Настройки

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

Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Укажите год
Укажите год
Применить Всего найдено 781. Отображено 100.
11-02-2020 дата публикации

Воздушная аэродинамическая станция

Номер: RU0000195928U1
Автор: Владимир Анатольевич Петров
Принадлежит: Владимир Анатольевич Петров

Полезная модель относится к области воздухоплавания, а именно к летательным аппаратам, барражирующим в течение длительного времени в пределах заданного района. Техническим результатом является повышение надежности работы всей системы или станции путем придания автономии летательному аппарату на время, необходимое для его приземления в случае возникновения неисправности в системе топливоподачи, а также на время автономной работы аппарата без подачи топлива с земли. Поставленная задача достигается тем, что воздушная аэродинамическая станция, содержит летающую платформу с движителями, приводимыми энергией, вырабатываемой преобразователем, работающим на жидком топливе, а также наземный пункт подачи жидкого топлива, связанный с летающей платформой, по меньшей мере, при помощи гибкого топливопровода. При этом наземный пункт снабжен насосом подачи топлива через топливопровод к летающей платформе. Согласно полезной модели, на платформе установлен редуцирующий топливный бачок с аварийным запасом топлива, из которого топливо подается к преобразователю. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 195 928 U1 (51) МПК B64C 39/02 (2006.01) B64F 3/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК B64C 2201/00 (2019.08); B64F 3/00 (2019.08) (21)(22) Заявка: 2019126409, 21.08.2019 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): Петров Владимир Анатольевич (RU) Дата регистрации: 11.02.2020 Приоритет(ы): (22) Дата подачи заявки: 21.08.2019 (45) Опубликовано: 11.02.2020 Бюл. № 5 1 9 5 9 2 8 R U (54) ВОЗДУШНАЯ АЭРОДИНАМИЧЕСКАЯ СТАНЦИЯ (57) Реферат: Полезная модель относится к области аэродинамическая станция, содержит летающую воздухоплавания, а именно к летательным платформу с движителями, приводимыми аппаратам, барражирующим в течение энергией, вырабатываемой преобразователем, длительного времени в пределах заданного работающим на жидком топливе, а также района. Техническим результатом является ...

Подробнее
Номер записи: 1
19-04-2012 дата публикации

System, floating unit and method for elevating payloads

Номер: US20120091258A1
Автор: Ronen Keidar, Shay Cohen
Принадлежит: SKY SAPIENCE LTD

A method, system and a floating unit. The floating unit includes a propeller, a frame, a propeller motor that is configured to rotate the propeller about a first axis; wherein the propeller motor is coupled to the frame, a movable steering element; a controller, for controlling at least one of the propeller motor and the movable steering unit to affect at least one of a location and an orientation of the floating unit; and an interfacing module for coupling a payload to the floating unit and for receiving power from a connecting element that couples the floating unit to a ground unit; wherein the power received by the power interface is utilized to power the propeller motor and the controller.

Подробнее
Номер записи: 2
13-02-2014 дата публикации

SYSTEMS AND METHODS FOR CONTROLLING AN AERIAL UNIT

Номер: US20140046504A1
Автор: Cohen Shy, Keidar Ronen, Shachor Gabriel
Принадлежит:

An aerial unit, a method and a system are provide, the system includes a ground unit; an aerial unit and a connecting element arranged to connect the ground unit to the aerial unit. The ground unit may include a connecting element manipulator, a ground unit controller for controlling the connecting element manipulator; and a ground unit location sensor arranged to generate ground unit location information indicative of a location of the ground unit. The wherein the aerial unit may include a first propeller, a frame, a first propeller motor, at least one steering element; and an aerial unit location sensor arranged to generate aerial unit location information indicative of a location of the aerial unit. At least one of the ground unit and the aerial unit includes a controller that is arranged to control, at least in response to a relationship between the aerial unit location information and the ground unit location information, at least one of the first propeller motor and the at least one steering element to affect at least one of the location of the aerial unit and an orientation of the aerial unit. 1. A system , comprising:a ground unit;an aerial unit; anda connecting element arranged to connect the ground unit to the aerial unit; a connecting element manipulator, for altering an effective length of the connecting element; wherein the effective length of the connecting element defines a distance between the ground unit and the aerial unit;', 'a ground unit controller for controlling the connecting element manipulator; and', 'a ground unit location sensor arranged to generate ground unit location information indicative of a location of the ground unit;, 'wherein the ground unit comprises a first propeller;', 'a frame;', 'a first propeller motor that is configured to rotate the first propeller about a first axis, wherein the first propeller motor is connected to the frame;', 'at least one steering element; and', 'an aerial unit location sensor arranged to generate ...

Подробнее
Номер записи: 3
06-01-2022 дата публикации

HYBRID TRANSPORTATION

Номер: US20220002000A1
Автор: Uskolovsky Alexander
Принадлежит:

Provided is a transportation system comprising a hybrid vehicle that is propelled on a highway by a linear induction electric motor comprising a stationary motor element (“stator”) and a moving motor element (“rotor”), where the stator is incorporated into a groove in the highway and the rotor is incorporated into the hybrid vehicle and protrudes into the groove in the highway; and where the hybrid vehicle further comprises at least one wing that elevates the hybrid vehicle when propelled to a take-off speed on the highway. Methods of transportation utilizing this hybrid vehicle transportation system are further provided. 1. A transportation system comprising a hybrid vehicle that is propelled on a highway by a linear induction motor comprising a stationary motor element (“stator”) and a moving motor element (“rotor”) , wherein the stator is incorporated into a groove in the highway and the rotor is incorporated into the hybrid vehicle and protrudes into the groove in the highway; wherein the hybrid vehicle further comprises at least one wing that elevates the hybrid vehicle when propelled to a take-off speed on the highway.2. The transportation system of claim 1 , wherein a groove part is the same width and/or the groove top is wider than the groove bottom.3. A method of transportation claim 1 , the method utilizing the transportation system of claim 1 , the method comprising(a) engaging the linear induction motor, wherein magnetic induction in the rotor causes its propulsion causing the hybrid vehicle to begin accelerating up to a take-off speed and to become elevated by interaction of the at least one wing with air,(b) the elevation causes the rotor to elevate up from the stator bottom in the groove, increasing the gap between the rotor and the stator and the reducing the magnetic flux thru the rotor and hence magnetic induction,(c) the reduction of magnetic induction and hence propulsion causes the hybrid vehicle to slow down and lower, thus reducing the ...

Подробнее
Номер записи: 4
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: 5
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: 6
12-01-2017 дата публикации

Spooler for unmanned aerial vehicle system

Номер: US20170008626A1
Автор: Andrew M. Shein, Jason S. Walker, John W. Ware, Samuel A. Johnson
Принадлежит: CyPhy Works Inc

In an aspect, in general, a spooling apparatus includes a filament feeding mechanism for deploying and retracting filament from the spooling apparatus to an aerial vehicle, an exit geometry sensor for sensing an exit geometry of the filament from the spooling apparatus, and a controller for controlling the feeding mechanism to feed and retract the filament based on the exit geometry.

Подробнее
Номер записи: 7
27-01-2022 дата публикации

RAPID AIRCRAFT INSPECTION WITH AUTONOMOUS DRONE BASE STATION SYSTEMS

Номер: US20220024577A1
Автор: Stamatovski Ivan
Принадлежит:

A system for inspecting an aircraft includes a drone, a base station, and a controller. The drone includes one or more cameras. The base station has a storage compartment configured to store the autonomous drone therein. The controller has a processor and a memory. The memory has instructions stored thereon, which when executed by the processor, cause the base station to drive to a first predetermined location relative to the aircraft, and cause the drone to fly from the storage compartment of the base station to a first predetermined position relative to the aircraft so that the drone can record image data of at least portions of the aircraft with the one or more cameras. 1. A system for inspecting an aircraft , the system comprising:an autonomous drone including at least one camera;a base station having a storage compartment configured to store the autonomous drone therein; drive to a first predetermined location relative to the aircraft; and', 'open the storage compartment;, 'a base station controller having a base station processor and a base station memory, the base station memory having instructions stored thereon, which when executed by the base station processor, cause the base station to'}and determine that the storage compartment of the base station is open;', 'take flight from the base station when the storage compartment is open;', 'fly to a first predetermined position relative to the aircraft; and', 'record image data of at least portions of the aircraft with the at least one camera., 'a drone controller having a drone processor and a drone memory, the drone memory having instructions stored thereon, which when executed by the drone processor, cause the autonomous drone to2. The system of claim 1 , wherein the base station includes at least one door that provides access to the storage location.3. The system of claim 2 , wherein the at least one door opens upwardly and outwardly to expose the storage compartment.4. The system of claim 1 , wherein claim ...

Подробнее
Номер записи: 8
27-01-2022 дата публикации

TETHER CONTROLLED DRONE

Номер: US20220024583A1
Автор: Barawkar Shraddha, Cohen Kelly, Kumar Manish
Принадлежит:

Systems, methods, and computer program products for controlling a drone using a tether. A drone is coupled to a distal end of the tether, and a force sensor measures one or more force parameters exerted on the drone by the tether. The force parameters are in turn used to generate control parameters, and the control parameters provided to a flight controller. The flight controller generates one or more propulsion parameters based on the control parameters, and provides the propulsion parameters to respective propulsion units of the drone. The drone can thereby be controlled by manipulating a proximate end of the tether, which changes the force parameters measured by the force sensor. 1. A system for controlling a drone , comprising:a tether having a proximal end and a distal end operatively coupled to the drone;a force sensor that measures a force parameter exerted on the drone by the tether;one or more processors; and receive a signal from the force sensor indicative of the force parameter; and', 'control at least one of an attitude and a position of the drone based at least in part on the force parameter., 'a memory coupled to the one or more processors and including program code that, when executed by the one or more processors, causes the one or more processors to2. The system of claim 1 , wherein the program code causes the one or more processors to control the at least one of the attitude and the position of the drone by:generating a control parameter based at least in part on the force parameter; andproviding the control parameter to a flight control module.3. The system of claim 2 , wherein the control parameter is a one of a roll angle claim 2 , a roll rate claim 2 , a pitch angle claim 2 , a pitch rate claim 2 , a yaw angle claim 2 , a yaw rate claim 2 , and an amount of thrust.4. The system of claim 3 , further comprising:a propulsion unit,wherein the flight control module generates a propulsion parameter based on the control parameter, and provides the ...

Подробнее
Номер записи: 9
11-01-2018 дата публикации

SYSTEM AND METHOD FOR ESTABLISHING A WIRELESS CONNECTION USING A SELF-POSITIONABLE WIRELESS DEVICE

Номер: US20180009526A1
Автор: EKL RANDY L., GRIESMANN DANIEL S., PROCTOR LEE M., Spengler Charles E.
Принадлежит:

A system and method for a providing a dynamic backhaul. In one example, the system includes a self-positionable wireless device (for example, a drone) including a dual-band radio configured to establish a wireless connection between the self-positionable wireless device and a wireless system. The dual-band radio initiates a narrowband wireless link with the wireless system via a first narrowband antenna of the self-positionable wireless device and a second narrowband antenna of the wireless system. A navigation system generates location, velocity and error estimate of the self-positionable wireless device. The location is transmitted to the wireless system using the narrowband wireless link. The self-positionable wireless device receives via the narrowband wireless link location, velocity and error estimate of the wireless system. The self-positionable wireless device establishes a directional broadband wireless link with the wireless system using the location, velocity and error estimate of the self-positionable wireless system and the wireless system. 1. A method of establishing a wireless connection between a self-positionable wireless device and a wireless system , the method comprising:establishing with the self-positionable wireless device, a narrowband wireless link via a first narrowband antenna of the self-positionable wireless device and a second narrowband antenna of the wireless system;generating with the self-positionable wireless device, a first location, a first velocity and a first error estimate of the self-positionable wireless device via a navigation system of the self-positionable wireless device;transmitting with the self-positionable wireless device, the first location, the first velocity and the first error estimate to the wireless system using the narrowband wireless link;receiving via the narrowband wireless link with the wireless system, a second location, a second velocity and a second error estimate of the wireless system; andestablishing ...

Подробнее
Номер записи: 10
11-01-2018 дата публикации

SYSTEMS FOR TRANSPORTING, DEPLOYING, AND DOCKING UNMANNED AERIAL VEHICLES MOUNTABLE ON A GROUND VEHICLE

Номер: US20180009549A1
Автор: PROKHOROV Danil V., Sullivan Richard M., Williams Paxton S.
Принадлежит:

A housing for a ground vehicle-mountable aerial vehicle is provided. The housing includes a base portion defining a cavity and an opening leading into the cavity. The cavity is structured to receive an unmanned aerial vehicle therein. The cavity is configured so as to open upwardly when the housing is mounted on the vehicle. The housing also includes a drafting wall structured to extend from the base portion at a location forward of at least a portion of the cavity when the housing is mounted on the ground vehicle. 1. A housing for an unmanned aerial vehicle , the housing comprising:a base portion defining a cavity and an opening leading into the cavity, the cavity being structured to receive an unmanned aerial vehicle therein, the cavity being configured so as to open upwardly when the housing is mounted on a ground vehicle; anda drafting wall structured to extend from the base portion at a location forward of at least a portion of the cavity when the housing is mounted on the ground vehicle.2. The housing of further comprising an unmanned aerial vehicle catcher assembly positioned between the drafting wall and the cavity.3. The housing of wherein the catcher assembly includes a first post mounted along a first side of the housing claim 2 , a second post mounted along a second side of the housing opposite the first side claim 2 , and a catching member suspendable between the first and second posts.4. The housing of wherein the first and second posts are extendable from and retractable into the housing.5. The housing of wherein the cavity has a dimension which narrows when proceeding from an exterior of the housing through the opening in a direction toward the base portion.6. The housing of further comprising an electromagnet positioned in the base portion.7. The housing of further comprising a charging mechanism for charging an unmanned aerial vehicle power source.8. The housing of wherein the charging mechanism comprises an induction coil.9. The housing of wherein ...

Подробнее
Номер записи: 11
09-01-2020 дата публикации

INFORMATION PROCESSING METHOD, CONTROL DEVICE, AND MOBILE TETHERING BODY

Номер: US20200010190A1
Автор: ASAI KATSUHIKO, INOUE KAZUO, JOHN Stephen William, KONISHI Kazunobu
Принадлежит:

An information processing method includes the following steps performed using a processor: obtaining first region information indicating a first region; obtaining first position information indicating the position of an unmanned aerial vehicle tethered to a mobile tethering body using a tether; determining, using the first region information and the first position information, a first destination which is a destination of the mobile tethering body; and moving the mobile tethering body to the first destination. The first destination is a position located at least a predetermined distance from a point which is on the boundary of the first region and located the shortest distance from the position of the unmanned aerial vehicle, in the direction from the point on the boundary of the first region to the position of the unmanned aerial vehicle. 1. An information processing method , comprising the following steps performed using a processor:obtaining first region information indicating a first region;obtaining first position information indicating a position of an unmanned aerial vehicle tethered to a mobile tethering body using a tether;determining a first destination using the first region information and the first position information, the first destination being a destination of the mobile tethering body; andmoving the mobile tethering body to the first destination, whereinthe first destination is a position located at least a predetermined distance from a point on a boundary of the first region in a direction from the point on the boundary of the first region to the position of the unmanned aerial vehicle, the point being located a shortest distance from the position of the unmanned aerial vehicle.2. The information processing method according to claim 1 , whereinthe first position information indicates a second destination as the position of the unmanned aerial vehicle, the second destination being a destination of the unmanned aerial vehicle, andthe information ...

Подробнее
Номер записи: 12
09-01-2020 дата публикации

CONTROL DEVICE, INFORMATION PROCESSING METHOD, AND TETHERING DEVICE

Номер: US20200010191A1
Автор: ASAI KATSUHIKO, INOUE KAZUO, JOHN Stephen William, KONISHI Kazunobu
Принадлежит:

A control device includes a processor which: obtains first region information indicating a first region; obtains first position information indicating the position of an unmanned aerial vehicle tethered to a tethering device using a tether; and controls the tethering device using the first region information and the first position information to cause the tether to have tension corresponding to a specified distance which is at least one of the shortest distance between a boundary of the first region and the position of the unmanned aerial vehicle and a distance included in a predetermined range from the shortest distance. 1. A control device , comprising a processor which is configured to:obtain first region information indicating a first region;obtain first position information indicating a position of an unmanned aerial vehicle tethered to a tethering device using a tether; andcontrol the tethering device using the first region information and the first position information to cause the tether to have tension corresponding to a specified distance which is at least one of a shortest distance between a boundary of the first region and the position of the unmanned aerial vehicle and a distance included in a predetermined range from the shortest distance.2. The control device according to claim 1 , whereinthe processor controls the tethering device to increase the tension of the tether as the specified distance decreases.3. The control device according to claim 2 , whereinthe processor controls the tethering device to cause the tension of the tether to increase as the specified distance decreases when the specified distance is less than a first threshold value, and cause the tension of the tether to be constant when the specified distance is greater than or equal to the first threshold value.4. The control device according to claim 2 , whereinthe processor controls the tethering device to cause the tension of the tether to be greater than a propulsive force of the ...

Подробнее
Номер записи: 13
14-01-2016 дата публикации

Methods and Systems for Determining a Priority Sequence for Changing a Position or an Attitude of an Aircraft in Hover Flight

Номер: US20160011600A1
Автор: Chubb Erik Christopher, Hachtmann Brian, Vander Lind Damon
Принадлежит: GOOGLE INC.

An example method may include receiving data representing an initial position and an initial attitude of an aircraft. The method further includes determining a change to a first attribute and a second attribute of the position or the attitude of the aircraft to achieve a subsequent position and a subsequent attitude. The method also includes determining a priority sequence for changing the first attribute and the second attribute of the position or the attitude of the aircraft based on a first thrust of the actuator to achieve the change to the first attribute and a second thrust of the actuator to achieve the change to the second attribute. The priority sequence is configured to cause changes to the first attribute before causing changes to the second attribute where the actuator is unable to concurrently provide the first thrust and the second thrust. 1. A method comprising:receiving data representing an initial position and an initial attitude of an aircraft configured to be coupled to a ground station via a tether, wherein the aircraft includes an actuator configured to change a position and an attitude of the aircraft;determining a change to a first attribute and a second attribute of the position or the attitude of the aircraft to achieve a subsequent position and a subsequent attitude;determining a priority sequence for changing the first attribute and the second attribute of the position or the attitude of the aircraft based on a first thrust of the actuator to achieve the change to the first attribute and a second thrust of the actuator to achieve the change to the second attribute, wherein the priority sequence is configured to cause changes to the first attribute before causing changes to the second attribute where the actuator is unable to concurrently provide the first thrust and the second thrust; andcausing the actuator to change the first attribute and the second attribute according to the priority sequence.2. The method of claim 1 , wherein ...

Подробнее
Номер записи: 14
09-01-2020 дата публикации

Navigation Using Self-Describing Fiducials

Номер: US20200012829A1
Автор: Christensen Randall S., Davidson Morgan E., Robinson Richard C.
Принадлежит: Canyon Navigation, LLC

In one embodiment, a self-describing fiducial includes a communication element that optically communicates navigation-aiding information. The navigation-aiding information may include a position of the self-describing fiducial with respect to one or more coordinate systems and the communication element communicates the navigation-aiding information to one or more navigating objects in the vicinity of the self-describing fiducial. In another embodiment, the communication element is further configured to communicate supplementary information describing a spatial relationship between the self-describing fiducial and the surrounding environment. 1. A self-describing fiducial comprising:a communication element that is configured to optically communicate navigation state estimation aiding information to one or more navigating objects in the vicinity of the self-describing fiducial, wherein the navigation-aiding information comprises a geographic position of the self-describing fiducial with respect to one or more coordinate systems; andthe communication element is further configured to communicate supplementary information describing a spatial relationship between the self-describing fiducial and the surrounding environment, wherein the supplementary information comprises at least one of: additional navigation-aiding information and guidance-aiding information.2. The fiducial of claim 1 , wherein the position comprises a three dimensional position.3. The fiducial of claim 1 , wherein the supplementary information comprises an external directionality of a feature of the self-describing fiducial.4. The fiducial of claim 1 , wherein the supplementary information comprises attitude of the self-describing fiducial with respect to one or more coordinate systems claim 1 , wherein the attitude information comprises at least one of: cardinal directions claim 1 , compass heading claim 1 , true north claim 1 , magnetic north claim 1 , path direction claim 1 , zenith directionality ...

Подробнее
Номер записи: 15
03-02-2022 дата публикации

Hybrid unmanned aerial vehicle systems with quick release tether assembly

Номер: US20220033078A1
Автор: Ido Gur, Jason Felder, Omri Dayan
Принадлежит: Easy Aerial Inc

An unmanned aerial vehicle system includes a ground station, a tether assembly coupled to the ground station, and an unmanned aerial vehicle. The unmanned aerial vehicle having a quick release mechanism selectively coupled to the tether assembly to restrain movement of the unmanned aerial vehicle. The quick release mechanism is electrically actuatable to decouple the tether assembly from the unmanned aerial vehicle for enabling the unmanned aerial vehicle to fly freely.

Подробнее
Номер записи: 16
21-01-2021 дата публикации

STABILITY SYSTEMS FOR TETHERED UNMANNED AERIAL VEHICLES

Номер: US20210016881A1
Автор: Blavier Mike, Buyse Mathieu, Coulon Jean Marc
Принадлежит:

An unmanned aerial vehicle including a body, a platform, a rotor, a tether cable, and an actuation system. The platform is coupled to the body such that the platform is rotatable relative to the body about a first horizontal axis of rotation. The rotor is rigidly coupled to the platform such that the rotor and the platform rotate together about the first horizontal axis of rotation. The tether cable extends away from the body and is coupled to the body such that the tether cable is rotatable relative to the body about a second horizontal axis of rotation. The first and second horizontal axes of rotation are normal to a vertical plane. The actuation system is configured to rotate the platform in a clockwise direction about the first horizontal axis of rotation when the tether cable rotates in a counter-clockwise direction about the second horizontal axis of rotation. 1. An unmanned aerial vehicle comprising:a body;a platform coupled to the body such that the platform is rotatable relative to the body about a first horizontal axis of rotation normal to a vertical plane extending through the body;a rotor rigidly coupled to the platform such that the rotor and the platform rotate together about the first horizontal axis of rotation;a tether cable extending away from the body and coupled to the body such that the tether cable is rotatable relative to the body about a second horizontal axis of rotation normal to the vertical plane; andan actuation system configured to rotate the platform in a clockwise direction about the first horizontal axis of rotation when the tether cable rotates in a counter-clockwise direction about the second horizontal axis of rotation.2. The unmanned aerial vehicle of claim 1 , wherein the vertical plane is a first vertical plane claim 1 , wherein the platform coupled to the body such that the platform is rotatable relative to the body about a third horizontal axis of rotation normal to a second vertical plane claim 1 , wherein the second ...

Подробнее
Номер записи: 17
28-01-2016 дата публикации

FLAT-STOCK AERIAL VEHICLES AND METHODS OF USE

Номер: US20160023743A1
Автор: Barrett Ronald M., Bramlette Richard B., Honea Robert B.
Принадлежит:

A flat-stock aerial vehicle includes a body having a plurality of flat-stock sheets connected to one another, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. The aerodynamic propulsors can provide lifting thrust, pitch, yaw, and roll control in both helicopter-like hover flight and airplane-like translational flight. 1. A flat-stock aerial vehicle comprising: a first flat-stock sheet having a first forward edge and a first aft edge and having an aft slot therein extending forward from the first aft edge, and', 'a second flat-stock sheet having a second forward edge and a second aft edge and having a forward slot therein extending aft from the second forward edge, wherein the aft slot is configured to engage with the forward slot;, 'a body having a forward body edge, an aft body edge, and a longitudinal axis, the body includingat least one motor; andat least three aerodynamic propulsors positioned between the forward body edge and aft body edge, the at least three aerodynamic propulsors defining a forward wing portion and an aft wing portion, the at least three aerodynamic propulsors driven by the at least one motor, the at least three aerodynamic propulsors being configured to provide lifting thrust, pitch, yaw, and roll control to the vehicle.2. The flat-stock aerial vehicle of claim 1 , wherein at least a portion of the body is made from flat-stock which is planar or possesses simple curves.3. The flat-stock aerial vehicle of claim 1 , wherein at least a portion of the body is made from laminated flat-stock which is planar or possesses simple curves.4. The flat-stock aerial vehicle of claim 1 , wherein the body has at least one cutout to accommodate electronics claim 1 , motors claim 1 , propellers claim 1 , landing gear claim 1 , or lights.5. The flat-stock aerial vehicle of claim 1 , further comprising removable landing gear which extend laterally beyond the radial outermost position of the at least three ...

Подробнее
Номер записи: 18
25-01-2018 дата публикации

UNMANNED FLUID-PROPELLED AERIAL VEHICLE

Номер: US20180022423A1
Автор: Demas Peter J., Low Nathan E.
Принадлежит:

A water-propelled or water-powered unmanned aerial vehicle including a base configured to carry a payload, and at least one nozzle attached thereto. The at least one nozzle is configured to selectively receive pressurized fluid from a source located remotely from the vehicle. The vehicle includes a control system configured to alter or otherwise selectively dictate the flow of fluid through the at least one nozzle and/or the orientation of the at least one nozzle with respect to the base in response to a received control signal for providing controlled unmanned vehicle flight. 1. A water-propelled unmanned aerial vehicle comprising:a base configured to carry a payload enclosed therein, the base having an input for receiving pressurized water from a source located remotely from the vehicle;a plurality of nozzles in fluid communication with the input, each of the plurality of nozzles attached to the base in a predetermined fixed orientation and configured to selectively receive and expel pressurized water from the source located remotely from the vehicle; anda control system configured to alter the flow of water through the plurality of nozzles in response to a received control signal to provide controlled flight of the vehicle.2. The aerial vehicle of claim 1 , wherein the plurality of nozzles comprise:a first plurality of nozzles fixedly attached and arranged radially about the base; anda horizontal thrust nozzle fixedly attached to the base and oriented so as to expel pressurized water in a direction generally horizontally with respect to the base.3. The aerial vehicle of claim 1 , further comprising an electrical generator configured to be driven by said pressurized water and operatively connected to the control system for supplying electrical power thereto.4. The aerial vehicle of claim 1 , wherein at least two of the plurality nozzles are fixedly attached to the base in at least partially opposing orientations such that force vectors generated from pressurized ...

Подробнее
Номер записи: 19
10-02-2022 дата публикации

GASEOUS MATTER CAPTURE SYSTEM AND METHOD

Номер: US20220041282A1
Автор: OREN Eran
Принадлежит:

A gaseous matter capture system and method comprising an aerial unit configured to capture gaseous matter directly from the atmosphere and further comprising storage means configured to transfer said gaseous matter for further processing in a non-aerial unit for the purposes of climate change mitigation and further use of captured gases. 1. A gaseous matter capture system , comprising:(i) at least one aerial unit configured to be airborne;(ii) at least one non-aerial unit;(iii) at least one gas separation means configured to be carried by the aerial unit;(iv) storage means configured to be carried by the aerial unit;(v) a controller configured to control the system's operation; and(vi) an energy source configured to enable the system's operation,wherein the at least one gas separation means is configured to separate at least one designated gaseous matter from the air,wherein the at least one separated gaseous matter is configured to be stored within the storage means, andwherein the aerial unit is configured to transfer the stored separated gaseous matter to the non-aerial unit.2. The system of claim 1 , wherein the at least one gas separation means is operable while the aerial unit is airborne at an altitude range of 5-15 km.3. The system of claim 1 , wherein the gas separation means comprises at least one pressure increasing apparatus.4. The system of claim 1 , wherein the gas separation means comprises chemical/biological catalysts configured to utilize gas separation procedure.58-. (canceled)9. The system of claim 1 , wherein the aerial unit further comprises self-steering means.10. The system of claim 1 , wherein the aerial unit is configured to be retrofitted to an aerial vehicle or integrated into the propulsion means of an aerial vehicle.11. (canceled)12. The system of claim 1 , wherein the storage means is at least one compressed gas container and wherein the system comprises guidance means configured to guide the at least one compressed gas container from ...

Подробнее
Номер записи: 20
24-01-2019 дата публикации

UAV Anchoring System

Номер: US20190023394A1
Автор: Ranaivoson Toky Ranaivoson
Принадлежит:

The UAV Anchor System is an anchoring system used to anchor a UAV to the ground. This system is primarily for beginners who has little to no experience in flying UAVs. The system anchor's the UAV to the ground which prevents the UAV to fly away and crash from a high altitude and also prevent from flying into objects, obstruction, people, traffic, etc. With this system, the user can safely practice with the flying exercises as per instructed in the manual. Once the user properly learns the mechanism of the UAV, the user can take off the anchor system and fly the UAV freely. 1. The eyelet anchor on the UAV is used to anchor the UAV to the ground. It is comprised of an eyelet anchor that's attached to the UAV , a carabiner clip , a double looped rope and an eyelet stake.2. The anchoring system is primarily for beginners who are new to flying UAVs. This includes the commercial industry where employees are required to fly a UAV. Anchoring the UAV will allow the user to safely fly an UAV and not have the UAV fly away rapidly and crash from a high altitude and also to prevent the UAV from hitting any type of obstruction including nearby people. Thus , this system will allow the user to learn quicker or for intermediate to expert flyers , this anchoring system can be used to better learn how to safely fly a UVA in any type of undesirable weather such as high winds.3. This system can also benefit expert flyers as they will usually not allow a beginner to fly their UAVs as they will fear crashing and damaging of their UAV.4. Parents can also greatly benefit from this system and they can anchor the UAV to the ground and leave their children unsupervised with the peace of mind that they will not fly the UAV into other people , objects , traffic , or people's property etc.5. This system is also beneficiary as users do not have to travel to a large field to fly their UAV. They can anchor their UAV's in their backyards , front yards , the closest public park or any small area ...

Подробнее
Номер записи: 21
26-01-2017 дата публикации

DEPLOYABLE AIRBORNE SENSOR ARRAY SYSTEM AND METHOD OF USE

Номер: US20170024854A1
Автор: Humfeld Keith Daniel
Принадлежит:

A deployable airborne sensor array system and method of use are provided herein. The system includes a tether configured to be coupled to and deployed from an aircraft and a plurality of airborne vehicles coupled to the tether. Each of the plurality of airborne vehicles includes different lift characteristics to form a three-dimensional (3D) array of airborne vehicles. Each airborne vehicle includes a sensing device configured to generate sensor data associated with a target. The system also include a computing device configured to process the sensor data received from each of said plurality of airborne vehicles and generate an image of the target based on the sensor data. 1. A deployable airborne sensor array system comprising:a tether configured to be coupled to and deployed from an aircraft;a plurality of airborne vehicles coupled to said tether, each of said plurality of airborne vehicles having different lift characteristics to form a three-dimensional (3D) array of airborne vehicles, each airborne vehicle comprising a sensor device configured to generate sensor data associated with a target; anda computing device configured to:process the sensor data received from each of said plurality of airborne vehicles; andgenerate an image of the target based on the sensor data.2. The system of claim 1 , wherein said tether comprises a tether network having a plurality of tethers coupling together one or more of said plurality of airborne vehicles.3. The system of claim 1 , wherein said different lift characteristics include unbalanced wings on at least first and second airborne vehicles that cause the first and second airborne vehicles to respectively glide to the left and to the right of the aircraft claim 1 , and further include a positive lift profile and negative lift profile on at least third and fourth airborne vehicles that cause the third and fourth airborne vehicles to respectively glide above and below the aircraft claim 1 , such that the plurality of airborne ...

Подробнее
Номер записи: 22
23-01-2020 дата публикации

SYSTEMS AND METHODS FOR ATTITUDE CONTROL OF TETHERED AEROSTATS

Номер: US20200024000A1
Автор: Glass Benjamin William, Goessling Andrew D., Vermillion Christopher R.
Принадлежит:

A control system for a tethered aerostat is provided, where at least one rotational and at least one translational degree of freedom are controlled to setpoints through the variation of tether lengths by an actuator system. The term tether includes a single tether, a tether group or a sub section of tether controlled by an individual actuator. Accurate rotational and translational control is essential for the successful operation of an aerostat under several applications, including surveillance, weather monitoring, communications, and power generation. For a given use case, the controller can be constructed and arranged to manage the tradeoff between several key performance characteristics, such as transient performance, steady-state pointing accuracy, tether tension regulation, and power generation. 1. A system for controlling a tethered aerostat , the system comprising:a base station including an actuation platform having an actuator system that is secured to the tethered aerostat via a plurality of tethers;the actuation platform having at least two actuators that each respectively control a control variable of at least some of the plurality of tethers; anda control unit that provides input to at least one of the at least two actuators to control a control variable of the controlled tethers.2. The system as set forth in wherein the control variable is tether payout length.3. The system as set forth in wherein the control variable is tether release speed.4. The system as set forth in wherein the control variable is tether acceleration.5. The system as set forth in wherein the control variable is tether tension.6. A system for controlling a tethered aerostat claim 1 , the system comprising:a base station including an actuation platform having an actuator system that is secured to the tethered aerostat via a plurality of tethers;the actuation platform having at least two actuators that each respectively control a control variable of at least some of the plurality of ...

Подробнее
Номер записи: 23
28-01-2021 дата публикации

TETHERED AERIAL VEHICLE

Номер: US20210024209A1
Автор: COSTA Lenardo Vieira, CRUZ Alejandro Arturo Rios, DE AZEVEDO Bruno Avena, DE CASTRO Davi Ferreira, DE MESQUITA Davi Lima, GARCIA Michelle Bueno, NETO Isamel Costa, NOGUEIRA Leonardo, RIBEIRO Raphael Galate Baptista, VIEIRA Waldir
Принадлежит:

A tethered aerial vehicle, connected to an anchorage system in the ground level through a cord, comprising a pair of fixed wings; and a drive assembly. The drive assembly comprises actuators configured to tilt the propeller's axle. The fixed wings define a center hole located close to a gravitational center of the aerial vehicle. Within the edges of the center hole located close to the gravitational center of the aerial vehicle is a gimbal anchored to the fixed wings structure. The drive assembly is located within the edges of the center hole and attached to the gimbal in a manner that the gimbal interfaces the connection between the fixed wings and the drive assembly. The drive assembly consists of coaxial propellers mounted on the same axle driven by a counterrotating motor. The coaxial propellers are configured to rotate in opposite directions with respect to each other. 1. A tethered aerial vehicle , connected to an anchorage system in the ground level through a cord , the aerial vehicle comprising:a pair of fixed wings; and "at least two actuators configured to tilt the propeller's axle in at least four directions,", 'a drive assembly, the drive assembly comprises the fixed wings define a center hole located close to a gravitational center of the aerial vehicle;', 'within the edges of the center hole located close to the gravitational center of the aerial vehicle there is a gimbal anchored to the fixed wings structure at the inner margin of the center hole;', 'the drive assembly is located within the edges of the center hole;', 'the drive assembly is attached to the gimbal in a manner that the gimbal interfaces the connection between the fixed wings and the drive assembly, providing several degrees of angular freedom between the drive assembly and the fixed wings;', 'the drive assembly consists of at least two coaxial propellers mounted on the same axle driven by a counterrotating motor; and', 'the coaxial propellers are configured to rotate in opposite ...

Подробнее
Номер записи: 24
28-01-2021 дата публикации

DRONE MOUNTED WIND TURBINE-GENERATOR SYSTEM

Номер: US20210025367A1
Автор: SIA Yik Hei
Принадлежит:

An airborne wind turbine system for generation of power via windbags and waterbags. 1620d. An ocean water power-generator apparatus () for the generation of renewable energy comprising:{'b': 25', '640', '640', '641', '642, 'i': ax', 't', 'b, 'an inlet port assembly () comprising a top horizontal beam (), a bottom horizontal beam (), and movable arms (, ) attached to the top horizontal beam and the bottom horizontal beam and configured to allow movement of the top horizontal beam and the bottom horizontal beam into an open and closed configuration;'}{'b': '612', 'a plurality of diversion ports () at an end of the inlet port assembly;'}{'b': '611', 'a plurality of turbine generators () connected to the diversion ports;'}{'b': '614', 'an outlet port () at an end of the turbine generators; and'}{'b': 650', '660, 'an anchoring assembly (, ) connected at a first end to the inlet port assembly and anchored at a second end to a seafloor;'}wherein the apparatus is configured to collect ocean water through the inlet port and flow the ocean water through the diversion ports and force the ocean water through the turbine generators and then release the ocean water through the outlet port such that the turbines converts water current into electrical energy.2660650. The ocean water power-generator apparatus of wherein the anchoring assembly further comprises a fixed section () that is fixed to the seafloor and a removable section () that is releasably attached to the fixed section.3619619tb. The ocean water power-generator apparatus of further comprising mechanical jacks ( claim 1 , ) configured to open and close the inlet port.4295578axax. The ocean water power-generator apparatus of further comprising a tether line () connected at a first end to an end of one of the turbines and a second end to a ballast vessel () to support the weight of the turbine.5295508axax. The ocean water power-generator apparatus of further comprising a second tether line () at a first end to an end of ...

Подробнее
Номер записи: 25
23-01-2020 дата публикации

METHOD AND SYSTEM FOR CONTROLLING SAFE TAKEOFF AND LANDING OF PILOTLESS VERTICAL TAKEOFF AND LANDING (VTOL) AIRCRAFT

Номер: US20200026309A1
Автор: Ma Tao
Принадлежит:

In one aspect, a system for safely landing a vertical takeoff-and-landing (VTOL) aircraft in the air onto a landing pad on the ground is disclosed. The system can begin by determining an estimated location of the landing pad with a first accuracy. The system then reduces a height of the VTOL aircraft to a first level above the ground while approaching the estimated location of the landing pad. Next, the system determines an updated location of the landing pad with a second accuracy. The system subsequently reduces the height of the VTOL aircraft to a second level above the ground while approaching the updated location of the landing pad. Next, the system aligns a center point of the VTOL aircraft with a center location of the landing pad. Finally, the system lands the VTOL aircraft onto the landing pad by directly lowering the VTOL aircraft onto the landing pad. 1. A computer-implemented method for safely landing a pilotless vertical takeoff and landing (VTOL) aircraft in the air onto a landing pad on the ground , the method comprising:determining an estimated location of the landing pad with a first accuracy;reducing a height of the VTOL aircraft in the air to a first level above the ground while approaching the estimated location of the landing pad;determining an updated location of the landing pad with a second accuracy;reducing the height of the VTOL aircraft in the air to a second level above the ground while approaching the updated location of the landing pad;aligning a center point of the VTOL aircraft with a center location of the landing pad; andlanding the VTOL aircraft onto the landing pad by directly lowering the VTOL aircraft onto the landing pad.2. The computer-implemented method of claim 1 , wherein determining the estimated location of the landing pad with the first accuracy includes determining the estimated location based on information collected by one of:a GPS;one or more inertial sensors installed on the VTOL aircraft; anda combination of the ...

Подробнее
Номер записи: 26
02-02-2017 дата публикации

Coupling mechanism for aircraft

Номер: US20170029105A1
Автор: Bran Ferren, Donald G. Lariviere, James HIRAHARA
Принадлежит: Northrop Grumman Systems Corp

A device for connecting an aircraft to a tether secured to the ground includes an attachment mechanism secured to the tether. The attachment mechanism includes a projection having at least one opening. A hoop secured to the aircraft extends through each opening in the attachment mechanism. Each hoop forms a sliding connection with the associated opening such that the attachment member slides along the hoop in response to lateral movement of the aircraft relative to the ground.

Подробнее
Номер записи: 27
01-02-2018 дата публикации

MAINTAINING A STABLE PHASE DIFFERENCE BETWEEN MULTIPLE TETHERED VEHICLES LIFTING A PAYLOAD

Номер: US20180032089A1
Автор: Horn Gregory Mainland, Vander Lind Damon
Принадлежит:

A system to maintain a phase difference is disclosed. Two or more aircraft fly in a continuous periodic trajectory. The system maintains a phase difference between the two or more aircraft. Telemetry information for a reference aircraft moving in a first periodic trajectory is received. A phase difference between a primary aircraft and the reference aircraft with respect to the first periodic trajectory is determined. A variance in the phase difference between the primary aircraft and the reference aircraft from the target phase difference is determined. A new trajectory for the primary aircraft that decreases the variance in the phase difference with respect to the new periodic trajectory is determined, and the primary aircraft is maneuvered to follow the new trajectory. 1. A system to maintain a target phase difference comprising:an interface configured to receive telemetry information for a reference aircraft moving in a first periodic trajectory; and determine a phase difference between a primary aircraft and the reference aircraft with respect to the first periodic trajectory;', 'determine a variance in the phase difference between the primary aircraft and the reference aircraft from the target phase difference; and', 'determine a new trajectory for the primary aircraft that decreases the variance in the phase difference with respect to the new periodic trajectory., 'a processor configured to2. The system of claim 1 , wherein the processor is further configured to cause the primary aircraft to move in the new trajectory.3. The system of claim 1 , wherein the processor is configured to determine the primary aircraft to be ahead or behind of a target position based on the variance in phase difference.4. The system of claim 1 , wherein in the event that the primary aircraft is determined to be behind of a target position based on the variance in phase difference claim 1 , the processor is configured to compute the new trajectory such that the primary aircraft ...

Подробнее
Номер записи: 28
01-02-2018 дата публикации

ADJUSTING LOAD ON TETHERED AIRCRAFT

Номер: US20180032090A1
Автор: Horn Gregory Mainland, Vander Lind Damon
Принадлежит:

A system for adjusting a load on a tethered aircraft is disclosed. The aircraft is tethered to a payload. The system determines a new position for the tethered aircraft in the event that due to environmental effects, e.g., the aircraft is flying upwind or downwind, the load experienced by the tethered aircraft is not optimal. 1. A system to adjust a load on an aircraft including:an interface to receive wind information associated with a first aircraft; anda processor configured to determine based at least in part on the wind information whether a first aircraft included in a plurality of aircraft tethered to a payload and flying initially in an original elliptical trajectory is flying upwind or downwind;in the event the first aircraft is determined to be flying downwind, cause the first aircraft to fly further from a vertical axis of the payload than a corresponding distance associated with the original elliptical trajectory; andin the event the first aircraft is determined to be flying upwind, cause the first aircraft to fly nearer to a vertical axis of the payload than a corresponding distance associated with the original elliptical trajectory.2. The system of claim 1 , wherein the plurality of aircraft are in the process of lifting the payload.3. The system of claim 1 , wherein the plurality of aircraft includes a second aircraft claim 1 , wherein the first aircraft and the second aircraft fly opposite or nearly opposite from each other in the original elliptical trajectory.4. The system of claim 1 , wherein a second aircraft of the plurality of aircraft is configured to fly nearer to the vertical axis of the payload than a corresponding distance associated with the original elliptical trajectory in the event the first aircraft flies further from the vertical axis of the payload than a corresponding distance associated with the original elliptical trajectory and is configured to fly further from the vertical axis of the payload than a corresponding distance ...

Подробнее
Номер записи: 29
01-02-2018 дата публикации

FLIGHT CONFIGURATION FOR PAYLOAD AND LIFT AIRCRAFT

Номер: US20180032091A1
Автор: Horn Gregory Mainland, Vander Lind Damon
Принадлежит:

A flight configuration is disclosed. The flight configuration includes a lift configuration in which a lift aircraft lifts a powered payload via a tether. The flight configuration comprises a series of steps for transitioning from the lift configuration to a forward flight configuration. In the forward flight configuration, the lift aircraft and the powered payload are in horizontal alignment. 1. A system to lift and transport a payload comprising:one or more lift aircraft configured to lift the payload via one or more respective tethers in a lift configuration; and receive an indication to transition to a forward flight configuration in which the lift aircraft and the payload fly together in a forward flight direction; and', 'compute and initiate a series of maneuvers to transition the one of more lift aircraft and the payload from the lift configuration to the forward flight configuration., 'a processor configured to2. The system of claim 1 , wherein a flight configuration instruction is provided to the payload and the lift aircraft.3. The system of claim 1 , wherein the payload or the lift aircraft comprises an interface and a processor.4. The system of claim 1 , wherein the forward flight configuration comprises the payload towing the lift aircraft behind the payload.5. The system of claim 1 , wherein the forward flight configuration comprises the lift aircraft towing the payload behind the lift aircraft.6. The system of claim 1 , wherein the series of steps comprises increasing or decreasing power to the payload or the lift aircraft.7. The system of claim 1 , wherein the payload is powered.8. The system of claim 1 , wherein the payload provides power to the lift aircraft and the tether is powered.9. The system of claim 1 , wherein the payload and the lift aircraft each receive telemetry information about the other.10. The system of claim 1 , wherein a propeller of the lift aircraft is recharged in the forward flight configuration.11. The system of claim 1 , ...

Подробнее
Номер записи: 30
30-01-2020 дата публикации

VEHICLE-BASED DEPLOYMENT OF A TETHERED SURVEILLANCE DRONE

Номер: US20200033846A1
Автор: Blavier Mike, Buyse Mathieu, Coulon Jean Marc
Принадлежит:

In one embodiment, the disclosure provides an unmanned aerial system including a base station, an unmanned aerial vehicle (“UAV”), and a tether extending between the base station and the UAV. The base station includes a base housing coupled to a vehicle, a power source, a controller, and a first coupling mechanism coupled to the base housing. The UAV includes a UAV housing, a propulsion system coupled to the UAV housing, a second coupling mechanism, and at least one camera coupled to the UAV housing. The tether extends between the first coupling mechanism and the second coupling mechanism, and is configured to transmit power to the UAV, as well as transmit data signals between the base station controller and the UAV. 1. An unmanned aerial system , comprising: a base housing coupled to a vehicle,', 'a power source, and', 'a first coupling mechanism coupled to the base housing;, 'a base station including'} a UAV housing,', 'a propulsion system coupled to the UAV housing, the propulsion system configured to provide sustained flight of the UAV,', 'a second coupling mechanism coupled to the UAV housing, and', 'at least one camera coupled to the UAV housing;, 'an unmanned aerial vehicle (“UAV”) including transmit power to the UAV, and', 'transmit data signals between the base station and the UAV; and, 'a tether extending between the first coupling mechanism and the second coupling mechanism, the tether configured toa controller communicably coupled to the tether, the controller configured to control the propulsion system of the UAV.2. The unmanned aerial system of claim 1 , wherein the tether is configured to retractable storage within the base housing.3. The unmanned aerial system of claim 1 , wherein the first coupling mechanism further comprises a tensioning device including an electric motor claim 1 , a friction brake claim 1 , or both.4. The unmanned aerial system of claim 1 , further comprising at least one sensor configured to detect a relative orientation between ...

Подробнее
Номер записи: 31
05-02-2015 дата публикации

Tethered Gyroglider Control Systems

Номер: US20150039161A1
Автор: Calverley Grant Howard, Hastings Gregory Howard, Lang David
Принадлежит:

A flight control system for at least one tethered gyroglider along a flight path consistent with at least one flight mission is configured to fly the gyroglider within a portfolio of winds, managing an interaction between portfolios of at least four envelopes including wind, gyroglider performance, flight and base station. Every flight mission corresponds to at least one flight path associated with a set containing at least one first value and at least one second value. The control system is provided with a learning and library manager comprising a repository having stored sets of first values and associated second values for each flight path. The current first values associated with a current mission are corrected based on predicted or experienced flight paths and measurable outputs to attain the desired flight path. The corrected, experienced values, flight path and measurable output are further stored in the repository for further learning. 1. A control system for at least one tethered gyroglider along a flight path consistent with at least one flight mission , at least one of measured, simulated and calculated first values corresponding to at least one dynamic element associated with the at least one flight mission;', 'at least one second value corresponding to pre-determined settings associated with the at least one flight mission; and', 'stored flight paths associated with stored sets containing at least one of the stored first values and at least one of the stored second values, said stored flight paths corresponding to the at least one flight mission;, 'a learning and library manager having a repository, said library manager adapted to receive and store in said repository,'}, 'said control system comprisingan input manager adapted to receive current first values corresponding to the current state of said at least one dynamic element;a settings manager adapted to receive second values associated with at least one current flight mission of the at least one ...

Подробнее
Номер записи: 32
09-02-2017 дата публикации

A DRONE

Номер: US20170036761A1
Автор: CROCHAT Philippe
Принадлежит:

A drone with a horizontal rotor includes one or more rotor(s) () which rotate in a horizontal plane, each rotor () being equipped with one or more rigid or non-rigid blades (), the blade end being mounted on an electric motor () with a propeller. 111-. (canceled)12115116115116120121110111. A drone with a horizontal rotor comprising one or more rotor(s) ( , ) which rotate in a horizontal plane , each rotor ( , ) being equipped with one or more rigid or non-rigid blades ( , ) , the blade end being mounted on an electric motor ( , ) with a propeller.13122123. The drone as claimed in claim 12 , in which the blade end is equipped with a wing ( claim 12 , ).14120121. The drone as claimed in claim 12 , which comprises telescopic means that make it possible to adapt the radius of rotation of each blade ( claim 12 , ).15115116120121. The drone as claimed in claim 12 , in which each of the rotors ( claim 12 , ) is equipped with a winding claim 12 , unwinding device in order to vary the radius of rotation of each blade ( claim 12 , ) which is linked thereto.16. The drone as claimed in claim 15 , in which the winding claim 15 , unwinding device is in the hub.17120121. The drone as claimed in claim 12 , in which the propellers situated at the blade ends ( claim 12 , ) rotate in the reverse direction to the blade end vortex.18. The drone as claimed in claim 12 , in which the motors are permanent magnet motors.19. The drone as claimed in claim 12 , which comprises a single rotor and an electronic device for cyclically varying one of the aerodynamic parameters of the rotor claim 12 , combined with the presence of at least one sensor in order to ensure the stability of the drone.20115116114. The drone as claimed in claim 12 , which comprises two or more rotors ( claim 12 , ) and a device for controlling the speed of rotation of said two or more rotors so as to assure stability on one axis under the effect of the incident wind and in that the stability on the other axis is assured by ...

Подробнее
Номер записи: 33
09-02-2017 дата публикации

TETHER SYSTEM FOR AERIAL VEHICLE

Номер: US20170036777A1
Автор: Martin Richard George, Vaughn Brad Lee
Принадлежит:

According to some embodiments, there is provided a tether system for coupling an unmanned aerial vehicle (UAV) to an anchor location, the tether system comprising a tether line configured to couple the UAV to the anchor location during flight of the UAV, and an anti-entanglement (AE) member extending along a section of the tether line, the AE member having a first end proximate the UAV and a second end opposite the first end, proximate the anchor location. 1. A tether system for coupling an unmanned aerial vehicle (UAV) to an anchor location , the tether system comprising:a tether line configured to couple the UAV to the anchor location during flight of the UAV; andan anti-entanglement (AE) member extending along a section of the tether line, the AE member having a first end proximate the UAV and a second end opposite the first end, proximate the anchor location.2. The tether system of claim 1 , further comprising a line reel configured to maintain a predetermined tension level of the tether line during flight of the UAV.3. The tether system of claim 1 , further comprising a connector coupled to the first end of the AE member claim 1 , the connector configured to be removably attached to the UAV.4. The tether system of claim 3 , wherein the connector comprises a rotation device configured to rotate 360 degrees along an axis of the tether line claim 3 , the axis extending from the UAV to the anchor location.5. The tether system of claim 1 , wherein the tether system is configured to be coupled to the UAV at a surface of the UAV at a central location along the surface of the UAV.6. The tether system of claim 1 , further comprising a line weight attached to the second end of the AE member.7. The tether system of claim 1 , wherein the AE member is configured to flex corresponding to movement of the tether line as the tether line moves during flight of the UAV that is coupled to the tether line.8. The tether system of claim 7 , wherein the AE member comprises a plurality ...

Подробнее
Номер записи: 34
08-02-2018 дата публикации

Midair Tethering of an Unmanned Aerial Vehicle with a Docking Station

Номер: US20180039286A1
Автор: Gerhards Keith, Minnick Danny J., Tirpak Christopher Boyd
Принадлежит:

Unmanned aerial vehicle docking systems and methods are presented herein. A UAV may hover in a hovering position above a docking pad of the UAV docking system based on positioning measurements. An on-board camera may image a machine-readable code present on the docking pad. The hovering position of the UAV above the docking pad may be adjusted based on imaging of the machine-readable code and ranging measurements to the docking pad. A tether can be extended from the UAV towards the docking pad. The hovering position of the UAV and extension of the tether can be adjusted such that a mating device present on a distal end of the tether engages with a coupling device of the UAV docking pad. The tether may be reeled in to the UAV to assist in lowering the UAV from the hovering position to a landing position on the docking pad. 2. The UAV docking system of claim 1 , wherein the tether line claim 1 , while the magnetic coupler of the UAV docking station is coupled with the UAV mating device claim 1 , the tether line transfers power to a battery on-board the UAV.3. The UAV docking system of claim 1 , the on-board UAV docking system further comprising a ranging sensor that determines an altitude of the UAV above the UAV landing pad.4. The UAV docking system of claim 1 , wherein the recharging system of the UAV docking station comprises a wireless charger that wirelessly transfers power to the UAV when the UAV is docked with the UAV docking station.5. The UAV docking system of claim 1 , wherein the UAV landing pad comprises multiple visual machine-readable codes that identify different zones of the UAV landing pad claim 1 , wherein the UAV landing pad accommodates multiple UAVs in the different zones.6. The UAV docking system of claim 1 , wherein the magnetic coupler of the UAV docking station comprises an electromagnet claim 1 , wherein the electromagnet is powered down during a takeoff procedure of the UAV after the UAV has begun hovering above the UAV landing pad.7. The ...

Подробнее
Номер записи: 35
24-02-2022 дата публикации

SPOOLER FOR UNMANNED AERIAL VEHICLE SYSTEM

Номер: US20220055745A1
Автор: Johnson Samuel A., Shein Andrew M., Walker Jason S., Ware John W.
Принадлежит:

In an aspect, in general, a spooling apparatus includes a filament feeding mechanism for deploying and retracting filament from the spooling apparatus to an aerial vehicle, an exit geometry sensor for sensing an exit geometry of the filament from the spooling apparatus, and a controller for controlling the feeding mechanism to feed and retract the filament based on the exit geometry. 1. A system comprising:a mobile vehicle; anda spooling apparatus mounted on the mobile vehicle and comprising:a filament feeding mechanism for deploying and retracting a filament from the spooling apparatus to an aerial vehicle;an exit geometry sensor for sensing an exit geometry of the filament from the spooling apparatus; anda controller for controlling the filament feeding mechanism to feed and retract the filament based on the exit geometry.2. The system of claim 1 , wherein the controller is configured to control the filament feeding mechanism to feed and retract the filament based on the exit geometry when the mobile vehicle moves.3. The system of claim 2 , wherein the controller is configured to control the filament feeding mechanism to feed and retract the filament based on the exit geometry when the aerial vehicle is controlled to follow movement of the mobile vehicle.4. The system of claim 1 , wherein the exit geometry sensor comprises:a tube coaxially surrounding a portion of the filament at a point where the filament exits the spooling apparatus; anda position sensor coupled to the tube, for measuring an angular position of the tube.5. The system of claim 1 , wherein the spooling apparatus is configured to draw power from the mobile vehicle.6. The system of claim 1 , wherein the aerial vehicle is collapsible.7. The system of claim 1 , wherein the spooling apparatus is configured to receive global positioning system (GPS) coordinates of the aerial vehicle from the aerial vehicle.8. The system of claim 1 , further comprising the aerial vehicle.9. The system of claim 8 , ...

Подробнее
Номер записи: 36
07-02-2019 дата публикации

Methods and Systems For Line Transfer

Номер: US20190039730A1
Автор: Smoor Jacobus Johan
Принадлежит:

The invention relates to a system and to a method for the transfer of a line or a heaving line for a line, wherein the system comprises at least a flying vehicle, provided with a connection provision adapted for releasably connecting a line or heaving line to said flying vehicle 1. A system for transfer of a line or a heaving line for a line , wherein the system comprises at least a flying vehicle , provided with a connection provision adapted for releasably connecting a line or heaving line to said flying vehicle.2. The system according to claim 1 , wherein the flying vehicle is a remotely controllable vehicle.3. The system according to claim 1 , wherein the flying vehicle is a drone.4. The system according to claim 1 , wherein the flying vehicle is provided with a homing system for returning the vehicle automatically to a home position.5. The system according to claim 1 , wherein the flying vehicle is provided with a target system for automatically flying the vehicle to a designated target position.6. The system according to claim 1 , wherein the connection provision comprises at least a clamp.7. The system according to claim 1 , wherein the system comprises at least one magnet claim 1 , connected to or connectable to at least one of the flying vehicle and a line or heaving line to be transferred.8. The system according to claim 1 , wherein the flying vehicle is provided with an ejection system for ejecting a line or heaving line connected to the flying vehicle.9. The system according to claim 1 , wherein the flying vehicle is provided with at least a camera.10. The system according to claim 1 , wherein a line or heaving line is provided claim 1 , having a signaling device attached to or attachable to said line or heaving line.11. The system according to claim 1 , wherein the system comprises a tug boat and wherein the line is a towing line claim 1 , which preferably is connected to or connectable to a heaving line to be engaged by the flying vehicle.12. The ...

Подробнее
Номер записи: 37
24-02-2022 дата публикации

CABLE, CONNECTION STRUCTURE PROVIDED WITH CABLE, WIRE HARNESS, AND MOORED MOBILE BODY

Номер: US20220059251A1
Автор: Kaneko Hiroshi
Принадлежит: FURUKAWA ELECTRIC CO., LTD.

The purpose of the present invention is to provide a cable used to at least moor a moving body to be moored and supply power thereto, such that weight of the whole cable can be reduced. A cable according to the present invention connects a moving body to be moored to a unit assembly including a power supply unit. The cable is used to at least moor the moving body to be moored to the unit assembly and supply power from the power supply unit to the moving body to be moored. The cable includes a conductor constituted with element wires, and at least part of the element wires is a high-strength aluminum-based conductor. 1. A cable for connecting a moored mobile body to a unit assembly including a power supply unit , for use at least in mooring of the moored mobile body to the unit assembly and in power supply from the power supply unit to the moored mobile body ,the cable comprising a conductor constituted with element wires, at least part of the element wires being a high-strength aluminum-based conductor.2. The cable according to claim 1 , wherein the high-strength aluminum-based conductor has a tensile strength of 180 MPa or more.3. The cable according to wherein the high-strength aluminum-based conductor is composed of an 8000-series aluminum alloy.4. The cable according to claim 1 , wherein the high-strength aluminum-based conductor is composed of a 5000-series aluminum alloy.5. The cable according to claim 1 , wherein the high-strength aluminum-based conductor is composed of a 6000-series aluminum alloy.6. The cable according to claim 1 , wherein the high-strength aluminum-based conductor has a fibrous metal structure in which crystal grains uniformly extend in an extending direction of the high-strength aluminum-based conductor claim 1 , and the crystal grains have an average value of less than or equal to 500 nm with respect to a dimension perpendicular to a longitudinal direction of the crystal grains on a cross section thereof parallel to the extending ...

Подробнее
Номер записи: 38
16-02-2017 дата публикации

TETHERED UNMANNED AERIAL VEHICLE FIRE FIGHTING SYSTEM

Номер: US20170043872A1
Автор: Corson Michael, Whitaker Todd Michael
Принадлежит:

A tethered unmanned aerial vehicle firefighting system includes a firefighting drone, a lifting drone and a tether line coupling the firefighting drone to a control station through the lifting drone. The control station includes a control unit for controlling the firefighting drone and the lifting drone, a fire retardant supply, a pump coupled to the fire retardant supply, and a power supply. The tether line includes a power line coupling the power source to and powering the firefighting drone and a fire retardant hose coupled between the pump and a nozzle carried by the firefighting drone. A lifting tower hold the tether from the control station at a height above ground level, and the lifting drone maintains the tether above obstruction for the firefighter drone. The firefighter drone disperses fire retardant from the nozzle for firefighting purposes and with a substantially unlimited supply of retardant and power. 1. A tethered unmanned aerial vehicle firefighting system comprising:a firefighting drone having at least one drive motor and a nozzle;a control station including a control unit for controlling the firefighting drone, a fire retardant supply, a pump coupled to the fire retardant supply and a power supply; anda tether line coupled between the control station and the firefighting drone, the tether line including a power line coupling the power source to and powering the at least one drive motor of the firefighting drone, and a fire retardant hose coupled between the pump and the nozzle for supplying fire retardant to the nozzle carried by the firefighting drone under pressure.2. A tethered unmanned aerial vehicle firefighting system as claimed in wherein the control station is carried by a tanker helicopter.3. A tethered unmanned aerial vehicle firefighting system as claimed in further comprising a lifting drone engaging the tether line intermediate the control station and the firefighting drone to support the tether line above ground level and above ...

Подробнее
Номер записи: 39
14-02-2019 дата публикации

METHOD AND APPARATUS FOR CABLE-DRIVEN ADAPTIVE VIBRATION CONTROL

Номер: US20190047705A1
Автор: Diao Xiumin, Xiong Hao
Принадлежит: PURDUE RESEARCH FOUNDATION

A vibration control system for an unmanned aerial vehicle (UAV) is disclosed. The system includes a base platform fixedly coupled to a UAV structure, a working platform coupled to the base platform by two or more cables at two or more connection points on the working platform, and two or more actuators positioned either on the base platform or the working platform, each actuator configured to receive a signal to adjust tension in a corresponding cable, wherein by adjusting tension in the two or more cables, natural frequency of the working platform can be adjusted in response to frequency of vibration experienced by the working platform in order to maintain a frequency ratio (FR) of the vibration frequency to the natural frequency at or above a predetermined value. 1. A vibration control drive system used in an unmanned aerial vehicle (UAV) , comprising:a base platform fixedly coupled to a UAV structure;a working platform coupled to the base platform by two or more cables at two or more connection points on the working platform;two or more actuators positioned either on the base platform or the working platform, each actuator configured to receive a signal to adjust tension in a corresponding cable; anda first controller coupled to and adapted to control the two or more actuators, whereby two or more control signals are calculated for the two or more actuators based on a target position from a current position of the working platform according to one of (i) an open-loop configuration, (ii) a first closed-loop configuration utilizing velocity of the working platform as a feedback signal, or (iii) a second closed-loop configuration utilizing velocity of the working platform as a first feedback signal and the position information of the working platform as a second feedback signal.2. The drive system of claim 1 , wherein each of (i) the open-loop claim 1 , (ii) the first closed loop claim 1 , and (iii) the second closed loop configurations initially calculates the ...

Подробнее
Номер записи: 40
25-02-2016 дата публикации

UNMANNED AERIAL VEHICLE HAVING AN ONBOARD CLEANING DEVICE

Номер: US20160052644A1
Автор: Chin Hon Wah, Gross Bill, Hyde Roderick A., JR. Lowell L., Kare Jordin T., Myhrvold Nathan P., Petroski Robert C., Tegreene Clarence T., Wood
Принадлежит:

Described embodiments include an unmanned aerial vehicle and a method. The unmanned aerial vehicle includes an airframe, and a rotary wing system coupled with the airframe and configured to aerodynamically lift the vehicle in the air. The unmanned aerial vehicle includes a flight controller configured to control a movement of the vehicle while airborne. The unmanned aerial vehicle includes a cleansing controller configured to manage removal by an onboard cleaning device of a surface contamination from a selected portion of a surface of an external object. The unmanned aerial vehicle includes the onboard cleaning device. 1. An unmanned aerial vehicle comprising:an airframe;a rotary wing system coupled with the airframe and configured to aerodynamically lift the vehicle in the air;a flight controller configured to control a movement of the vehicle while airborne;a cleansing controller configured to manage removal by an onboard cleaning device of a surface contamination from a selected portion of a surface of an external object; andthe onboard cleaning device.2. The vehicle of claim 1 , wherein the cleansing controller is configured to manage the removal by the onboard cleaning device of the surface contamination from the external object while the unmanned aerial vehicle is airborne.3. The vehicle of claim 1 , wherein the cleansing controller is configured to manage the removal by the onboard cleaning device of a surface contamination while the unmanned aerial vehicle is attached to the external object.4. The vehicle of claim 1 , wherein the cleansing controller is configured to direct an airstream emitted by the onboard cleaning device at the selected portion of the surface with sufficient force to dislodge the surface contaminant.5. The vehicle of claim 1 , wherein the onboard cleaning device includes a container carried by the airframe and configured to store air or other gas.6. The vehicle of claim 1 , wherein the onboard cleaning device includes an onboard air ...

Подробнее
Номер записи: 41
25-02-2021 дата публикации

Detachable Power Tethering Systems for Aircraft

Номер: US20210053676A1
Автор: Brand Albert G., Poster Scott David
Принадлежит: Bell Textron Inc.

An electric power tethering system for an aircraft having a vertical takeoff and landing flight mode including a takeoff phase and/or a hover phase includes a surface power source and a power tether having a surface end configured to couple to the surface power source and an aircraft end configured to couple to the aircraft. The power tether is configured to transmit power from the surface power source to the aircraft in the takeoff phase and/or the hover phase. The power tether is detachable to decouple the surface power source from the aircraft in response to a power tether release event during flight. 1. An electric power tethering system for an aircraft having a vertical takeoff and landing flight mode including a takeoff phase and a hover phase , the system comprising:a surface power source; anda power tether having a surface end configured to couple to the surface power source and an aircraft end configured to couple to the aircraft, the power tether configured to transmit power from the surface power source to the aircraft in the takeoff phase and the hover phase;wherein the power tether is detachable to decouple the surface power source from the aircraft in response to a power tether release event during flight.2. The electric power tethering system as recited in wherein the surface power source further comprises at least one of a power grid claim 1 , a generator or a battery.3. The electric power tethering system as recited in wherein the surface power source further comprises a retraction spool configured to retract the power tether following the power tether release event.4. The electric power tethering system as recited in wherein the surface power source further comprises a mobile surface power source configured to move along a surface while the power tether couples the mobile surface power source to the aircraft.5. The electric power tethering system as recited in further comprising a land vehicle to transport the mobile surface power source along a ...

Подробнее
Номер записи: 42
22-02-2018 дата публикации

TETHERED UNMANNED AERIAL VEHICLE

Номер: US20180050798A1
Автор: KAPURIA ANUJ
Принадлежит:

A tethered UAV () is disclosed. The UAV () may carry a payload (). The payload may include camera, radio mast, or sensors. Power supply to the UAV () via a tether cable () from a ground station () may be varied using a reconfigurable power converter. Further, the UAV () may enter an autopilot mode based on a disruption of power supply from a power source at the ground station (), low energy level of the power source, and a temperature of the power converter. In the autopilot mode, power may be supplied to the UAV () from an on-board battery and wireless communication may be initiated between the UAV () and the ground station () via a network (). 1. An Unmanned Aerial Vehicle (UAV) comprising:a central unit to store pre-programmed instructions for operation of the UAV;an electronic speed controller, coupled to the central unit, to regulate flying speed of the UAV; and receive power for the UAV; and', 'supply the received power in a varying level., 'a power converter, coupled to the electronic speed controller to2. The UAV of further comprising a power management module claim 1 , coupled to the power converter claim 1 , to switch between the power converter and a battery based on a power requirement of the UAV claim 1 , wherein the battery is on board the UAV to supply power stored within the battery.3. The UAV of claim 1 , wherein the power converter is further to:determine an operational status of the UAV; andprovide a predefined level of power based on the operational status to supply the power.4. The UAV of claim 3 , wherein the operational status of the UAV is one of a payload weight claim 3 , a flight status claim 3 , and a power status of the UAV.5. The UAV of claim 1 , further comprising an auto pilot module claim 1 , coupled to the power management module claim 1 , to:receive an input from the power management module; andactivate the battery for power supply to the UAV.6. The UAV of claim 5 , further comprising a Ground Facing camera (GFC) coupled to the ...

Подробнее
Номер записи: 43
21-02-2019 дата публикации

TETHERED UNMANNED AERIAL VEHICLE SYSTEM

Номер: US20190055036A1
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 for use with an unmanned aerial vehicle (UAV) , the system comprising:a base;a vertically-oriented elongate structure comprising a lower end and an upper end, wherein the elongate structure includes an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end;a deployable cushioning-device coupled to the elongate structure;a tether comprising a portion that extends from the upper access-point to the UAV; and detecting abnormal operation of the UAV; and', 'responsive to detecting abnormal operation of the UAV, causing the deployable cushioning-device to deploy., 'a computing system configured for performing a set of acts comprising2. The system of claim 1 , wherein the base comprises a vehicle.3. The system of claim 1 , wherein the vertically-oriented elongate structure comprises a mast having an adjustable height.4. The system of claim 1 , wherein the deployable cushioning-device comprises a set of one or more deployable cushioning components ...

Подробнее
Номер записи: 44
04-03-2021 дата публикации

MONITORING EVENTS EMPLOYING A DRONE HAVING A CAMERA CONTROLLED VIA AN APPLICATION

Номер: US20210061466A1
Автор: Gee Howard
Принадлежит:

The disclosure provides a monitoring system for live event, a computing device to use with the monitoring, and a computer program product that can be used to control the monitoring. In example, the monitoring system includes: (1) a control structure and a drone having a camera, wherein the drone is tethered to the control structure, and (2) a computing device having an integrated transceiver configured to receive an access signal and a processor configured to control operations of the drone and the camera, when having permission based on the access signal, to capture images from the camera. 1. A monitoring system for live events , comprising:a control structure and a drone having a camera, wherein the drone is tethered to the control structure; and an integrated transceiver configured to receive an access signal; and', 'a processor configured to control operations of the drone and the camera, when having permission based on the access signal, to capture images from the camera., 'a computing device, including2. The viewing system as recited in claim 1 , wherein the computing device includes a memory having an application stored thereon claim 1 , and the processor controls operation of the drone and the camera via the application.3. The monitoring system as recited in claim 2 , wherein the application communicates with a remote server via the integrated transceiver to receive the access signal.4. The monitoring system as recited in claim 1 , wherein the access signal is an encoded/encrypted access signal and the processor is configured to convert the encoded/encrypted access signal to an access code employing the application to obtain the permission.5. The monitoring system as recited in claim 1 , wherein the integrated transceiver is configured to receive the access signal via either a cellular network claim 1 , a wireless local area network (WLAN) claim 1 , or a combination of both.6. The monitoring system as recited in claim 1 , wherein the computing device further ...

Подробнее
Номер записи: 45
04-03-2021 дата публикации

Unmanned Aerial Vehicle Tether Spool

Номер: US20210061487A1
Автор: Briggs, IV Fred Melvelle, Stave Todd
Принадлежит: Blue Vigil, LLC

A drum is rotatably mounted on a carriage. A cable is configured to: transport power, connect with a drum connector disposed on the drum, and connect with an unmanned aerial vehicle (UAV) via a UAV connector. A drum actuator is configured to rotate the drum. A UAV feed is configured to align the cable as it exits the device towards the UAV. A tension sensor is configured to measure a tension of the cable. A controller receive as tension measurement from the tension sensor; and controls the drum actuator to maintain a determined tension on the cable while: dispensing the cable; holding the cable steady; or collecting the cable. 1. A device comprising:a drum rotatably mounted on a carriage; transport power;', 'connect with a drum connector disposed on the drum; and', 'connect with an unmanned aerial vehicle (UAV) via a UAV connector;, 'a cable configured toa drum actuator configured to rotate the drum;a UAV feed configured to align the cable as it exits the device towards the UAV;a tension sensor configured to measure a tension of the cable; and at least one processor;', receive a tension measurement from the tension sensor; and', dispensing the cable;', 'holding the cable steady; or', 'collecting the cable., 'control the drum actuator to maintain a determined tension on the cable while], 'a tangible medium comprising instructions that, when executed by the at least one processor, cause the controller to], 'a controller comprising2. The device according to claim 1 , further comprising a power transfer circuit configured to deliver power to a UAV from a battery when power on the cable falls below a threshold value.3. The device according to claim 2 , wherein the power transfer circuit is connected to the UAV connector.4. The device according to claim 1 , further comprising a remote UAV power supply configured to provide power to the UAV via the cable.5. The device according to claim 1 , further comprising a command circuit configured to deliver a landing command to a ...

Подробнее
Номер записи: 46
28-02-2019 дата публикации

RADIO FREQUENCY STEALTHY TETHERED AIRCRAFT

Номер: US20190061938A1
Автор: McCorkle John W.
Принадлежит:

A tethered aircraft is provided in which the conductive tether is broken into two or more sections and where at least one section is an RF-isolating section that acts to reduce or control RF current flow on the tether. Reducing the RF current flow reduces the interaction of the tether with incoming RF waves. This allows reduced radar cross-section and reduced reflections that inhibit the performance of RF payloads, such as direction finding. The RF-isolating sections also allow RF currents to be controlled, such as forcing current to flow in a desired location to form an antenna built into the tether. The disclosure identifies 4 different RF-isolating sections to allow optimization for weight and frequency band coverage. The application of using sectioned tethers, as disclosed here, is useful not only for tethers that convey power, but also for tethers that serve other purposes, such as conveying information and signals. 1. A tether system , comprising: a first interval that is a first radio-frequency-isolating interval which includes at least one of: a first magnetic-choke section, a first open-stub-transmission-line section, a first open-stubbed-magnetic-choke section, or a first magnetic-flux-coupled section, and', 'a multi-conductor cable connected to the first interval., 'a multi-conductor tether, including'}2. The tether system of claim 1 , whereinthe multi-conductor tether is configured to conduct power from a ground-based power source to an aircraft.3. The tether system of claim 1 , whereinthe magnetic-choke section includes a length of the multi-conductor cable that passes through or is wound around a core, to form a choke that inhibits radio frequency current from flowing through the magnetic choke-section.4. The tether system of claim 3 , whereinthe core is a high mu core.5. The tether system of claim 3 , whereinthe core is an air core.6. The tether system of claim 3 , whereinthe core is a resistive or ferrite-loaded bendable material.7. The tether system ...

Подробнее
Номер записи: 47
27-02-2020 дата публикации

METHOD FOR LANDING A TETHERED AIRCRAFT AND LAUNCH AND LAND SYSTEM

Номер: US20200062421A1
Автор: PAZ DUART Marcos
Принадлежит:

The invention relates to a method for landing a tethered aircraft (), comprising the steps of •—approaching a ground site with said aircraft, thereby shortening free length of tether () between the aircraft and the ground site until said free length of tether reaches a predetermined value, •—further approaching the ground site with said aircraft, thereby keeping free length of tether fixed at said predetermined value, •—retaining the tether to form a loop, wherein the loop is tensed and tightened by the moving aircraft, and •—damping said tightening of said loop in order to decelerate the aircraft until it stands at the ground site. The invention further relates to a launch and land system () for a tethered aircraft comprising a runway () for the aircraft, a winch () for the tether, and a retention system () for forming a loop of the tether between the winch and the aircraft approaching the runway, wherein said retention system features a damping device () for damping a tightening of said loop caused due to movement of the aircraft upon approach and landing in order to decelerate said aircraft. 110-. (canceled)11: A method for landing an aircraft that is tethered to a ground site by a tether , the method comprising:approaching the ground site with said aircraft, thereby shortening a free length of the tether between the aircraft and the ground site until said free length of the tether reaches a predetermined value;further approaching the ground site with said aircraft while keeping the free length of the tether fixed at said predetermined value;retaining the tether to form a loop, wherein the loop is tensed and tightened by the moving aircraft; anddamping said tightening of said loop in order to decelerate the aircraft until the aircraft stands at the ground site.12: The method according to claim 11 , wherein said predetermined value for the free length of tether is selected such that the decelerated aircraft comes to stand within a predetermined target area at said ...

Подробнее
Номер записи: 48
19-03-2015 дата публикации

Methods and Systems for Transitioning an Aerial Vehicle Between Hover Flight and Crosswind Flight

Номер: US20150076284A1
Автор: Chubb Erik Christopher, Vander Lind Damon
Принадлежит: GOOGLE INC.

A method may involve operating an aerial vehicle in a hover-flight orientation. The aerial vehicle may be connected to a tether that defines a tether sphere having a radius based on a length of the tether, and the tether may be connected to a ground station. The method may involve positioning the aerial vehicle at a first location that is substantially on the tether sphere. The method may involve transitioning the aerial vehicle from the hover-flight orientation to a forward-flight orientation, such that the aerial vehicle moves from the tether sphere. And the method may involve operating the aerial vehicle in the forward-flight orientation to ascend at an angle of ascent to a second location that is substantially on the tether sphere. The first and second locations may be substantially downwind of the ground station. 1. A method comprising:operating an aerial vehicle in a hover-flight orientation, wherein the aerial vehicle is connected to a tether that defines a tether sphere having a radius based on a length of the tether, wherein the tether is connected to a ground station;while the aerial vehicle is in the hover-flight orientation, positioning the aerial vehicle at a first location that is substantially on the tether sphere, wherein the first location is substantially downwind of the ground station;transitioning the aerial vehicle from the hover-flight orientation to a forward-flight orientation, such that the aerial vehicle moves from the tether sphere, wherein the aerial vehicle has attached flow, and wherein a tension of the tether is reduced; andoperating the aerial vehicle in the forward-flight orientation to ascend at an angle of ascent to a second location that is substantially on the tether sphere, wherein the second location is substantially downwind of the ground station.2. The method of claim 1 , wherein the aerial vehicle has attached flow during the ascent.3. The method of claim 1 , wherein operating the aerial vehicle in the forward-flight ...

Подробнее
Номер записи: 49
19-03-2015 дата публикации

Methods and Systems for Transitioning an Aerial Vehicle Between Crosswind Flight and Hover Flight

Номер: US20150076289A1
Автор: Chubb Erik Christopher, Vander Lind Damon
Принадлежит: GOOGLE INC.

A method may involve operating an aerial vehicle in a hover-flight orientation. The aerial vehicle may be connected to a tether that defines a tether sphere having a radius based on a length of the tether, and the tether may be connected to a ground station. The method may involve positioning the aerial vehicle at a first location that is substantially on the tether sphere. The method may involve transitioning the aerial vehicle from the hover-flight orientation to a forward-flight orientation, such that the aerial vehicle moves from the tether sphere. And the method may involve operating the aerial vehicle in the forward-flight orientation to ascend at an angle of ascent to a second location that is substantially on the tether sphere. The first and second locations may be substantially downwind of the ground station. 1. A method comprising:operating an aerial vehicle in a crosswind-flight orientation, wherein the aerial vehicle is connected to a tether that defines a tether sphere having a radius based on a length of the tether, wherein the tether is connected to a ground station;while the aerial vehicle is in the crosswind-flight orientation, positioning the aerial vehicle at a first location that is substantially on the tether sphere, wherein the first location is substantially downwind of the ground station;transitioning the aerial vehicle from the crosswind-flight orientation to a forward-flight orientation, such that the aerial vehicle moves from the tether sphere, wherein the aerial vehicle has attached flow, and wherein a tension of the tether is reduced; andoperating the aerial vehicle in the forward-flight orientation to ascend at an angle of ascent to a second location, wherein the second location is substantially downwind of the ground station.2. The method of claim 1 , wherein the aerial vehicle has attached flow during the ascent.3. The method of claim 1 , wherein operating the aerial vehicle in the forward-flight orientation to ascend at the angle of ...

Подробнее
Номер записи: 50
07-03-2019 дата публикации

Apparatus, device and method for automated launch and recovery of a kite

Номер: US20190071175A1
Автор: James Nathaniel Chafe, Kevin Wade Silbert, Paul Charles Seiffert
Принадлежит: Maritime Applied Physics Corp

A kite launch device that includes a kite, a mast, a guide device coupled to the mast, and a winch. The kite includes a canopy, a base structure for at least one device, a plurality of support lines coupled to the canopy and the base structure, a guide line coupled to the canopy, and a tether coupled to the base structure. The guide device is configured to grab the guide line. The winch is coupled to the tether of the kite. The winch is configured to extend and retract the tether. In some implementations, the kite includes a guide element coupled to the base structure and the guide line. In some implementations, the guide device is configured to encircle the guide element in order to grab the guide line.

Подробнее
Номер записи: 51
24-03-2022 дата публикации

POWER GENERATING WINDBAGS AND WATERBAGS

Номер: US20220090576A1
Автор: SIA Yik Hei
Принадлежит:

Self-enabled means of sustainable energies generation and storage. Self-sufficiency in conversion of propulsion energies. Decarbonization of the global shipping industry. Empowering the blue ocean fleet of merchant liners with self-created propulsion power. Backed up by grid energy storage systems; and low carbon bunkers. To break free from the shackles of dirty energies; from being slaves of energy poverty. To achieve energy independence! Including: sustainable energies generation systems using wind-sails; pontoons; pliable; flexible semi-solid shrouds; made of plastics; polymers; etc. to capture fluids; channelling it through constricted tunnels to drive wind turbines; tidal turbines; etc. integrated with drones; robotic technologies for conversion into renewable electricity. An extremely scalable system, apparatus, equipment, techniques and ecosystem configured to produce renewable green energy with high productivity and efficiency. 1900901. A system () for self-generation and storage of renewable propulsion energies for ocean vessels (); wherein said decarbonization and conversion from fossil energies to green energies are enabled by means of:{'b': 920', '921', '905', '906, "a plurality of panels () embedded with a multitude of wind and tidal turbine units (); for the extraction and conversion of wind and tidal energies into electricity for driving the ship's electrified engine (); propeller ();"}{'b': '901', 'claim-text': [{'b': 910', '904', '902', '903', '904, 'i': 'a', 'a batteries storage system () comprising: grid storage batteries(′); including: transformer (); rectifier or inverter (); operating batteries (″);'}, {'b': 910', '509', '549', '704', '907', '908', '909, 'i': b', 'z', 'z', 'z, 'a hydrogen storage system () including means of: conversion by electrolyzers (); storage in tank (); liquid ammonia tank (); cylinders (); dissociation of hydrogen from ammonia using PEM-catalytic membrane (); and the reconversion of hydrogen into electricity using fuel- ...

Подробнее
Номер записи: 52
26-03-2015 дата публикации

AEROSTAT SYSTEM

Номер: US20150083849A1
Автор: Glass Benjamin W., Lanford Ephraim R., Vermillion Christopher R.
Принадлежит:

The invention provides an improved aerostat system including an aerostat, multiple tether groups and a base station. Spatially distinct tether groups allow for improved stability and controllability over a wide range of wind conditions. Independent actuation of the tether groups allows for control of the aerostat pitch and roll angle. A rotating platform including rails to rest the aerostat allows docking without auxiliary tethers, minimizing or eliminating the ground crew required to dock traditional aerostat systems. An optional controller allows remote or autonomous operation of the aerostat system. The invention is intended to extend the flight envelope in which aerostat systems can safely operate. 1. An aerostat system that allows for improved control in a variety of wind conditions , passive alignment into the wind , and autonomous docking , the system comprising:(1) an aerostat including a shroud;(2) multiple tether groups arranged on the shroud so that there is defined substantial separation distance between tether attachment points in each of a longitudinal (forward/aft), direction and a lateral (side/side) direction, each of the multiple tether groups being independently actuated by a respective winch assembly; and(3) a base station located with respect to a ground surface including a rotating platform, the platform interconnected to the multiple tether groups and including a rail assembly that selectively engages the aerostat in a docked configuration with respect to the platform.2. The system as set forth in claim 1 , further comprising one or a plurality of forward tether lead-off points and a plurality of claim 1 , or one claim 1 , aft tether lead-off points on the base station claim 1 , the forward tether lead-off points being separated from the aft-tether lead-off points at a lead-off-point separation distance that is approximately similar to a forward and aft separation of the tether attachment points on the shroud claim 1 , thereby defining a ...

Подробнее
Номер записи: 53
24-03-2016 дата публикации

Apparatus and methods for tethered aerial platform and system

Номер: US20160083115A1
Автор: Kevin Hess
Принадлежит: Kevin Hess

A drone system includes a drone that includes a propulsion system, a flight stabilizer system, and an air payload interface unit, and a camera system, wherein the camera system includes a camera stabilizing unit, and a ground support system to which the drone is detachably coupled through a tether unit, and for providing electrical power to the propulsion system. The drone system further includes a ground payload interface unit for receiving and transmitting command and telemetry information to the air payload interface unit through the tether unit, and a controlling device for controlling the propulsion system and the camera system through the tether unit.

Подробнее
Номер записи: 54
23-03-2017 дата публикации

BASE STATION DESIGN ASSIST SYSTEM UTILIZING UNMANNED AERIAL VEHICLE, AND SERVER USED FOR THE SYSTEM

Номер: US20170083645A1
Автор: Miyakawa Junichi
Принадлежит:

To provide a system comprising: an unmanned aerial vehicle; and a free space location database, wherein the unmanned aerial vehicle has: a camera that is capable of 360°-image capturing on a horizontal plane; a positioning apparatus that measures a location of the unmanned aerial vehicle; a direction measuring apparatus that measures a direction of the unmanned aerial vehicle; an altitude measuring apparatus that measures an altitude of the unmanned aerial vehicle; and an information transmitting unit that transmits, to the free space location database, camera image data captured by the camera at every predetermined altitude, and the location, direction and altitude of the unmanned aerial vehicle at time of image capturing by the camera, and based on the camera image data, and the location, direction and altitude of the unmanned aerial vehicle, the free space location database corrects 3D data including terrain information to generate free space location data. 1. A system comprising:an unmanned aerial vehicle; anda free space location database, wherein a camera that is capable of 360°-image capturing on a horizontal plane;', 'a positioning apparatus that measures a location of the unmanned aerial vehicle;', 'a direction measuring apparatus that measures a direction of the unmanned aerial vehicle;', 'an altitude measuring apparatus that measures an altitude of the unmanned aerial vehicle; and', 'an information transmitting unit that transmits, to the free space location database, camera image data captured by the camera at every predetermined altitude, and the location, direction and altitude of the unmanned aerial vehicle at time of image capturing by the camera, and, 'the unmanned aerial vehicle hasbased on the camera image data, and the location, direction and altitude of the unmanned aerial vehicle, the free space location database corrects 3D data including terrain information to generate free space location data.2. The system according to claim 1 , wherein ...

Подробнее
Номер записи: 55
25-03-2021 дата публикации

Aerial system utilizing a tethered uni-rotor network of satellite vehicles.

Номер: US20210086895A1
Автор: Justin M Selfridge
Принадлежит: Individual

A tethered uni-rotor network of multiple tethered satellite vehicles; each having lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems, operating in persistent state of rotation, driven by propulsion units on each satellite vehicle, where airfoils generate lift which supports aerial system. As system rotates, centrifugal forces pull satellite vehicles outwards, which keeps tethers taught. The tethers are attached to inboard portions of each lifting surface, which places their structural members under tension, thereby eliminating an adverse bending moment common to all traditional fixed-wing aircraft. Tethers provide large spatial separation eliminating rotor downwash field interactions, slowing system rotation rate, and permitting an ideal elliptic load distribution across wings. This reduces weight within structural members, uses higher aspect ratio wings to minimize induced drag, and employ thin-thickness high-camber airfoil profiles for superior lift-to-drag ratios, resulting in a more aerodynamically efficient aircraft, requiring less power than fixed-wing without sacrificing hover capability.

Подробнее
Номер записи: 56
21-03-2019 дата публикации

QUADCOPTER PRESSURE WASHER

Номер: US20190084677A1
Автор: VanHaelst Charles
Принадлежит:

A quadcopter pressure washer that may facilitate cleaning objects and surfaces in remote areas. The quadcopter pressure washer includes a tubular airframe, a plurality of rotary motors, a battery and controller, a pair of antennae, a signal receiver, a nozzle, a turret, a high-pressure hose, a pressure washer, a direct current or a DC power source, an alternating current/direct current or a AC/DC converter and a 120V AC power source. The quadcopter pressure washer also includes an operator control panel include additional a pair of antennae that extend upward in a programmable position from the operator control panel to transmit or receive any suitable electromagnetic signals. The additional pair of antennae utilizes state-of-the-art Doppler radar technology in electrical communication with the battery and controller. The operator control panel includes a signal emitter positioned in front of the operator control panel. 1. A quadcopter pressure washer , comprising:a tubular airframe having a planar top surface and a plurality of tubular supports, the tubular supports are attached to each corner of the planar top surface and extend outward and downward, the tubular supports have a pad placed on each end of the tubular supports to stabilize the quadcopter pressure washer while in use;a plurality of rotary motors disposed on each corner of an interior portion of the planar top surface, such that each rotary motor is coplanar with the planar top surface of the tubular airframe and has a propeller to produce lift for the quadcopter pressure washer;a battery and controller placed on a center top portion of the planar top surface, the battery and controller provide controlled electrical power to the quadcopter pressure washer, such that the battery and controller includes a non-transitory storage media that resides on the battery and controller;a pair of antennae extending upward from the battery and controller to receive any suitable electromagnetic signals, the pair of ...

Подробнее
Номер записи: 57
21-03-2019 дата публикации

CONTEXTUAL PRESENTATION SYSTEM

Номер: US20190087145A1
Автор: Chung Yeon Tae, McCown Rachel, Park Yeonjoon, Petty Bryan
Принадлежит:

A contextual presentation system is disclosed. The contextual presentation system may include a communication device. Further, the communication device may be configured for receiving the at least one presentation content from an external content providing device. Further, the contextual presentation system may include a storage device configured for storing each of at least one presentation content and at least one presentation criteria. Further, the contextual presentation system may include at least one sensor configured for sensing at least one contextual data associated with the contextual presentation system. Further, the contextual presentation system may include a processing device communicatively coupled with each of the communication device, the storage device and the at least one sensor. Further, the contextual presentation system may include at least one presentation device configured for presenting the at least one presentation content based on the analyzing. 1. A contextual presentation system comprising:at least one connection to an on-board display device configured for presenting the at least one presentation content based on the analyzing context-determining data, wherein the at least one on-board display device is communicatively coupled to a processing device;a storage device configured for storing each of the at least one presentation content, at least one audience position and at least presentation criteria that determines viewing area of display;at least one of geo-spatial, geo-imaging and angular orientation sensor configured for sensing the at least one context-determining data associated with the contextual presentation system;a processing device communicatively coupled with each of the display device, the at least one connection, the storage device and the at least one of geo-spatial, geo-imaging and angular orientation sensor, wherein the processing device is configured for analyzing the at least one context-determining data and checking ...

Подробнее
Номер записи: 58
05-05-2022 дата публикации

HYBRID UNMANNED AERIAL VEHICLE SYSTEMS WITH QUICK RELEASE TETHER ASSEMBLY

Номер: US20220135223A1
Автор: Dayan Omri, Felder Jason, Gur Ido
Принадлежит:

An unmanned aerial vehicle system includes a tether assembly, an unmanned aerial vehicle, a processor, and a memory. The unmanned aerial vehicle comprising a housing and a slider plate supported by the housing. The memory containing instructions thereon, which, when executed by the processor, cause the unmanned aerial vehicle to move the slider plate relative to the housing to selectively decouple the tether assembly from the housing.

Подробнее
Номер записи: 59
01-04-2021 дата публикации

LANDING APPARATUSES FOR UNMANNED AERIAL VEHICLES

Номер: US20210094687A1
Автор: Azzouz Michael, Brock Nelson, Carthew James, Sohmshetty Raj, Wykoff Richard
Принадлежит: FORD GLOBAL TECHNOLOGIES, LLC

Landing apparatuses for unmanned aerial vehicles are provided herein. An example UAV includes a frame; a propeller rotatably coupled to the frame; and a landing guard armature extending from the frame. A terminal end of the landing guard armature extends beyond a propeller radius of the propeller. The landing guard armature has a surface area that is sized to promote airflow around the landing guard armature. 1. An unmanned aerial vehicle , comprising:a frame;a propeller rotatably coupled to the frame; anda landing guard armature extending from the frame, wherein a terminal end of the landing guard armature extends beyond a propeller radius of the propeller, wherein the landing guard armature has a surface area that is sized to promote airflow around the landing guard armature.2. The unmanned aerial vehicle according to claim 1 , wherein landing guard armature is a thin plate comprising:a first portion that extends away from the frame in such a way that the first portion is positioned below the propeller; anda second portion that angles upwardly from the first portion.3. The unmanned aerial vehicle according to claim 2 , wherein at least one of the first portion or the second portion comprises at least one of a wheel claim 2 , a bearing claim 2 , a roller claim 2 , a low-friction coating claim 2 , or combinations thereof.4. The unmanned aerial vehicle according to claim 1 , wherein the surface area of the landing guard armature is smaller than a surface area of a blade of the propeller.5. The unmanned aerial vehicle according to claim 1 , wherein the landing guard armature is located from the propeller in such a way that a cavity or opening is formed there between to further promote airflow.6. The unmanned aerial vehicle according to claim 1 , wherein the landing guard armature has an arcuate configuration that substantially corresponds to an angled sidewall of a landing compartment of a landing apparatus which receives the unmanned aerial vehicle.7. A system claim ...

Подробнее
Номер записи: 60
05-04-2018 дата публикации

Methods, Systems, and Devices for Tether Core Diagnostics and Monitoring

Номер: US20180094619A1
Автор: Patten Elias Wolfgang, Sellers Robert S.
Принадлежит:

An example system includes a ground station, an aerial vehicle, a tether, a probe, and a control system. The tether includes a core having a strength member as well as an electrical conductor that is wound around the core. The probe is attached to the strength member so that the probe is able to measure an electrical property of at least a portion of the strength member. The control system is configured to measure the electrical property along the strength member at a predetermined measurement rate and also determine that the electrical property is outside a predetermined range. Based on the electrical property, damage to the tether core can be assessed. 1. A system , comprising:a ground station;an aerial vehicle; a core having a strength member; and', 'an electrical conductor wound around the core;, 'a tether coupled to the ground station at a first end and to the aerial vehicle at a second end, wherein the tether comprisesa probe coupled to the strength member of the tether, wherein the probe is configured to measure an electrical property of at least a portion of the strength member; at a predetermined measurement rate, measure the electrical property along the portion of the strength member of the tether; and', 'determine that the electrical property is outside a predetermined range., 'a control system configured to2. The system of claim 1 , wherein the control system is further configured to:based on the electrical property being outside the predetermined range, determine that a mechanical property of the strength member has changed.3. The system of claim 1 , wherein the control system is further configured to:based on the electrical property being outside the predetermined range, determine that the strength member of the tether is damaged.4. The system of claim 1 , wherein the control system is further configured to:determine a tension in the tether;determine a temperature of the tether; andbased on the tension, the temperature, and the electrical property ...

Подробнее
Номер записи: 61
19-03-2020 дата публикации

DEVICE FOR SUPPLYING POWER TO A WIRED DRONE

Номер: US20200091834A1
Автор: CALVEZ Frank Cyril, DE MARLIAVE Christian Marie, DUBOIS François Bernard, Guilhem, Olivier, PENET Marie Marc Hervé, Timothée
Принадлежит:

The present invention relates to a device for supplying electrical power to a wired system for a drone (). The device according to the invention includes at least one power converter () on the ground and one power converter () at the level of the drone (), regulation at the level of the converter on the ground ensures that the output voltage of the power converter () on the ground increases when the output current of the power converter () on the ground increases. The method according to the invention is intended for all wired drones, the wire () of which is used to supply electrical power to the drone (). 1. A device for supplying power to a wired drone , including at least:a power converter on the ground,a power converter at the level of the drone,a wire connecting the power converters and,{'sub': B', 'B, 'the device being characterized in that a regulation of the power converter on the ground ensures that the voltage Udelivered by the power converter on the ground increases when the current Idelivered by the power converter on the ground increases, and this over the power range of normal use of the drone.'}2. The device according to claim 1 , characterized in that the regulation compensates at least partially the voltage drop between the output of the power converter on the ground and the input of the power converter at the level of the drone claim 1 , due to the resistance Rof the wire.3. The device according to claim 1 , characterized in that the regulation ensures a voltage Uat the input of the power converter at the level of the drone claim 1 , close to the optimal operating voltage of the power converter at the level of the drone.4. The device according to claim 1 , characterized in that the voltage Udelivered by the power converter on the ground increases linearly with the current claim 1 , according to an affine law of the type U=U+RIwhere Udesignates a constant voltage claim 1 , close to the optimal power supply voltage of the power converter at the level ...

Подробнее
Номер записи: 62
14-04-2016 дата публикации

Tether Termination Systems and Methods

Номер: US20160102654A1
Автор: GilroySmith Bryan Christopher, Hachtmann Brian, Patten Elias Wolfgang
Принадлежит:

An Airborne Wind Turbine (“AWT”) may be used to facilitate conversion of kinetic energy to electrical energy. An AWT may include an aerial vehicle that flies in a path to convert kinetic wind energy to electrical energy. The aerial vehicle may be tethered to a ground station with a tether that terminates at a tether termination mount. In one aspect, the tether has a core and at least one electrical conductor. The tether core may be terminated at a first location in a tether termination mount along an axis of the termination mount, and the at least one electrical conductor may be terminated at a second location in the tether termination mount along the same axis that the core is terminated. This termination configuration may focus tensile stress on the tether to the tether core, and minimize such stress on the at least one electrical conductor during aerial vehicle flight. 1. A tether termination system , comprising: a core, and', 'at least one electrical conductor; and, 'a tether comprisinga tether termination mount comprising a rotatable termination anchor, wherein the termination anchor is coupled to the tether,wherein the core of the tether is secured in a cavity of the termination anchor at a first location,wherein the at least one electrical conductor of the tether is secured in the cavity of the termination anchor at a second location, andwherein the core of the tether and the at least one electrical conductor of the tether may rotate within the cavity of the termination anchor about an axis of the termination anchor.2. The tether termination system of claim 1 , wherein the first location is proximal to the second location.3. The tether termination system of claim 2 , wherein the core of the tether enters the cavity of the termination anchor at a proximal end of the termination anchor claim 2 , and wherein the at least one electrical conductor of the tether enters the cavity of the termination anchor on a lateral surface of the termination anchor.4. The tether ...

Подробнее
Номер записи: 63
26-03-2020 дата публикации

Aerial system utilizing a tethered uni-rotor network of satellite vehicles.

Номер: US20200094955A1
Автор: Justin Selfridge
Принадлежит: Individual

A tethered uni-rotor network of satellite vehicles, is a novel aerial system which combines the best features of both fixed-wing and rotorcraft design methodologies, while minimizing their respective deficiencies. It is made up of a central hub with multiple tethers, where each tether arm radiates outward and attaches to a satellite vehicle; each having lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The entire system operates in a state of rotation, which is driven by the propulsion units on each satellite. As the system rotates, centrifugal forces pull the satellite vehicles outward, which maintain tension on the tether arms. As the satellite vehicles move through space, the airfoils generate lift which supports each each satellite and a distributed portion of the weight of the central hub.

Подробнее
Номер записи: 64
26-03-2020 дата публикации

Aerial system utilizing a tethered uni-rotor network of satellite vehicles.

Номер: US20200094956A1
Автор: Selfridge Justin
Принадлежит:

A tethered uni-rotor network of satellite vehicles, is a novel aerial system which combines the best features of both fixed-wing and rotorcraft design methodologies, while minimizing their respective deficiencies. It is made up of a central hub with multiple tethers, where each tether arm radiates outward and attaches to a satellite vehicle; each having lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The entire system operates in a state of rotation, which is driven by the propulsion units on each satellite. As the system rotates, centrifugal forces pull the satellite vehicles outward, which maintain tension on the tether arms. As the satellite vehicles move through space, the airfoils generate lift which supports each satellite and a distributed portion of the weight of the central hub. 1. A method of dynamically controlling an aerial vehicle comprising the process of altering a translation of the aerial vehicle ,where the aerial vehicle comprises a central hub, and two or more tether arms,where each tether arm comprises a tether and a satellite vehicle,where each tether arm is secured to the central hub by its respective tether,where the tether of each tether arm is a flexible cable filament that transfers tensile forces, but has an amount of flexibility such that it does not transfer compressive forces or bending moments, between the respective satellite vehicle and the central hub,where each satellite vehicle comprises one or more propulsion units and one or more lifting surfaces, andwhere translation of the central hub is implemented by applying collective and cyclic commands to each of the satellite vehicles.2. The method of claim 1 , further comprising an action of collectively adjusting a forward velocity of each satellite vehicle claim 1 , to alter the rotation rate of the aerial vehicle claim 1 , thus changing the amount of lift generated on each winged lifting surface claim 1 , thereby invoking vertical ...

Подробнее
Номер записи: 65
26-03-2020 дата публикации

Tethered Unmanned Aerial Vehicle System

Номер: US20200094989A1
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 for use with an unmanned aerial vehicle (UAV) , the system comprising:a base;a vertically-oriented elongate structure comprising a lower end and an upper end, wherein the elongate structure includes an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end;a deployable cushioning-device coupled to the elongate structure;a tether comprising a portion that extends from the upper access-point to the UAV; anda computing system configured to cause the deployable cushioning-device to deploy.2. The system of claim 1 , wherein the base comprises:a vehicle.3. The system of claim 1 , wherein the vertically-oriented elongate structure comprises:a mast having an adjustable height.4. The system of claim 1 , wherein the deployable cushioning-device comprises:a set of one or more deployable cushioning components extending around an outer surface of the elongate structure.5. The system of claim 1 , wherein the computing system is further configured to: ...

Подробнее
Номер записи: 66
08-04-2021 дата публикации

Wide-Area Motion Imaging Systems and Methods

Номер: US20210101678A1
Автор: Bari Joseph, Bojanowski Kyle, Bowen Christopher, Cason William, Dye Victoria, Fang Cindy Y., Johnson Donald, Ross William D., White Lauren L.
Принадлежит:

A wide-area motion imaging system provides 360° persistent surveillance with a camera array that is small, light-weight, and operates at low power. The camera array is mounted on a tethered drone, which can hover at heights of up to 400′, and includes small imagers fitted with lenses of different fixed focal lengths. The tether provides power, communication, and a data link from the camera array to a ground processing server that receives, processes and stores the imagery. The server also collects absolute and relative position data from a global positioning system (GPS) receiver and an inertial measurement unit (IMU) carried by the drone. The server uses this position data to correct the rolling shutter effect and to stabilize and georectify the final images, which can be stitched together and shown to a user live or in playback via a separate user interface. 1. A system for wide-area motion imaging , the system comprising:an unmanned aerial vehicle (UAV);a camera array, attached to the UAV and operably coupled to a processor, to acquire motion images of an area around the UAV; anda remote server, communicatively coupled to the processor, to store and process the motion images acquired by the camera array.2. The system of claim 1 , wherein the UAV has a center of mass aligned with a center of mass of the camera array along a vertical centerline of the UAV.3. The system of claim 1 , wherein the camera array is configured to acquire the motion images over a 360° horizontal field of view.4. The system of claim 1 , wherein the camera array comprises:a first row of cameras, each having a first fixed focal length, to acquire a first portion of the motion images at a first spatial resolution; anda second row of cameras, each having a second fixed focal length different than the first fixed focal length, to acquire a second portion of the motion images at substantially the first spatial resolution.5. The system of claim 1 , wherein the remote server is communicatively ...

Подробнее
Номер записи: 67
03-07-2014 дата публикации

TETHERED PAYLOAD SYSTEM AND METHOD

Номер: US20140183300A1
Автор: Cote Gregory S., Giorgi Thomas, MacCulloch David
Принадлежит: L-3 Communications Corporation

A vehicle, especially a maritime vessel, is provided with an autogyro drawn by a tether. The tether contains mechanical strengthening components that enable it to securely retain the autogyro to the vehicle. The tether also contains two electrical conductors carrying different phases of AC power to the autogyro, and four optical fibers carrying optical data signals to and from the autogyro electronic payloads and avionics control circuitry. Signal converters at ends of the tether convert a wide range of electrical or wireless signals to optical data signals for transmission along the tether, and then back into the original electrical signal format for use by the autogyro or vehicle electronics. 1. A method for interaction with an environment around a vehicle , said method comprising:providing an airborne platform connected by a tether to the vehicle, said airborne platform remaining aloft at least in part by airflow relative to the airborne platform;transmitting electrical power from the vehicle to the airborne platform via a power conductor in the tether; andreceiving the electrical power in airborne electronic payload circuitry on the airborne platform, the airborne electronic payload circuitry using said electrical power to engage in the interaction with the environment; andcarrying upward optical data signals between the vehicle and the airborne platform via an optical fiber in the tether;converting the upward optical data signals received at the aerial platform to received electrical signals and providing the received electrical signals to the payload circuitry; andgenerating local electrical signals in the payload circuitry responsive to the interaction with the environment,converting the local electrical signals on the aerial platform to downward optical signals, andtransmitting the downward optical data signals to the vehicle via the optical fiber, or via another optical fiber in the tether.2. A method as described in claim 1 , wherein the airborne platform ...

Подробнее
Номер записи: 68
04-04-2019 дата публикации

Faired Tether Systems with Tail Span Sections

Номер: US20190100305A1
Автор: Patten Elias Wolfgang, Shapiro Matthew, Sicard Jérôme
Принадлежит:

Systems including tethers with one or more attached airfoil tails are described. Some systems include reversibly deformable struts that attach the tails to a tether to allow for stretch of the tether when the tether is under tension. The form of the tails may vary along the length of the tether to account for different aerodynamic design considerations. 1. A system comprising:a ground station;an aerial vehicle;a tether coupled between the ground station and the aerial vehicle, the tether comprising a tether body and an electrical conductor, wherein the tether takes the form of a first airfoil shape comprising a leading edge of the tether, a trailing edge of the tether, and a tether chord length; anda plurality of tails, wherein each tail takes the form of a respective airfoil shape comprising, respectively, a chord length, a span length, a leading edge, and a trailing edge,wherein each tail is disposed at a respective distance from the tether and coupled to the tether by at least two struts, andwherein each tail is oriented such that the leading edge of the respective tail is nearer the tether than the trailing edge of the respective tail.2. The system of claim 1 , further comprising a plurality of tail sets claim 1 , wherein each tail set contains at least one tail claim 1 , wherein each tail in a respective tail set has the same respective airfoil shape as each other tail in the respective tail set claim 1 , and wherein the airfoil shape for each tail in the respective tail set is different than the respective airfoil shapes for the tails in other tail sets.3. The system of claim 2 , wherein each tail in the respective tail set has the same respective span length as each other tail in the respective tail set claim 2 , and wherein the span length for each tail in the respective tail set is different than the respective span length for tails in other tail sets.4. The system of claim 3 , further comprising a first tail set and a second tail set of the plurality of ...

Подробнее
Номер записи: 69
04-04-2019 дата публикации

Vertical Takeoff and Landing Unmanned Aerial Vehicle (VTOL-UAV)

Номер: US20190100308A1
Автор: Simionescu Petru A.
Принадлежит:

A vertical takeoff and landing unmanned aerial vehicle (VTOL-UAV) is provided consisting of one central motor which drives one ducted fan and one or more rotors. These rotors can be coaxial with the fan, or can be located off-center being driven via a transmission. For flight control purposes, all or a portion of the air circulated by the ducted fan and/or by the central rotor is diverted through a plurality of side ducts towards the periphery of the vehicle and then downwards, each of these side duct being fitted at their peripheral ends with air-flow vectorization means. These air-flow vectorization means can be in the form of parallel vanes, and/or in the form of thrust-control buckets, which are turnable around axes perpendicular to the flow of air, and are actuated by servomotors via cables or linkages. 1. Vertical takeoff and landing unmanned aerial vehicle (VTOL-UAV) comprising a central motor which drives one ducted fan , one rotor coaxial with the fan , and a plurality of rotors that are off-centered , said VTOL-UAV being further equipped with a plurality of side ducts which direct all or part of the air moved by the ducted fan outwards , at first up , then horizontally , then downwards , said side ducts being fitted at their peripheral end with air flow vectorization means for the purpose of altitude , attitude and anti-torque control of the VTOL-UAV.2. VTOL-UAV according to where claim 1 , in a top view claim 1 , said side ducts are slightly spiraled in the same direction claim 1 , then straight claim 1 , and have an overall appearance of a polar array centered at the axis of the ducted fan claim 1 , while in their median-vertical planes said side ducts are two-by-two parallel and off-centered by a certain amount.3. VTOL-UAV according to where the side ducts are four in number claim 1 , and claim 1 , when viewed from above claim 1 , two side ducts appear spiraled clockwise claim 1 , the other two appear spiraled counterclockwise claim 1 , and all four ...

Подробнее
Номер записи: 70
02-06-2022 дата публикации

A UAV CARRIER

Номер: US20220171410A1
Автор: AMSILI Shay, Doron Eyal
Принадлежит:

A system comprising: an Unmanned Aerial Vehicle (UAV) carrier comprising a power supply, the UAV carrier connected, via respective wires, to one or more UVs, wherein: (a) each of the UVs is capable of performing maneuvers irrespective of maneuvers of the UAV carrier during performance of a mission; and (b) each of the UVs receives at least one of an electrical current from the power supply or digital data from the UAV carrier through the respective wires, during performance of the mission. 133.-. (canceled)34. A system comprising:at least one Unmanned Aerial Vehicle (UAV); anda UAV carrier configured to carry the at least one UAV from an origin to a destination; one or more first cameras; and', operate the first cameras to capture at least one image of a mission area;', 'identify, on the image, for the at least one UAV, a respective UAV target, being indicative of a destination of the respective UAV; and', 'send to the at least one UAV, respective target identification information, based on the image and on the respective UAV target;, 'a first controller configured to], 'wherein the UAV carrier comprises one or more motors;', 'one or more second cameras; and', (a) receive the respective target identification information;', '(b) operate the second cameras to capture navigation images of a sub portion of the mission area;', '(c) analyze the respective target identification information and the navigation images to determine a spatial disposition of the given UAV from the respective UAV target; and', '(d) operate one or more of the motors to direct the given UAV to the respective UAV target based on the results of the analysis., 'a second controller configured to], 'wherein the at least one given UAV comprises35. The system of claim 34 , wherein the second controller is further configured to repeat steps (b) to (d) continuously claim 34 , until the given UAV reaches the respective UAV target.36. The system of claim 34 , wherein the target identification information is a ...

Подробнее
Номер записи: 71
09-06-2022 дата публикации

SYSTEM AND METHOD FOR PROVIDING ELECTRICAL POWER TO A TETHERED AERIAL VEHICLE

Номер: US20220177159A1
Автор: Bostick Randall
Принадлежит:

An aerial vehicle electrical power system for use with a tethered aerial vehicle, and related methods are provided. The aerial vehicle electric power system includes a plurality of light-emitting diodes (LEDs) carried by an aerial vehicle. At least one electrical circuit is carried by the aerial vehicle. The at least one electrical circuit has a DC buck converter electrically in series with at least a portion of the plurality of LEDs. A tether is connected between the aerial vehicle and a power source positioned remote from the aerial vehicle. Electrical power is transmitted to the aerial vehicle and at least a portion of the plurality of LEDs through the tether. The electrical circuit minimizes variances in power supplied to the aerial vehicle and the plurality of LEDs. 1. An aerial vehicle electrical power system comprising:an aerial vehicle; at least one electrical circuit carried by the aerial vehicle, wherein the at least one electrical circuit has a DC buck converter electrically in series with at least a portion of the plurality of LEDs;', 'a tether connected between the aerial vehicle and a power source positioned remote from the aerial vehicle, wherein electrical power is transmitted to the aerial vehicle and at least a portion of the plurality of LEDs through the tether; and', 'at least one resistance device electrically in parallel to the DC buck converter,', 'wherein the at least one resistance device further comprises an amperage boost regulator, wherein the amperage boost regulator comprises at least one of: a resistor or an LED, and', 'wherein when a voltage received through the tether across the DC buck converter approaches a maximum input voltage level of the DC buck converter, the amperage boost regulator draws greater amperage thereby causing a voltage drop, wherein an input voltage remains below the maximum voltage level of the DC buck converter., 'a plurality of light-emitting diodes (LEDs) carried by the aerial vehicle;'}2. The system of claim ...

Подробнее
Номер записи: 72
27-04-2017 дата публикации

Hydraulically Propelled Drone for Delivering Firefighting fluid

Номер: US20170113787A1
Автор: Hein Kim F.
Принадлежит:

A hydraulically propelled drone is provided for delivering firefighting fluid to an elevated location. The drone comprises a housing having a primary inlet configured to receive the distal end of a fire hose, a primary outlet configured to receive the inlet end of a primary nozzle, a central passageway configured to conduct fluid from the primary inlet to the primary outlet, and at least one secondary outlet communicating with the central passageway. At least one lift nozzle communicates with the secondary outlet and is configured to direct fluid in a generally downward direction so as to produce an upward thrust on the drone housing, and at least one valve is contained within the housing and configured to control the flow of said fluid through the primary nozzle and the at least one lift nozzle nozzle. 1. A hydraulically propelled drone for delivering firefighting fluid , the drone comprising;a drone housing including a primary inlet configured to receive a distal end of the fire hose, a primary outlet, a central passageway configured to conduct fluid from said primary inlet to said primary outlet, and at least one secondary outlet communicating with said central passageway;a primary nozzle having an inlet end configured to communicate with the primary outlet of the drone housing and an outlet end configured to discharge said fluid;at least one lift nozzle communicating with said secondary outlet and configured to direct fluid in a generally downward direction so as to produce an upward thrust on the drone housing; andat least one valve contained within the drone housing and configured to control the flow of said fluid through said primary nozzle and said at least one lift nozzle.2. The hydraulically propelled drone according to claim 1 , wherein:said at least one secondary nozzle comprises at set of at least four lift nozzles, including at least a pair of front nozzles located in a front portion of said housing and at least a pair of rear nozzles located in a rear ...

Подробнее
Номер записи: 73
27-04-2017 дата публикации

Method and Apparatus for an Airborne Drone Training Track

Номер: US20170113816A1
Автор: Atchley Michael D., High Donald R., Natarajan Chandrashekar, Thompson John P.
Принадлежит:

An airborne drone training track includes both a ground track and a ceiling track. The ceiling track can be disposed above and be at least essentially aligned with the ground track. Airborne drone attachment tethers movably attach an airborne drone to each of these tracks. A lower airborne drone attachment tether movably attaches to the ground track and to a bottom portion of the airborne drone. A plurality of upper airborne drone attachment tethers movably attach to the ceiling track and to upper portions of the airborne drone. By one approach there is only one lower airborne drone attachment tether and four upper airborne drone attachment tethers. 1. An airborne drone training track comprising:a ground track;a ceiling track disposed above and at least substantially aligned with the ground track;a lower airborne drone attachment tether having a first end movably attached to the ground track and a second end configured to attach to a bottom portion of an airborne drone;a plurality of upper airborne drone attachment tethers, each having a first end movably attached to the ceiling track and a second end configured to attach to an upper portion of the airborne drone.2. The airborne drone training track of wherein the ground track comprises at least one rail and wherein the ceiling track comprises at least one rail.3. The airborne drone training track of wherein the ground track is attached to an indoor floor of a building.4. The airborne drone training track of wherein the ceiling track is attached to an indoor ceiling of the building.5. The airborne drone training track of wherein the tethers comprise a flexible material.6. The airborne drone training track of wherein the tethers are substantially nonelastic.7. The airborne drone training track of wherein at least substantially all of the outer surface of the tethers are colored to highly contrast with at least a majority of other surfaces that are located visually proximal to the airborne drone training track.8. The ...

Подробнее
Номер записи: 74
18-04-2019 дата публикации

Systems and methods for unmanned aerial vehicles

Номер: US20190112048A1
Автор: Matthew CULVER
Принадлежит: Individual

An unmanned aerial system (UAS) may comprise an unmanned aerial vehicle (UAV) configured to display advertising. The UAV may include a connector configured to attach to a display screen. The display screen may be configured to receive data from the UAV and display a message based on the data. The UAS may be controlled by a remote control, which may command the UAV to display a specific message. The remote control may control the flight of the UAV as well as the functionality of the one or more components. The components attached to the UAV, may include a camera, a robotic arm, or a display screen. The UAS may be configured to, for example, display advertising messages in a predetermined area, display advertising messages in response to the UAV determining a specific event or recognizing a specific person, and/or launch fireworks.

Подробнее
Номер записи: 75
09-04-2020 дата публикации

SYSTEM AND METHOD FOR HANDLING WIND TURBINE COMPONENTS FOR ASSEMBLY THEREOF

Номер: US20200109698A1
Автор: Bech Anton, Frederiksen Christian Skov, Jensen Ivar J.B.K., Larsen Gerner, Pedersen Gunnar K. Storgaard, Petersen Klaus Lynge
Принадлежит: VESTAS WIND SYSTEMS A/S

A method of handling a wind turbine component for assembly or maintenance, comprising moving one or more unmanned air vehicles to respective positions proximal to a wind turbine component so that the wind turbine component can be supported by the one or more unmanned air vehicles; and controlling the one or more unmanned air vehicles to lift the wind turbine component and manoeuvre said component with respect to a wind turbine. The invention extends to a system for handling a component of a wind turbine, comprising a plurality of unmanned air vehicles (UAVs); a UAV ground station computer system; and one or more lifting harnesses for carrying by the plurality of unmanned air vehicles. 1. A method of handling a wind turbine component for assembly or maintenance , the method comprising:moving one or more unmanned air vehicles to respective positions proximal to a wind turbine component so that the wind turbine component can be supported by the one or more unmanned air vehicles;controlling the one or more unmanned air vehicles to lift the wind turbine component and manoeuvre said component with respect to a wind turbine;the method further including guiding the component to the wind turbine using a guidance system.2. The method of claim 1 , wherein the guidance system is an optical guidance system claim 1 , a radar-based guidance system or a lidar based guidance system.3. The method of claim 1 , wherein each unmanned air vehicle supports the component by way of a respective support line.4. The method of claim 1 , wherein a pair of unmanned air vehicles are attached to a respective support line.5. The method of claim 1 , wherein each of the unmanned air vehicles is attached to a lifting yoke claim 1 , which is in turn attached to the component by one or more support lines.6. The method of claim 3 , wherein the support lines are slings that run underneath the component.7. The method of claim 1 , wherein the relative positions of the unmanned air vehicles are coordinated ...

Подробнее
Номер записи: 76
03-05-2018 дата публикации

Ground station and tether for unmanned aerial vehicles

Номер: US20180118374A1
Автор: Joseph Koehler, Manuel LOMBARDINI, Rashad MOARREF
Принадлежит: Stabilus Inc

An unmanned aerial vehicle system includes a ground station including a case, a power supply housed in the case, and a tether having a first end and a second end opposite to the first end. The first end of the tether is coupled to the case. The unmanned aerial vehicle system also includes a module including smart battery authentication circuitry configured to be coupled to the second end of the tether. The module is configured to be connected to an unmanned aerial vehicle. The smart battery authentication circuitry enables the unmanned aerial vehicle to receive power from the power supply housed in the case when the module is connected to the unmanned aerial vehicle.

Подробнее
Номер записи: 77
04-05-2017 дата публикации

GROUND STATION FOR AIRBORNE WIND TURBINE

Номер: US20170121036A1
Автор: Hachtmann Brian, Vander Lind Damon
Принадлежит:

An Airborne Wind Turbine (“AWT”) may be used to facilitate conversion of kinetic energy to electrical energy. An AWT may include an aerial vehicle that flies in a path to convert kinetic wind energy to electrical energy. The aerial vehicle may be tethered to an active azimuth ground station. In one aspect, the ground station has platform that is rotatable about an azimuth axis. The platform is coupled to an azimuth slewing bearing that is coupled an azimuth drive motor operable to rotate the platform about the azimuth axis. The platform may be coupled to a winch frame with an interior cavity. The winch frame may be coupled to a winch drum that is rotatable about a central axis. The winch drum may be coupled to a winch drum slewing bearing and a winch drum drive motor operable to rotate the winch drum about the central axis. 1. A ground station , comprising:a tower;a platform rotatable relative to the tower via an azimuth slewing bearing;at least one azimuth drive motor coupled to the azimuth slewing bearing and configured to rotate the platform about an azimuth axis;a winch frame coupled to the platform;a winch drum rotatable relative to the winch frame via a winch slewing bearing; andat least one winch drive motor coupled to the winch slewing bearing and configured to rotate the winch drum about a central axis;wherein the winch frame comprises an interior cavity configured to house the at least one azimuth drive motor and the at least one winch motor.2. The ground station of claim 1 , further comprising:a tether adapted to be wound about the winch drum when the winch drum is rotated in a first direction about the central axis;wherein the ground station is configured to rotate (i) the platform about the azimuth axis and (ii) the winch drum about the central axis, such that the azimuth and central rotations accumulate the tether on the winch drum in a repeating pattern.3. The ground station of claim 2 , wherein the winch drum further comprises a grooved surface about ...

Подробнее
Номер записи: 78
14-05-2015 дата публикации

AIRBORNE WIND ENERGY CONVERSION SYSTEM WITH GROUND GENERATOR AND UNORTHODOX POWER CAPTURE OR TRANSFER

Номер: US20150130188A1
Автор: Goldstein Leonid
Принадлежит:

An airborne wind energy conversion system with a ground generator and unorthodox power capture or transfer means, including such embodiments as: a system with an ultra-long flexible wing, which serves both for power harvesting and power transfer; a system with a tethered wing, the tether having an airfoil cross section in at least a substantial part of its length and participating in power harvesting; a system with a very long semi-circular wing, harvesting and transferring wind power by its helical motion; a system in which a conventional wing both harvests wind power and excites waves in the tether, the waves transferring the power. 1. A device for converting wind energy into electrical energy , comprising:a ground platform;a rotational member on the ground platform;an airborne very long flexible wing, coupled to the rotational member;wherein flexing of the wing causes significant change in the distance between at least one end of the very long airborne flexible wing and the center of the very long airborne flexible wing; andan electric generator on the ground platform, the electric generator being rotationally coupled to the rotational member.2. The device of claim 1 , wherein the very long flexible wing is adapted to harvest wind energy.3. The device of claim 2 , wherein the significant change in the distance is 10% or more.4. The device of claim 2 , wherein the very long flexible wing has a non-cambered profile along most of its length.5. The device of claim 2 , wherein the very long flexible wing has a cambered profile along most of its length.6. The device of claim 2 , wherein wing sections with a camber in one direction alternate with wing sections with a camber in the opposite direction.7. The device of claim 2 , wherein the very long flexible wing is adapted to move crosswind.8. The device of claim 2 , further comprising a belt claim 2 , coupled to the very long flexible wing; and wherein the rotational member comprises a pulley or a sheave or a sprocket; ...

Подробнее
Номер записи: 79
11-05-2017 дата публикации

TETHERED WING STRUCTURES COMPLEX FLIGHT PATH

Номер: US20170129600A1
Автор: Demers Bouchard Etienne, RANCOURT David
Принадлежит:

A vertical liftoff aircrafts system includes a plurality of unmanned wing structures configured for collective vertical liftoff; a plurality of tethers respectively connected to the plurality of wing structures; and a fuselage including a connector thereon for mechanically connecting the plurality of tethers. The fuselage includes a power pack for powering the plurality of wing structures via the plurality of tethers, whereby the plurality of wing structures is operatively interconnected to the fuselage with the plurality of tethers for lifting the fuselage. A method and a kit thereof also are disclosed. 1. A vertical liftoff aircrafts system comprising:a plurality of unmanned wing structures configured for collective vertical liftoff;a plurality of tethers respectively connected to the plurality of wing structures; anda fuselage including a connector thereon for mechanically connecting the plurality of tethers, the fuselage including a power pack for powering the plurality of wing structures via the plurality of tethers, whereby the plurality of wing structures is operatively interconnected to the fuselage with the plurality of tethers for lifting the fuselage.2. The vertical liftoff aircrafts system of claim 1 , wherein the plurality of wing structures is electrically powered.3. The vertical liftoff aircrafts system of claim 1 , wherein each wing structure is including a wing structure control unit.4. The vertical liftoff aircrafts system of claim 3 , wherein the control unit of each of the wing structure is periodically changing the flight velocity vector defined by at least one of the flight parameters.5. The vertical liftoff aircrafts system of claim 4 , wherein one of the flight parameters is selected from the group consisting of:a speed of the wing structure along the flight path;a forward tilt of the wing structure overall flight path;a sideway tilt of the wing structure overall flight path; anda geometry of the flight path.6. The vertical liftoff aircrafts ...

Подробнее
Номер записи: 80
23-04-2020 дата публикации

PERSISTENT AERIAL RECONNAISSANCE AND COMMUNICATION SYSTEM

Номер: US20200122830A1
Автор: Anderson Bretton E., Bohorquez Felipe, Filippov Misha, Greiner Helen, Jeffords Jason, Johnson Sam, Mcclure Kevin Michael, Salazar Kim, Sebesta Kenneth D., Shein Andrew M., Stoll Perry, Won Chikyung, Zaparovanny Alexey
Принадлежит:

The present invention relates to systems and methods for powering and controlling flight of an unmanned aerial vehicle. The unmanned aerial vehicles can be used in a networked system under common control and operation and can be used for a variety of applications. Selected embodiments can operate while tethered to a portable control station. A high speed tether management system can be used to facilitate both mobile and static tethered operation. Modular components provide for both tethered and fully autonomous flight operations. 1. A unmanned aerial vehicle system comprising:an unmanned aerial vehicle (UAV) having an onboard computer;a tether communicatively connected to the aerial vehicle; anda tether management system having a tether controller and a moveable arm that deploys the tether from a tether retainer during flight of the aerial vehicle.2. The system of wherein the moveable arm rotates around an axis of a stationary tether winding element.3. The system of further comprising a base controller wherein the base controller comprises a high voltage source and an Ethernet link claim 1 , the tether management system and base controller being mounted in a portable housing.4. The system of further comprising a modular unit that attaches to the tethered aerial vehicle.5. The system of further comprising a motor coupled to the moveable arm to actuate movement of the arm about the tether retainer that includes a fixed spool on which the tether is wound.6. The system of wherein the tether comprises a wire and an optical fiber.7. The system of further comprising a launch vehicle on which the tether management system is mounted such that the aerial vehicle can be launched from the launch vehicle.8. The system of further comprising a base controller having at least one processor and a voltage source that are mounted in a control station housing.9. The system of wherein the tether management system is mounted on a plate in the control station housing.10. The system of ...

Подробнее
Номер записи: 81
19-05-2016 дата публикации

SYSTEMS AND METHODS FOR ATTITUDE CONTROL OF TETHERED AEROSTATS

Номер: US20160139601A1
Автор: Glass Benjamin W., Goessling Andrew D., Vermillion Christopher R.
Принадлежит:

A control system for a tethered aerostat is provided, where at least one rotational and at least one translational degree of freedom are controlled to setpoints through the variation of tether lengths by an actuator system. The term tether includes a single tether, a tether group or a sub section of tether controlled by an individual actuator. Accurate rotational and translational control is essential for the successful operation of an aerostat under several applications, including surveillance, weather monitoring, communications, and power generation. For a given use case, the controller can be constructed and arranged to manage the tradeoff between several key performance characteristics, such as transient performance, steady-state pointing accuracy, tether tension regulation, and power generation. 1. A system for controlling a tethered aerostat , the system comprising:a base station including an actuation platform having an actuator system that is secured to the tethered aerostat via a plurality of tethers;the actuation platform having at least two actuators that each respectively control a control variable of at least some of the plurality of tethers; anda control unit that provides input to at least one of the at least two actuators to control a control variable of the controlled tethers.2. The system as set forth in wherein the control variable is tether payout length.3. The system as set forth in wherein the control variable is tether release speed.4. The system as set forth in wherein the control variable is tether acceleration.5. The system as set forth in wherein the control variable is tether tension.6. A system for controlling a tethered aerostat claim 1 , the system comprising:a base station including an actuation platform having an actuator system that is secured to the tethered aerostat via a plurality of tethers;the actuation platform having at least two actuators that each respectively control a control variable of at least some of the plurality of ...

Подробнее
Номер записи: 82
18-05-2017 дата публикации

SYSTEM FOR STARTING AND LANDING A FLIGHT-CAPABLE WING CONSTRUCTION

Номер: US20170138346A1
Автор: Gebhardt Christian, KÖVESDI Peter
Принадлежит:

A wind-driveable wing construction () which comprises a tether line (), which is designed to connect the wing construction to a ground station () during operation, and one end of the tether line () being attached to the wing construction; and a bridle line system comprising a multiplicity of bridle lines (). At least two bridle lines having an end connected to the wing construction and at least one bridle line has an end connected to the tether line (). The bridle line system is detachably connected to the tether line, during operation. The tether line () has a first sleeve () which is attached to the tether line, the bridle line system has a second sleeve (), to which the at least one bridle line () is connected. A capture cable is passed through the second sleeve, and the sleeves are designed to form a detachable connection. 130-. (canceled)3130. A flight-capable , wind-driveable wing construction () comprising:{'b': 40', '10', '40, '(i) a tether line (), which is designed to connect the wing construction to a ground station () during operation, and one end of the tether line () being attached to the wing construction; and'}{'b': 70', '71', '40, '(ii) a bridle line system comprising a multiplicity of bridle lines (, ), where at least two bridle lines having an end connected to the wing construction and at least one bridle line having an end which is connected to the tether line (), and the bridle line system being detachably connected to the tether line, during operation;'}{'b': 40', '130', '120', '70', '71, 'wherein the tether line () has a first sleeve () which is attached to the tether line, the bridle line system has a second sleeve (), to which the at least one bridle line (, ) is connected, and, during operation, a capture cable is passed through the second sleeve, and the first and second sleeves are designed to form a detachable positive or non-positive connection during operation.'}32120171181130171181130. The wing construction according to claim 31 , ...

Подробнее
Номер записи: 83
26-05-2016 дата публикации

TETHERED AERIAL SYSTEMS FOR DATA GATHERING

Номер: US20160144958A1
Автор: Peverill James, Woodworth Adam
Принадлежит:

A tethered unmanned aerial vehicle (“UAV”) may be outfitted with a sensor payload for data gathering. The tethered UAV may be tethered to a ground station for constricting the flight space of the UAV while also providing the option for power delivery and/or bidirectional communications. The tethered UAV's flight path may be extended by introducing one or more secondary UAVs that cooperate to extend the horizontal flight path of a primary UAV. The ground station, which may be coupled with the tethered aerial vehicle, may comprise a listening switch configured to determine a condition of the tether such that the supply of power to the tether may be terminated when tether damage or a tether severance is detected. 1. A safety method for use with a tethered aerial vehicle having a tether with a power cable , the safety method comprising the steps of:transmitting electrical power from a ground station to the tethered an aerial vehicle through the tether power cable;receiving at the ground station, via the tether, a tether line condition electrical signal;listening, with a listening device disposed at the ground station, to the tether line condition electrical signal to determine whether the tether line condition signal is at a predetermined acceptable level;if the tether line condition electrical signal is determined to be at the predetermined acceptable level, continue to monitor the line condition signal;if the tether line condition electrical signal is determined to be below the predetermined acceptable level, determine whether the tether is severed;if the tether is determined to be not severed, instruct the tethered aerial vehicle to (i) land at a ground station and (ii) reset the listening device;if the listening device resets, continue to listen to the line condition electrical signal;if the listening device does not reset, continue to land the tethered aerial vehicle at the ground station;if the tether is determined to be severed, (i) cut power to the tether, (ii) ...

Подробнее
Номер записи: 84
10-06-2021 дата публикации

SYSTEMS AND METHODS FOR MODULAR UNMANNED VEHICLES

Номер: US20210171198A1
Автор: Pegg Albert, Prsa Steven Andrew, Wennemer Dietmar Frank
Принадлежит:

An unmanned vehicle (UV) is provided. The UV comprises an aircraft component, an interposer component electrically and mechanically coupled to the aircraft component, and a payload component electrically and mechanically coupled to the interposer component. The interposer component comprising a processor and a memory storing instructions which when executed by the processor configured the processor to receive a communication from one of the aircraft component or the payload component, and sent the communication to the other of the aircraft component or the payload component. 1. An unmanned vehicle (UV) comprising:an aircraft component;an interposer component communicatively and mechanically coupled to the aircraft component; anda payload component communicatively and mechanically coupled to the interposer component; a processor; and', receive a communication from one of the aircraft component or the payload component; and', 'send the communication to the other of the aircraft component or the payload component., 'a memory storing instructions which when executed by the processor configure the processor to], 'wherein the interposer component comprises'}2. The UV as claimed in claim 1 , wherein the aircraft claim 1 , interposer and payload components are communicatively coupled by at least one of:an electrical contact connection;a tether wire connection; ora wireless radio connection.3. The UV as claimed in claim 1 , wherein one of the UV or interposer is communicatively coupled to a ground station via an electrical tether wire connection.4. The UV as claimed in claim 1 , wherein:the aircraft component comprises an aircraft-payload connector;the interposer component comprises an interposer-aircraft connector; andwherein the aircraft component is mechanically coupled to the interposer component via a connection between the aircraft-payload connector and the interposer-aircraft connector.5. The UV as claimed in claim 1 , wherein:the interposer component comprises an ...

Подробнее
Номер записи: 85
25-05-2017 дата публикации

SYSTEMS AND METHODS FOR POWERING AN AIRBORNE VEHICLE FROM A GROUND POWER SUPPLY

Номер: US20170144754A1
Автор: Brandt Randy L., Limvorapun Suhat
Принадлежит:

Systems and methods for powering an airborne transport vehicle from a ground power supply are provided. One system is a hovercraft power system having a ground power supply coupled with at least one on-board DC-DC power converter, wherein the on-board DC-DC power converter is positioned on-board a hovercraft. The hovercraft power system further includes a power cord tethered to the hovercraft, wherein the power cord is capable of delivering at least 100 kilowatts (kW) of power from the ground power supply to the hovercraft. The hovercraft power system also includes a tether dispenser configured to dispense or retract the power cord tethered to the hovercraft. 1. A hovercraft power system , the system comprising:a ground power supply coupled with at least one on-board DC-DC power converter, the on-board DC-DC power converter positioned on-board a hovercraft;a power cord tethered to the hovercraft, wherein the power cord is capable of delivering at least 100 kilowatts (kW) of power from the ground power supply to the hovercraft; anda tether dispenser configured to dispense or retract the power cord tethered to the hovercraft.2. The hovercraft power system of claim 1 , wherein the ground power supply comprises a hydrogen fuel cell.3. The hovercraft power system of claim 1 , wherein the ground power supply comprises a diesel engine.4. The hovercraft power system of claim 1 , further comprising a heat sink coupled adjacent to the at least one on-board DC-DC power converter.5. The hovercraft power system of claim 4 , wherein the heat sink does not comprise a heat pipe.6. The hovercraft power system of claim 1 , wherein the at least one on-board DC-DC power converter in mounted such that airflow from one or more propellers of the hovercraft cools the at least one on-board DC-DC power converter.7. The hovercraft power system of claim 1 , wherein the tether dispenser comprises a reel that dispenses and retracts the power cord at a preselected tension.8. The hovercraft power ...

Подробнее
Номер записи: 86
25-05-2017 дата публикации

TETHER ORIENTATION SENSOR FOR CONTROLLING THE POSITION OF A TETHERED AIRCRAFT

Номер: US20170147007A1
Автор: Burroughs Daniel, Ducharme Alfred D., Whitaker Lucas C.
Принадлежит:

An unmanned aerial vehicle has a substrate. A tether sensor is mounted on the substrate. The tether sensor determines an orientation of the tether relative to the substrate. A micro controller, receiving the measured orientation from the tether sensor, determines an orientation of the tether relative to the substrate, and as a function of the orientation, determines a corrective value and outputs the corrective value to the unmanned aerial vehicle as at least one of a roll output and a pitch output control signal. 1. An unmanned aerial vehicle comprising:a substrate;a tether sensor mounted on the substrate, the tether sensor determining an orientation of the tether relative to the substrate; anda micro controller, receiving the measured orientation from the tether sensor, and determining an orientation of the tether relative to the substrate, and as a function of the orientation, determining a corrective value and outputting the corrective value to the unmanned aerial vehicle as at least one of a roll output and a pitch output control signal.2. The unmanned aerial vehicle of claim 1 , wherein the tether sensor includes at least three strain sensors;a tether connection being disposed along at least one axis formed by at least a first strain sensor and a second strain sensor of the three or more strain sensors, each strain sensor measuring a strain applied by the tether to the tether sensor; andthe micro controller, receiving the measured strain from each respective strain sensor, determining a net strain as a function of a strain measured at each strain sensor, and as a function of the net strain, determining a corrective value and outputting the corrective value as at least one of a roll output and a pitch output control signal.3. The unmanned aerial vehicle of claim 2 , wherein the tether is secured at a first end at the tether connection and add a second end at a position fixed relative to the ground.4. The unmanned aerial vehicle of claim 2 , wherein the ...

Подробнее
Номер записи: 87
07-05-2020 дата публикации

TACTICAL AERIAL PLATFORM

Номер: US20200140071A1
Автор: Heinen Gregory W., Miller Charles, Morris Peter B., Shea John P.
Принадлежит:

An aerial platform having motive devices for obtaining and maintaining loft of the aerial platform, the motive devices being pivotable relative to a wing of the aerial platform for aerial maneuvering of the aerial platform while generally maintaining stable disposition of the wing relative to the ground. The motive devices may include blades having selectively adjustable pitch for varying output force of respective motive devices. The aerial platform may further include one or more bladed turbines outwardly coupled to the wing and drivable by wind for generating power for the aerial platform. In some cases, the aerial platform may be tethered via a flexible power cable to a power source. 1. An aerial platform , comprising:a central section including at least two motive devices for providing loft of the aerial platform;an outer wing extending at least partially about the central section; anda gimballing element interconnecting the central section and the outer wing for allowing rotation of the central section relative to the outer wing about a pivot axis of the gimballing element;wherein in the at least two motive devices include a forward motive device and an aft motive device, with the pivot axis between the forward motive device and the aft motive device.2. (canceled)3. The aerial platform of claim 1 , wherein the at least two motive devices are oppositely disposed to one another about the gimballing element.4. The aerial platform of claim 1 , wherein each of the motive devices includes a plurality of blades claim 1 , each blade of a respective plurality of blades being synchronously rotatable about a respective blade axis extending longitudinally along each respective blade.5. The aerial platform of claim 1 , wherein each of the motive devices includes blades having a plane of rotation claim 1 , wherein the planes of rotation of the motive devices are fixed relative to one another.6. The aerial platform of claim 1 , wherein each of the motive devices includes ...

Подробнее
Номер записи: 88
17-06-2021 дата публикации

PAYLOAD RELEASE SYSTEM FOR VERTICAL LAUNCH

Номер: US20210179248A1
Автор: Tasovski Vasil
Принадлежит: LOON LLC

The technology provides a launch rig structure capable of filling a very large balloon envelope while the balloon is arranged vertically. The filled balloon is capable of staying aloft in the stratosphere with its payload for months or longer. The launch rig structure is configured to rotate up to 360° in response to current wind conditions. It includes an integrated lifting boom and gas handling system to fill the envelope. A payload release assembly is configured to couple with a rigid connection member of the balloon, enabling the envelope to be filled while in a vertical orientation. The payload release assembly is part of a launch cart that is positioned within the interior space of the launch rig. A gripper assembly engages with the rigid connection member. Once the envelope is filled, the gripper assembly disengages from the connection member so that the balloon floats away from the launch rig. 1. A payload release assembly for securing a lighter-than-air platform during a launch operation , the lighter-than-air platform including a balloon envelope and a payload coupled to the balloon envelope , the payload release assembly comprising:a launch arm assembly having a first end and a second end remote from the first end, the first end engageable to a launch cart that is configured to store the balloon envelope, the launch arm assembly being configured to actuate between a pre-launch position and a launch position; anda gripper assembly operatively coupled to the second end of the launch arm, the gripper assembly being configured to secure a connection member of the lighter-than-air platform, the connection member having a shaft member and a crossbar, the gripper assembly having a first section configured to receive the shaft member and a second section configured to secure the crossbar prior to launching.2. The payload release assembly of claim 1 , wherein the first section of the gripper assembly includes a support block with a pair of fingers adapted to ...

Подробнее
Номер записи: 89
11-06-2015 дата публикации

Systems and Apparatus for Tether Termination Mount for Tethered Aerial Vehicles

Номер: US20150158585A1
Автор: Hachtmann Brian, Hardham Corwin, Nelson Rob, Vander Lind Damon
Принадлежит:

Wind energy systems, such as an Airborne Wind Turbine (“AWT”), may be used to facilitate conversion of kinetic energy to electrical energy. An AWT may include an aerial vehicle that flies in a path to convert kinetic wind energy to electrical energy. The aerial vehicle may be tethered to a ground station with a tether that terminates at a tether termination mount. In one aspect, the tether may be a conductive tether that can transmit electricity and/or electrical signals back and forth between the aerial vehicle and the ground station. The tether termination mount may include one or more gimbals that allow for the tether termination mount to rotate about one or more axis. In a further aspect, the tether termination mount may include a slip ring that allows for rotation of the tether without twisting the tether. 1. A tether termination mount , comprising: a first gimbal, comprising a primary bearing system and wherein the first gimbal is configured for movement substantially about a primary axis;', 'a second gimbal, comprising a secondary bearing system and wherein the second gimbal is configured for movement substantially about a secondary axis;, 'a gimbal system, comprisinga slip ring, comprising a stationary portion and a rotatable portion, wherein the stationary portion of the slip ring is coupled to the second gimbal, wherein the stationary portion and rotatable portion are electrically coupled, and wherein the rotatable portion is electrically coupled to a tether; anda spindle, comprising a proximate spindle end and a distal spindle end, wherein the spindle is configured to constrain a portion of the tether, and wherein the proximate spindle end is coupled to the rotatable portion of the slip ring.2. The spindle of claim 1 , further comprising a spindle bearing system claim 1 , wherein the bearing system is located at the distal spindle end claim 1 , and wherein the bearing system provides a rotatable surface against which the tether may rotate relative to the ...

Подробнее
Номер записи: 90
11-06-2015 дата публикации

Systems and Apparatus for Tether Termination Mount for Tethered Aerial Vehicles

Номер: US20150158586A1
Автор: Hachtmann Brian, Hardham Corwin, Nelson Rob, Vander Lind Damon
Принадлежит:

Wind energy systems, such as an Airborne Wind Turbine (“AWT”), may be used to facilitate conversion of kinetic energy to electrical energy. An AWT may include an aerial vehicle that flies in a path to convert kinetic wind energy to electrical energy. The aerial vehicle may be tethered to a ground station with a tether that terminates at a tether termination mount. In one aspect, the tether may be a conductive tether that can transmit electricity and/or electrical signals back and forth between the aerial vehicle and the ground station. The tether termination mount may include one or more gimbals that allow for the tether termination mount to rotate about one or more axis. In a further aspect, the tether termination mount may include a slip ring that allows for rotation of the tether without twisting the tether. 1. An apparatus comprising: a first gimbal, comprising a primary bearing system and wherein the first gimbal is configured for movement substantially about a primary axis;', 'a second gimbal, comprising a secondary bearing system and wherein the second gimbal is configured for movement substantially about a secondary axis;, 'a gimbal system, comprisinga slip ring, comprising a stationary portion and a rotatable portion, wherein the stationary portion of the slip ring is coupled to the second gimbal, wherein the stationary portion and rotatable portion are electrically coupled, and wherein the rotatable portion is electrically coupled to a tether; anda spindle, comprising a proximate spindle end and a distal spindle end, wherein the spindle is configured to constrain a portion of the tether, and wherein the proximate spindle end is coupled to the rotatable portion of the slip ring.2. The apparatus of claim 1 , further comprising a spindle bearing system claim 1 , wherein the bearing system is located at the distal spindle end claim 1 , and wherein the bearing system provides a rotatable surface against which the tether may rotate relative to the spindle.3. The ...

Подробнее
Номер записи: 91
11-06-2015 дата публикации

Ground Station with Shuttled Drum for Tethered Aerial Vehicles

Номер: US20150158600A1
Автор: Brian Hachtmann, Damon Vander Lind
Принадлежит: Google LLC

A system may include an aerial vehicle, a perch platform configured to receive the aerial vehicle, and a ground station coupled to the aerial vehicle via a tether. The ground station may include a winch including a winch drum configured to move laterally and spin in a manner such that the tether is wound onto on the winch drum in a repeating pattern, possibly utilizing a fixed position levelwind. The system may additionally include a tower around which the winch and the perch platform can rotate about a vertical axis relative to the tower. The system may further utilize the tether forces on the levelwind to help move the perch platform around the vertical axis or be driven actively by a motor.

Подробнее
Номер записи: 92
14-05-2020 дата публикации

Tethered Drone System

Номер: US20200148348A1
Автор: Bradley Aiden Nathaniel, Bradley Nathaniel T., Paugh Joshua S.
Принадлежит: PearTrack Security Systems, Inc.

A tethered drone system and method includes a tethered drone and a tether. The tether includes a conductor to communicate at least power and control signals. The tethered drone system further includes a control system configured to receive the tethered drone. The control system provides power for the tethered drone. The control system includes a user interface for managing the control signals. 1. A tethered drone system , comprising:a tethered drone including a tether, wherein the tether includes a conductor to communicate at least power and control signals; anda control system configured to receive the tethered drone, wherein the control system provides power for the tethered drone, and wherein the control system includes a user interface for controlling the control signals.2. The tethered drone system of claim 1 , wherein the tether communicates a liquid from the control system to an outlet extending from the drone.3. The tethered drone system of claim 1 , further comprising:one or more cameras integrated with the drone.4. The tethered drone system of claim 1 , further comprising:a plurality of propellers providing lift and throttle to the tethered drone.5. The tethered drone system of claim 1 , wherein the control system is a utility truck.6. The tethered drone system of claim 1 , wherein the user interface includes controls for altitude and directional controls.7. The tethered drone system of claim 1 , wherein the control system includes a landing pad for landing the tethered drone.8. The tethered drone system of claim 1 , wherein the control system further includes a generator for powering the drone claim 1 , and a pump for pumping fluid up through the tether.9. The tethered drone system of claim 1 , wherein the tethered drone includes a back-up battery in case the tether fails.10. The tethered drone system of claim 1 , wherein the control vehicle includes a cradle for launching and storing the tethered drone.11. The tethered drone system of claim 1 , wherein ...

Подробнее
Номер записи: 93
23-05-2019 дата публикации

Multi-Tether Clock-Face De-Twist

Номер: US20190154003A1
Автор: Charles Nordstrom
Принадлежит: Makani Technologies LLC

Airborne turbine systems with multiple aerial vehicles connected via multiple tethers to a shared ground station are disclosed. The ground station includes a multi-tether clock-face de-twist apparatus with a de-twist element that rotates along with the looping aerial vehicles. The de-twist element may be passively rotated through torque applied via the tethers or may be actively rotated via a drive system.

Подробнее
Номер записи: 94
08-06-2017 дата публикации

GATHERING DATA FROM MACHINE OPERATING AT WORKSITE

Номер: US20170161972A1
Автор: Moloney Neil J., Natale Nicholas A.
Принадлежит: CATERPILLAR INC.

A data gathering system associated with a machine operating at a worksite is provided. The data gathering system includes a base station located at the worksite and an unmanned aerial device (UAD) in communication with the base station and the machine. The UAD includes an image capturing unit for capturing images of an area around the machine and a controller in communication with the image capturing unit. The controller receives a first input from the machine indicative of one or more machine parameters, and receives a second input from the image capturing unit indicative of the images of the area around the machine. The controller further determines multiple operational parameters associated with an operation of the machine based on the first input and the second input, and transmits the determined multiple operational parameters to at least one of the machine and the base station. 1. A data gathering system associated with a machine operating at a worksite , the data gathering system comprising:a base station located at the worksite; and an image capturing unit configured to capture one or more image of an area around the machine; and', receive a first input from the machine via the cable, the first input indicative of one or more machine parameters;', 'receive a second input from the image capturing unit, the second input indicative of the one or more images of the area around the machine;', 'determine multiple operational parameters associated with an operation of the machine based on the first input and the second input; and', 'transmit the determined multiple operational parameters to at least one of the machine and the base station., 'a controller in communication with the image capturing unit, the controller configured to], 'an unmanned aerial device communicatively coupled to the machine using a cable, and configured to communicate with the base station, wherein the cable is configured to receive electric power from the machine to propel the unmanned ...

Подробнее
Номер записи: 95
14-06-2018 дата публикации

POWER GENERATING WINDBAGS AND WATERBAGS

Номер: US20180163702A1
Автор: SIA Yik Hei
Принадлежит:

A method of using a bagged power generation system comprising windbags and waterbags integrated with drones and adapting drone technologies for harnessing wind and water power to produce electricity. An extremely scalable and environmentally friendly method, system, apparatus, equipment, techniques and ecosystem configured to produce renewable green energy with high productivity and efficiency. 1222. A system for generation of electrical power by means of a deep sea diving energy generator placed in sea water () comprising:{'b': 51', '230, 'a drive unit () comprised of a underwater drone (;'}{'b': 200', '50', '33, ') having at least one tether line (), the tether line includes a plurality of waterbags connected in series to the tether line and a retract line () attached to an end of the tether line, the tether line attached to the underwater drone;'}{'b': 55', '54, 'a driven unit () having a body that includes a generator (), the driven unit attached to the underwater drone by the at least one tether line;'}wherein tensile force exerted on the waterbags by the sea water current is transferred via the tether line to the driven unit to generate electricity;wherein the underwater drone controls the system and depowers the system by turning the retract line.2525349. The system of wherein the driven unit further includes a line reel drum () claim 1 , a gearbox () claim 1 , a retract motor () claim 1 , and means for supporting the driven unit claim 1 , wherein the retract motor is operable to reel in and retract back the tethers and waterbag and the drive unit is adapted to turn the retract line. This application is a continuation of U.S. application Ser. No. 15/630,670, filed Jun. 22, 2017, which is a continuation-in-part of U.S. application Ser. No. 15/270,500, filed Sep. 20, 2016, now U.S. Pat. No. 9,698,652, which is a continuation of U.S. application Ser. No. 14/976,855, filed Dec. 21, 2015, now U.S. Pat. No. 9,447,775, which is a continuation of U.S. application Ser ...

Подробнее
Номер записи: 96
30-05-2019 дата публикации

DUAL-KITE AERIAL VEHICLE

Номер: US20190161183A1
Автор: Hagianu Mihai
Принадлежит:

Systems and methods are disclosed for implanting a dual-kite aerial vehicle including a first kite apparatus, a second kite apparatus, and a tether extending between the first and second kite apparatuses. In particular, the disclosed systems include a first kite apparatus including a first flight controller that maintains flight at a first altitude. The disclosed system further includes a second kite apparatus including a second flight controller that maintains flight at a second altitude. The flight controllers can cooperatively maintain a gradient air movement between the first and second altitudes by extending or retracting the tether to modify a difference in the air movements between the first and second kite apparatuses. The systems described herein additionally include components for generating electrical energy from the gradient air movement to extend a flight time of the dual-kite aerial vehicle. 1. A dual-kite aerial vehicle , comprising:a first kite apparatus;a second kite apparatus coupled to the first kite apparatus by a tether extending between the first kite apparatus and the second kite apparatus; and a first flight controller coupled to one or more actuators of the first kite apparatus to control a flight path of the first kite apparatus; and', 'a second flight controller coupled to one or more actuators of the second kite apparatus to control a flight path of the second kite apparatus; and, 'a flight control system comprisingwherein the flight control system maintains a gradient air movement between a first air movement at a first altitude of the first kite apparatus and a second air movement at a second altitude of the second kite apparatus, wherein the first altitude is higher than the second altitude.2. The dual-kite aerial vehicle of claim 1 , wherein the dual-kite aerial vehicle comprises a single tether extending between the first kite apparatus and the second kite apparatus.3. The dual-kite aerial vehicle of claim 1 , further comprising a ...

Подробнее
Номер записи: 97
11-09-2014 дата публикации

Autonomous aircraft

Номер: US20140251743A1
Автор: James J. Childress, John J. Viniotis
Принадлежит: Boeing Co

Systems and methods to launch an aircraft are disclosed. In one embodiment, a system comprises an electrically powered buoyant aircraft, a control system to maneuver the aircraft and a tether adapted to couple to the aircraft and to a ground-based power supply to provide power to the aircraft while the aircraft is coupled to the tether, wherein the aircraft can disconnect autonomously from the tether in response to a command signal. Other embodiments may be described.

Подробнее
Номер записи: 98
25-06-2015 дата публикации

Systems and Apparatus for Winch Drum Mechanism

Номер: US20150175277A1
Автор: Hachtmann Brian
Принадлежит:

Wind energy systems, such as an Airborne Wind Turbine (“AWT”), may be used to facilitate conversion of kinetic energy to electrical energy. An AWT may include an aerial vehicle that flies in a path to convert kinetic wind energy to electrical energy. The aerial vehicle may be tethered to a ground station via a tether that terminates at a tether termination mount. In one aspect, the ground station may have a motor that may be used, for example, as a winch motor to turn the drum to assist in deployment and/or refraction of the tether and AWT. It may be desirable to be able to switch from an engaged and disengaged condition of the motor. For example, it may be desirable to disengage the motor to help reduce wear on the drivetrain and/or to help reduce loads on the drivetrain. 1. A winch drum assembly , comprising:a base platform;a support bracket coupled to the base platform;a winch drum rotatably coupled to the support bracket via a drive shaft, wherein the winch drum acts as a rotational load on the drive shaft;a tether with a first end coupled to the winch drum, wherein the tether is configured to be wound or unwound from about the winch drum as the winch drum rotates;a drivetrain coupled to the drive shaft; a motor drive;', 'a motor output shaft coupled to the drivetrain; and', 'a motor housing including at least one protrusion, wherein the motor housing is configured to rotate about the motor output shaft and relative to the support bracket; and, 'a motor comprisinga stop block located in proximity to the motor housing such that rotation of the motor housing in a first direction causes the at least one protrusion to contact the stop block and prevent further rotation of the motor housing about the motor output shaft in the first direction.2. The assembly of claim 1 , wherein the stop block is further configured such that rotation of the motor housing in a second direction opposite the first direction causes the at least one protrusion to contact the stop block and ...

Подробнее
Номер записи: 99
25-06-2015 дата публикации

Path Based Power Generation Control for an Aerial Vehicle

Номер: US20150177737A1
Автор: Jensen Kenneth, Lind Damon Vander
Принадлежит:

Methods and systems described herein relate to power generation control for an aerial vehicle. An example method may include operating an aerial vehicle in a crosswind-flight orientation substantially along a first flight path to generate power. The first flight path may include a substantially circular path that allows the aerial vehicle to generate the power. While the aerial vehicle is in the crosswind-flight orientation the method may include determining to reduce the power being generated by the aerial vehicle, and responsive to the determination, determining a second flight path that will reduce the power generated by the aerial vehicle when operating on the second flight path. Once determined, the aerial vehicle may operate substantially along the second flight path. 1. A method comprising:operating an aerial vehicle in a crosswind-flight orientation substantially along a first flight path to generate power, wherein the first flight path is constrained by a tether that defines a tether sphere having a radius based on a length of the tether, wherein the aerial vehicle is coupled to a ground station through the tether, and wherein the first flight path is substantially on the tether sphere and includes a substantially circular path that allows the aerial vehicle to generate the power; and determining to reduce the power being generated by the aerial vehicle;', 'responsive to the determination, determining a different second flight path that will reduce the power generated by the aerial vehicle when operating on the second flight path, wherein the different second flight path is substantially on the tether sphere; and', 'operating the aerial vehicle substantially along the different second flight path., 'while the aerial vehicle is in the crosswind-flight orientation2. The method of claim 1 , wherein determining to reduce the power being generated by the aerial vehicle comprises determining to reduce the power being generated based on a temperature of a ...

Подробнее
Номер записи: 100