescopic aiming camera, having a rangefinder, carried by the at least one rigid lifting surface structure,a weapon having a barrel and carried within the at least one rigid lifting surface structure where the barrel is positioned and arranged perpendicularly to the ...

Подробнее

Номер записи: 95

04-01-2018 дата публикации

DYNAMICALLY ADJUSTING UAV FLIGHT OPERATIONS BASED ON RADIO FREQUENCY SIGNAL DATA

Номер: US20180004207A1

Автор: Blanc-Pâques Fabien, Cummings Logan, Michini Bernard J.

Принадлежит:

In some implementations, a UAV flight system can dynamically adjust UAV flight operations based on radio frequency (RF) signal data. For example, the flight system can determine an initial flight plan for inspecting a RF transmitter and configure a UAV to perform an aerial inspection of the RF transmitter. Once airborne, the UAV can collect RF signal data and the flight system can automatically adjust the flight plan to avoid RF signal interference and/or damage to the UAV based on the collected RF signal data. In some implementations, the UAV can collect RF signal data and generate a three-dimensional received signal strength map that describes the received signal strength at various locations within a volumetric area around the RF transmitter. In some implementations, the UAV can collect RF signal data and determine whether a RF signal transmitter is properly aligned. 1. A system comprising one or more processors , and a non-transitory computer-readable medium including one or more sequences of instructions that , when executed by the one or more processors , cause the system to perform the operations comprising:navigating an unmanned aerial vehicle (UAV);periodically monitoring radio frequency (RF) signals external to the UAV;determining a received signal strength indication (RSSI) value for the monitored RF signals at a plurality of geospatial locations during the navigation of the UAV; andstoring a plurality of RSSI values and the respective geospatial locations of where a corresponding value was monitored.2. The system of claim 1 , the operations further comprising:adjusting navigation of the UAV system to locations where the determined RSSI value of the monitored signals remains below a threshold RSSI value.3. The system of claim 1 , the operations further comprising:preventing navigation of the UAV to a position of a stored geospatial location based on the corresponding stored RSSI value.4. The system of claim 1 , the operations further comprising:obtaining ...

Подробнее

Номер записи: 96

04-01-2018 дата публикации

Dynamically adjusting uav flight operations based on thermal sensor data

Номер: US20180004231A1

Автор: Bernard J. Michini, Fabien Blanc-Paques

Принадлежит: Unmanned Innovation Inc (dba Airware)

In some implementations, a UAV flight system can dynamically adjust UAV flight operations based on thermal sensor data. For example, the flight system can determine an initial flight plan for inspecting a flare stack and configure a UAV to perform an aerial inspection of the flare stack. Once airborne, the UAV can collect thermal sensor data and the flight system can automatically adjust the flight plan to avoid thermal damage to the UAV based on the thermal sensor data.

Подробнее

Номер записи: 97

04-01-2018 дата публикации

CAMERA CONFIGURATION ON MOVABLE OBJECTS

Номер: US20180004232A1

Автор: TANG Ketan, ZHANG Honghui, Zhao Cong

Принадлежит:

Systems and methods for obstacle detection and state information determination are provided. In some embodiments, a movable object may carry one or more imaging devices. The imaging devices may be arranged on the movable object so as to have a field of view oriented vertically relative to the movable object. The arrangement of the imaging device may complement or supplant existing arrangement schemes and provide efficient, multi-functional and cost-effective means of arranging imaging devices on movable objects. 1. A method for using an imaging device carried by a movable object , the method comprising:receiving, at one or more processors, first image data from the imaging device carried by the movable object, wherein the imaging device is arranged on top of the movable object;generating, at the one or more processors, a control signal to control one or more propulsion units of the movable object to cause the movable object to move;receiving, at the one or more processors, second image data from the imaging device having the field of view oriented upward relative to the movable object after the movable object has moved;identifying, with aid of the one or more processors, a target based on the first image data and the second image data; anddetermining, with aid of the one or more processors, state information of the movable object or the target, based on the first image data and the second image data.2. The method of claim 1 , wherein the state information of the movable object is a position of the movable object.3. The method of claim 1 , wherein the state information of the movable object is a velocity of the movable object.4. The method of claim 1 , wherein the state information comprises details of the target.5. The method of claim 1 , wherein the imaging device is fixedly arranged with a principal axis parallel to a vertical axis of the movable object.6. The method of claim 1 , wherein the imaging device is coupled to the movable object via a coupling that ...

Подробнее

Номер записи: 98

02-01-2020 дата публикации

SYSTEM AND METHOD FOR CONTROLLER-FREE USER DRONE INTERACTION

Номер: US20200004236A1

Автор: Liu Lixin, Lu Jia, Wang Mengqiu, Zhang Tong

Принадлежит:

System and method for controlling an aerial system, without physical interaction with a separate remote device, based on sensed user expressions. User expressions may include thought, voice, facial expressions, and/gestures. User expressions may be sensed by sensors associated with the aerial device or a remote device. 1. An aerial system , comprising:a body;a lift mechanism coupled to the body;an optical system controllably mounted to the body by an actuation system; anda processing system coupled to the lift mechanism, the optical system, and the actuation system, the processing system configured to:recognize and track a target person,scan the target person for user expressions and compare against a set of predefined user expressions, each user expression in the set of user expressions having an associated type and an associated instruction, the type of each user expression being one of a first type and a second type;detect a first one of the predefined user expressions andif the type associated with the detected first one of the predefined user expressions is of the first type, execute the instruction associated with the first one of the predefined user expressions until a second one of the predefined user expressions is detected, andif the type associated with the detected first one of the predefined user expressions is of the second type: (1) initiate the instruction associated with the first one of the predefined user expressions, (2) continue to scan the target person for user expressions and (3) continue to execute the instructions associated with the first one of the predefined user expressions while the first one of the predefined user expressions is detected.2. An aerial system claim 1 , as set forth in claim 1 , further comprising a sensing system to sense user features and to send data related to the sensed user features to the processing system claim 1 , the processing system being configured to scan for user expressions as a function of the data ...

Подробнее

Номер записи: 99

02-01-2020 дата публикации

METHOD AND APPARATUS FOR CONTROLLING F CHANNEL

Номер: US20200004238A1

Автор: Chen Chaobin, Liu Qiming

Принадлежит:

The present disclosure provides an F channel control method. The method includes receiving a mapping signal; parsing an F channel identifier and a specified function from the mapping signal; and mapping the F channel corresponding to the F channel identifier to the specified function. 1. An F channel control method , comprising:receiving a mapping signal;parsing an F channel identifier and a specified function from the mapping signal; andmapping the F channel corresponding to the F channel identifier to the specified function.2. The method of claim 1 , wherein the specified function includes a signal output function outputting a specific type of signal.3. The method of claim 2 , further comprising:receiving a trigger signal, the trigger signal including the F channel identifier and a characteristic parameter of the specific type of signal; andoutputting the specific type of signal having the characteristic parameter through the F channel.4. The method of claim 2 , further comprising:receiving a trigger configuration signal, the trigger configuration signal including the F channel identifier, the characteristic parameter of the specific type of signal, and a parameter of the trigger signal, the parameter of the trigger signal describing the trigger signal, and the trigger signal triggering the F channel to output the specified type of signal having the characteristic parameter; andassociating the F channel corresponding to the F channel identifier, the specific type of signal having the characteristic parameter, and the parameter of the trigger signal.5. The method of claim 2 , further comprising:receiving a trigger signal;determining the specific type of signal having the characteristic parameter associated with a parameter of the trigger signal; andoutputting the specific type of signal through the F channel.6. The method of claim 3 , further comprising:determining that the trigger signal is from a designated device.7. The method of claim 1 , wherein the specified ...

Подробнее

Номер записи: 100