44results about "Conjoint controls" patented technology

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

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.

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.

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).

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

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

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 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.

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.

The aerial drone system includes a first drone (14), a second drone (14), and an electronic media tether (36) coupled to the first drone and the second drone, wherein the first drone (14) includes a first drone body and a first propeller system configured to propel the first drone through the air, and the second drone (14) includes a second drone body and a second propeller system configured to propel the second drone through the air, and the electronic media tether (36) includes a plurality of light-emitting diodes (LEDs) (37) and is configured to transmit power to the plurality of LEDs (37).

The present invention is an Electric servo system which controls and automates gate openings based on GPS speed and position data that results in precise and reliable modern variable and constant rate application. The Electric servo system also allows for Mechanical gate linkages to remain intact, resulting in few changes to the aircraft and redundancy of emergency components. A Mechanical input connect / disconnect is used to effortlessly transfer between the automated Electric servo system and the Mechanical gate system.

The invention discloses a single-person low-altitude aircraft based on a distributed power and intelligent attitude stabilizing system and a control method, and relates to the technical field of aviation flight, the single-person low-altitude aircraft comprises a central bearing unit, a control unit and a control unit, the central bearing unit is constructed into a rigid backpack structure conforming to a human body back curve; a distributed propulsion system includes; the pair of main lift ducted fans are symmetrically and pivotally mounted on two sides of the central bearing unit, and ducted nozzles of the main lift ducted fans can be controlled to perform vector deflection; the multiple auxiliary stabilizing ducted fans are installed on the adjustable exoskeleton supports corresponding to the four limbs of the user respectively, the multiple fans disperse propulsive force to the back and the four limbs, a real-time adjusting algorithm is matched, the body balance problem in the flying process is effectively solved, and the user can keep the stable posture without continuously and finely adjusting the limbs. By means of the design, the two hands of an operator can be naturally liberated in the flying process, and the device can be used for executing task operations such as shooting and detection.

This flying body system comprises a flying body (1) that can execute predetermined work, and an energy supply body (2) that can supply energy to the flying body (1).

Aircraft with pitch management system and method for correcting the pitch of an aircraft [Aircraft 1 comprising at least one pair of wings 2, at least one horizontal thruster 3, an elevator 10 blown by at least one of the horizontal thrusters 3 and a control system arranged to receive piloting instructions and thrust data, and to generate downstream commands to the horizontal thruster 3 and to the elevator 10, the control system comprising a control member arranged to convert the piloting instructions into upstream control instructions, a pitch sensor arranged to determine data representative of the pitch of the aircraft 1, a speed data input of the aircraft 1, and a computer arranged to receive the upstream control instructions, the data representative of the pitch and the speed data, the computer being arranged to generate downstream pitch commands to the elevator 10,the computer being arranged to determine pitch correction components for the downstream controls of the elevator.,

A payload system for carrying a payload including a platform configured to support the payload, and a payload distribution sensor configured to sense the distribution of the payload on the platform. At least two autonomous aerial vehicles are provided, with coupling arrangements being configured to couple each vehicle to the platform. One or more processing devices configured to determine a payload distribution in accordance with signals from the payload distribution sensor and control operation of the vehicles in accordance with the determined payload distribution to thereby allow the platform and payload to be lifted.

Disclosed is an aircraft control system 100 for controlling actuation of an aircraft component 700, the system comprising 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. Also disclosed is an aircraft 1000, aircraft assembly and a method of controlling an aircraft component of an aircraft.

A method for controlling an aircraft comprising at least two engines, each engine being arranged in its own engine compartment, each engine being connected to a fuel supply circuit provided with its own fuel supply cut-off for cutting off a fuel supply, the aircraft comprising at least one fire detector in each engine compartment, the aircraft comprising at least one first extinguisher and one second extinguisher. An automatic assistance phase comprises, in the event of fire being detected in an engine compartment, automatically and with an avionics system, activating the fuel supply cut-off of the engine present in the compartment concerned, then triggering the first extinguisher, then triggering the second extinguisher in predetermined respective conditions.

Systems, methods, and devices are provided herein for controlling one or more movable objects via a graphical user interface. A method for controlling a movable object may be provided. The method may comprise generating a motion path comprising at least one spatial point defined relative to one or more parameters of a target object; and determining one or more motion characteristics of the movable object for the at least one spatial point.

An unmanned aerial vehicle intelligent emergency voice report system and method includes monitoring operational parameters of the UAV, monitoring environmental parameters within and external to the UAV, and processing the operational parameters and the environmental parameters, in a controller, to determine when the UAV is in an emergency condition. When the controller determines the UAV is in an emergency condition, the controller is used to: process the operational parameters to determine how the UAV will respond the emergency condition; automatically determine a communication transmission frequency; tune an onboard communication device to the communication transmission frequency; generate analog voice waveforms that provide information regarding the emergency condition; supply the analog voice waveforms to the onboard communication device; and command the onboard communication device to transmit the analog voice waveforms on the communication transmission frequency.

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) are electrically connected to the same internal simplex computer (80) of the electric actuator (40). Each toggle device (50) is connected to one of the respective external duplex computers (21, 24, 27). Each toggle device (50) is configured to connect to the associated stator (42, 43, 44) either the internal simplex computer (80) or the respective external duplex computer (21, 24, 27). The internal simplex computer (80) is self-monitoring and communicates with the three external duplex computers (21, 24, 27). (Shorthand figure: Figure 1)