76results about "Conjoint controls" patented technology

Towed aerodynamic platforms approach the behavior of flat plate airfoils to achieve high lift-to-drag (L:D) performance when operated at low pitch angles. A lead aircraft may tow multiple platforms to form train units. Low form drag and high L:D enable solar aircraft that are more robust and faster than approaches extending wingspan rather than extending the length of the aerial train. Applications extend beyond solar aircraft and include vehicles towed along an overhead monorail system and aerial drones.

To control a group behavior while reducing the complexity of reward design.SOLUTION: A control system includes: a second learning unit 12 that performs adversarial learning of a generative model having a generator 121 that generates pseudo-policy data similar to true policy data, using a policy of a course that the first UAV2a should take sequentially from its current position obtained by learning by a first learning unit 11 as the true policy data, and a classifier 122 that distinguishes between the pseudo-policy data generated by the generator 121 and the true policy data; a generation unit 14 that generates the pseudo-policy data similar to the true policy data by using a learned generator 121' obtained by the adversarial learning of the second learning unit 12; and a setting unit 15 that sets information including the pseudo-policy data generated by the generation unit 14 to each moving body UAV2 as control information for controlling the courses of multiple UAV2s.SELECTED DRAWING: Figure 1

A lifting system includes an unmanned aerial vehicle, a thruster device, a first wire, a first reel, a second thruster device, a second wire, a second reel, and a controller. When the unmanned aerial vehicle is in a position separated from the ground, the controller detaches the first thruster device and the second thruster device from the unmanned aerial vehicle, causes the first reel to reel out the first wire, detaches the second thruster device from the first thruster device, and causes the second reel to reel out the second wire.

An electric flight control system comprising an actuation subassembly, having three external duplex computers for controlling an electric actuator. The electric actuator has three stators electrically connected to three respective switching devices, the switching devices being electrically connected to a same internal simplex computer of the electric actuator, each switching device being connected to a respective external duplex computers, each switching device being configured to connect the internal simplex computer or respective external duplex computer to the associated stator, the internal simplex computer being self-monitored and communicating with the three external duplex computers.

The application discloses a dual-redundancy steering engine control system for a UAV and a configuration method, comprising M steering engine controllers and N steering engines; the M steering engine controllers are connected with a flight pipe computer through a bus; each of the steering engine controllers has n channels and is connected with n steering engines; N>n, N>=M; the steering engines comprise dual-redundancy linear steering engines, dual-redundancy rotary steering engines, single-redundancy linear steering engines and single-redundancy rotary steering engines; wherein the dual-redundancy linear steering engines are connected with one channel of two different steering engine controllers respectively, the dual-redundancy rotary steering engines are connected with one channel of two different steering engine controllers respectively, and the single-redundancy linear steering engines and the single-redundancy rotary steering engines are connected with one channel of corresponding steering engine controllers. The dual-redundancy isosmorphism design is adopted, the two redundancies do not interact, work independently, the structure is simple, and the reliability is high.

Systems, apparatuses, methods, and computer program products are provided herein. For example, a method is described herein includes identifying aviation operations program data representative of one or more aviation operations programs. In some embodiments, the method includes configuring the one or more aviation operations programs in accordance with at least one of a plurality of aviation implementation states. In some embodiments, the method includes providing aviation mission data to an external aviation mission device. In some embodiments, the method includes receiving, from the external aviation mission device, first program implementation data in response to an aviation mission activation event. In some embodiments, the method includes initiating performance of one or more aviation mission actions based on the first program implementation data.

An aircraft control system 100 including a control assembly 110 having control units, including a first control unit 130 for controlling actuation of the aircraft component during a first time period, using electrical resource 512 from a first electrical resource device 510, and a second control unit 140 for controlling actuation of the aircraft component during a second time period, and a switch mechanism 120 for switching control of the actuation of the aircraft component between the first and second control units, wherein the switch mechanism has a first electrical resource device status input 513 for indicating the status of the first electrical resource device 510 and wherein, the switch mechanism is configured to switch control between the first 130 and second 140 control units based on the first electrical resource device status input 513.

The present application belongs to the field of structure design control, and relates to a wide-range efficient low-noise control method based on structure electrical control collaborative matching. The method comprises: constructing a multi-rotor unmanned aerial vehicle maneuvering model; constructing four maneuvering models of propeller model, motor model, electronic speed controller model and battery model according to environmental information, propeller parameters, motor parameters, electronic speed controller parameters and battery parameters; correcting the maneuvering model; modeling analysis and correcting the battery model in the maneuvering model according to the influence of different temperatures on the battery performance, and then iteratively correcting the battery parameters to realize electrical control collaborative matching. The method provided by the present application updates the multi-rotor unmanned aerial vehicle maneuvering model according to environmental factors, iteratively corrects different propeller and battery parameters to realize electrical control collaborative matching, and finally realizes robust application at a wide-range altitude of 0-5000 meters.

An unmanned aerial vehicle system assembled from individual components that can disassemble back into separate components in flight on command from a remote operator or from an onboard automated controller. The separate components may then each descend via individual parachutes and / or may be padded, and may sound audible warnings during descent. The system thus reduces the potential for impact damage to the components and to property on the ground, as well as the potential for personal injury to bystanders, that would normally result from an aircraft crash. The system also avoids the need to fully replace the vehicle system as recovered components may be easily found, reassembled, and reused. In some instances, the system may deliberately self-destruct selected components and data to prevent recovery. Mission simulations may train the controller to predict problems and responsively adapt responses to ensure successful mission completion under various operating conditions.

A flight path generation apparatus (300) is configured to generate a flight path for an aircraft (100) capable of autonomously flying, and includes: an airframe information acquisition unit (301) configured to acquire airframe information including airframe IDs and take-off places of a plurality of aircraft (100); a movement information acquisition unit (302) configured to acquire movement information related to scheduled take-off times and destinations of the plurality of aircraft; a generation unit (303) configured to generate flight paths from the take-off places to landing places corresponding to the destinations based on the airframe information and the movement information; and a communication unit (304) configured to transmit the flight paths to the aircraft.

A work machine configured to operate on the ground comprises a body, an operating apparatus, a point measuring assembly, a kinematic position sensing assembly, and a controller. The operating apparatus is moveably coupled to the body and has a tool selectively engaging or passing over the ground. The point measuring assembly is coupled to the operating apparatus, is moved together with the operating apparatus and measure distances. The kinematic position sensing assembly is coupled to at least one of the operating apparatus and the body of the work machine, measures positions of the operating apparatus, and transmits signals indicative of the positions of the operating apparatus. The controller receives the signals indicative of the distances from the point measuring assembly and the signals indicative of the positions of the operating apparatus from the kinematic position sensing assembly to calculate at least one simulated surface.

The present invention relates to an electric flight control system (10) comprising an actuation subset (C), having three external duplex computers (21, 24, 27) for controlling an electric actuator (40). The electric actuator (40) has three stators (42, 43, 44) electrically connected to three respective toggle devices (50), the toggle devices (50) being electrically connected to the same internal simplex computer (80) of the electric actuator (40), each toggle device (50) being connected to one of the respective external duplex computers (21, 24, 27), each toggle device (50) being configured to connect to the associated stator (42, 43, 44) the respective internal simplex computer (80) or external duplex computer (21, 24, 27), the internal simplex computer (80) being self-monitored and communicating with the three external duplex computers (21, 24, 27).

A system for managing the deceleration of an aircraft enabling the control in real time of the position of the aircraft on a braking axis, includes a braking system; a calculator configured to: calculate, from aircraft data and from external data, a sequence of use of the braking system intended to brake the aircraft over a predetermined braking distance which associates a predetermined position on the braking axis with each braking instant; update in real time the sequence of use as a function of the difference between the position of the aircraft and the predetermined position; and a controller configured to control the braking system as a function of the sequence of use.

An autothrottle system interfaced with a Fully Automatic Digital Engine Control (FADEC) system having a command input that receives a sensed power control input (PCL) position signaling indicative of an aircraft's manual throttle setting, the autothrottle system generating a synthesized automatic output command signaling that virtualizes electrical characteristics of the sensed PCL position signaling such that the automatic output command signaling is recognized by the FADEC system as the sensed PCL position signaling.

A grouped flying object system (A) in which it possible for a plurality of flying objects (B) to fly while connected to a single supported object (C), said system (A) comprising: connection mechanisms (D) that connect the flying objects (B) to the supported object (C); and a grouped flight control unit that causes the plurality of flying objects (B) to fly in a coordinated manner.

This electrical architecture (1) for powering an electric propulsion system (3) of an aircraft (5) comprising two motors (7), comprises two electrical sources (9) each intended to power one of the motors (7), a flight control computer (11), and two electrical buses (13) each intended to connect an electrical source (9) to a respective motor (7), as well as a parallelization controller (17) of the electrical sources (9) and a switching member (19) configured to electrically connect the two electrical buses (13) on command of the parallelization controller (17), the parallelization controller (17) being configured to order the modification of the power supply of at least one motor (7) so as to equalize the voltages at the terminals of the switching member (19). Figure for the abstract: Fig. 1

A wireless network infrastructure for an aircraft includes a first communication unit to receive and transmit data signals from and to a control system in a secured domain of the aircraft, the first communication unit configured as a first network node of a wireless communication network, second communication units of corresponding aircraft devices in an unsecured domain of the aircraft and configured as second network nodes of the wireless communication network. The aircraft devices are operable by control signals sent from the control system to the aircraft devices and transmit control signals to the control system over the wireless communication network, each aircraft device having a communication unit further comprising additional control dissimilar from the control signals sent over the wireless communication network for operating the aircraft device independently. Also provided are an aircraft including the wireless network infrastructure and a method for wireless communication onboard an aircraft.

To provide a new technique which can be used for realizing early restoration of a life line such as electricity and water supply to a disaster area.SOLUTION: By a plurality of unmanned aerial vehicles, objects 4 to be laid which are either electric wires, hoses, or cord-like objects are suspended at intervals. The plurality of unmanned aerial vehicles autonomously fly in tandem flight along a laying route. When the unmanned aerial vehicle 5a of 1-st flight in flight order arrives at a final destination point 22, the plurality of unmanned aerial vehicles release the suspended installation objects 4 to be laid all at once and arrange the objects 4 to be laid on the ground surface.SELECTED DRAWING: Figure 9

To make it possible to extinguish a fire at an early stage in a fire convergence method and in a fire convergence unit.SOLUTION: A fire convergence method has steps of: arranging a gateway tunnel and a discharge tunnel on the periphery of a fire occurrence site; forming a space part by covering the fire occurrence site with an incombustible sheet; allowing the outside to communicate with the space part by the gateway tunnel; allowing the space part to communicate with the outside by the discharge tunnel; and supplying a fire-extinguishing agent to the space part.SELECTED DRAWING: Figure 1

A vehicle control and interface system described herein assists an operator of an aerial vehicle with the operation of an aerial vehicle, including automated control of the aerial vehicle during flight. The system can generate a graphical user interface (GUI) on which lateral guidance and vertical guidance initiation elements are displayed. The system can conditionally disable the vertical guidance initiation element from operator interaction until at least the operator interacts with the lateral guidance initiation element (e g., to prevent an undesirable roll maneuver during descent). If the operator interacts with the vertical guidance initiation element before engaging lateral guidance, the aerial vehicle may maintain a current altitude rather than climb or descend according to a target vertical guidance route. In this way, the GUI reformats elements based on the operational state of the aerial vehicle and reduces a risk of operational error.

Disclosed herein are systems comprising: a swarm of unmanned aerial vehicles (UAV); a payload comprising a surface material; and a controller configured to perform operations comprising: connecting each UAV of the swarm to a plurality of connecting points of the payload, such that the swarm of UAVs is configured to collectively support and move the payload; deploying the payload to a selected location and at a selected shape above an environment to provide a selected degree of shade to the environment by directing each UAV of the swarm to hover at a selected location; and adjusting the selected location and / or the selected shape of the payload to track a trajectory of the sun by adjusting the selected location of each UAV of the swarm.

The present invention provides a wireless network infrastructure (1) for an aircraft (10), comprising a first communication unit (6) configured to receive and transmit data signals from and to a control system (3) located in a secured domain (100) of the aircraft (10), the first communication unit (6) further being configured as a first network node of a wireless communication network (5), a plurality of second communication units (7, 7a-7c) of corresponding aircraft devices (4, 4a-4c) located in an unsecured domain (200) of the aircraft (10), the second communication units (7, 7a-7c) being configured as second network nodes of the wireless communication network (5), wherein the aircraft devices (4, 4a-4c) are configured to be operated by control signals sent from the control system (3) to the aircraft devices (4, 4a-4c) and transmit control signals to the control system (3)over the wireless communication network (5), wherein each aircraft device (4, 4a-4c) having a communication unit (7, 7a-7c) further comprises additional control means (8, 8a-8d) dissimilar from the control signals sent over the wireless communication network (5) for operating the aircraft device (4, 4a-4c) independently. Further, the present invention provides an aircraft (10) comprising the wireless network infrastructure (1) as well as a method for wireless communication onboard an aircraft (10).

The present invention relates to a method for controlling an aircraft (1) comprising at least two engines (16, 17), each engine (16, 17) being arranged in an engine compartment (21, 22) of its own, each engine (16, 17) being connected to a fuel supply circuit (31, 36) provided with a supply cut-off switch (34, 38) of its own for cutting off a fuel supply, said aircraft (1) comprising at least one fire detector (26-29) in each engine compartment (21, 22), said aircraft (1) comprising at least a first fire extinguisher (40) and a second fire extinguisher (45).An automatic assistance phase (PHASASSIST) comprises, in the event of a fire detected in an engine compartment, automatically and with an avionics system (60), an activation of the power cut-off switch (34, 38) of the engine (16, 17) present in the compartment concerned, then a triggering of the first extinguisher (40), then a triggering of the second extinguisher (45) under respective predetermined conditions.

A method includes determining an angular rate of a rotorcraft based on a pilot input of the rotorcraft; determining an attitude reference for the rotorcraft based on the angular rate, the determining including determining an attitude difference from a trim attitude of the rotorcraft; determining a linear acceleration error for the rotorcraft; determining a trim attitude of the rotorcraft, wherein the trim attitude is based on the linear acceleration error; and summing the attitude difference and the trim attitude to generate the attitude reference; determining a flight command for the rotorcraft based on the attitude reference; and controlling flight control elements of the rotorcraft based on the flight command.

The present invention relates to a fly-by-wire system for a tandem tilt-rotor aircraft. It consists of a flight control system, a tilt control system, and an information acquisition system. The three systems communicate via an RS485 bus. The flight control system, tilt control system, and information acquisition system respectively control the flight of the aircraft, the tilt of the rotor nacelle, and the engine speed, reducing the complexity of a single system. At the same time, each system is separately installed near the controlled object to prevent interference caused by too long signal lines. In the flight control system, all information acquisition and transmission tasks are implemented by the FPGA chip and the surrounding circuits. The airborne computer only focuses on the operation of the control algorithm, improving the utilization efficiency of the airborne computer and providing reliable support for adding more complex control algorithms. In the tilt control system, the tilt angle of the rotor nacelle is measured by using a resolver, which has the characteristics of simple installation, high precision, and fast response.

To provide a suspended aerial vehicle system which reduces an installation area and provides other advantages such as longer flight time and higher load resistance in comparison to a conventional drone product.SOLUTION: A suspended aerial vehicle system includes an aerial vehicle with a thruster assembly and a supporting line attached to the aerial vehicle that is capable of supporting at least some of the weight of the aerial vehicle. The supporting line may have an adjustable length which when varied, and in coordination with variations in a thrust characteristic of the aerial vehicle, may change the position of the aerial vehicle. Other aspects are also described and claimed.SELECTED DRAWING: Figure 1

A system (100) and a method for operating an aircraft (102) in a required time of arrival (RTA) mode include a control unit (110) configured to adapt one or more RTA parameters for the RTA mode of the aircraft (102) based tail-specific data (122) for the aircraft (102), and / or weather conditions at different locations along a flight path (200) of the aircraft (102) in the RTA mode.

The invention discloses a low-speed large-angle turning control system and method for a large aircraft, and belongs to the field of aircraft ground control. A low-speed large-angle turning controller and an auxiliary turning switch are designed and incorporated into an existing aircraft control system to jointly form a low-speed large-angle turning control system, cooperative turning control over front wheels and main wheels of an aircraft is achieved, and an additional mechanical executing mechanism does not need to be added; by means of the control method, when the aircraft turns, differential thrust and differential brake are provided, front wheel turning is assisted, and the target turning radius of the aircraft and lateral force borne by tires are effectively reduced.

An aircraft control system (100) including an aircraft control module (110), a trained classifier module (120), and an aircraft control processing engine (13). The aircraft control module (110) generates first control outputs (104a to 104c) based on received aircraft operating inputs (102a to 102d). The trained classifier module receives the aircraft operating inputs (102a to 102d) and generates second control outputs (104d to 104f). The aircraft control processing engine (130) receives the first control outputs (104a to 104c) and the second control outputs (104d to 104f) and generates operating control outputs (106a to 106c), based on the received first control outputs and second control outputs. The aircraft control processing engine (130) then controls the aircraft using the operating control outputs (106a to 106c).