26results about "Conjoint controls" patented technology

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 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 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.

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

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 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 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).

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.

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.

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)

An aerial towed platform flies behind a lead vehicle collecting more power than needed to overcome the drag of the towed platform. The towed platform planform is comprised mostly of a single photovoltaic sheet with lift forces on both the upper and lower surface of the sheet. The camber of the platform is preferably between 0.02 and 0.06 with distributed propulsion able to change camber continuity and increase lift relative to drag. The applications include, but is not limited to, aircraft, trucks, cars, railcars, and boats. The most-preferred application is vehicles with low drag where the solar power can provide more than 30% of the energy needs of the vehicle.

A craft comprises at least one hull; at least one wing coupled to the hull(s), wherein the at least one wing comprises a port side section and a starboard side section; a blown wing propulsion system comprising a plurality of propellers arranged along the port side section and the starboard side section of the at least one wing and configured to generate lift on the craft by blowing air over the at least one wing; and a control system configured to control a respective rotation rate of each propeller of the plurality of propellers. The control system is configured to, after receiving an indication to reduce airspeed of the craft, control the respective rotation rate of each propeller of a first subset of propellers to be a first rotation rate that is lower than a second rotation rate at which each propeller of a second subset of propellers rotate.

The application discloses an anti-crosswind vertical take-off and landing unmanned aerial vehicle and an anti-crosswind method thereof, and relates to the technical field of unmanned aerial vehicles. The anti-crosswind vertical take-off and landing unmanned aerial vehicle comprises an unmanned aerial vehicle body and a wind speed and direction instrument which is arranged separately from the unmanned aerial vehicle body. The unmanned aerial vehicle body comprises a fuselage, a flight control machine arranged in the fuselage, wings arranged on both sides of the fuselage, a propeller arranged in front of the wings, a motor in transmission connection with the propeller, a rudder surface arranged behind the wings, and a rudder in transmission connection with the rudder surface. The wind speed and direction instrument is in communication connection with the flight control machine, and the flight control machine is in cable connection with the motor and the rudder. The wind speed and direction information is measured by the wind speed and direction instrument, and the rudder is controlled to deflect and the motor is controlled to rotate according to the wind speed and direction information, attitude information and height information, so as to control the heading, height and yaw of the aircraft, make the wing span length direction consistent with the crosswind direction, and avoid landing of the aircraft in the case that the attitude is inclined without the need of a pilot to control and without the need of relying on the experience of the pilot.

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.

The invention relates to the technical field of aircraft control, and discloses an electric aircraft stall correction method which comprises the following steps: S1, stall judgment: judging whether an aircraft is in a stall state or not according to flight characteristics of the aircraft, and if the aircraft is in the stall state, performing attitude control; s2, core attack angle reduction: forwards pushing an operating rod according to the pushing amplitude of the operating rod according to the stall degree of the aircraft, keeping the longitudinal axis of the fuselage of the aircraft parallel to the horizon, and avoiding simultaneous operation of ailerons and rudders; s3, accelerator optimization: when the longitudinal axis of the fuselage of the aircraft is parallel to the horizon, the accelerator is slowly reduced, and the power output of the aircraft is reduced; s4, correcting the attitude: adjusting the side inclination angle of the aileron through the operating rod for many times, and controlling the wing to recover the horizontal state. The method has the advantages of improving the stall change success rate, reducing the safety risk and the like, and solves the problems that no unified technical guidance exists, and faults are easily expanded through blind operation.

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

An aircraft, a method of controlling the aircraft, and a control system (12) for the aircraft (10) has a fuselage (16) and tilt-wing (14) movable relative to the fuselage. A plurality of main propulsors coupled to main propellers (40) that is coupled to the tilt-wing, which are configured to provide a first maximum amount of thrust. A plurality of auxiliary propulsors coupled to auxiliary propellers (48) that are spaced apart from the tilt-wing, which are configured to provide a variable amount of thrust. A controller (72) signals the main propulsors to operate at the first maximum amount of thrust when the tilt-wing moves from the cruise position to the transition position, and signals the auxiliary propulsors to operate at the variable amount of thrust when the tilt-wing is in the transition position in which the first maximum amount of thrust and the variable amount of thrust together provide an overall thrust to descend and land the aircraft.

The present application provides an aircraft control device, an aircraft control method, and a non-transitory computer-readable recording medium storing a program. The aircraft control device (56) has a determination section (66) that determines whether to limit supply of surplus power among power generated by a generator (42) to a battery (30) based on a remaining capacity of the battery (30), and a control section (62) that causes a motor (31A) to consume the surplus power by increasing a rotational speed of a rotor (18), i.e., a rotor rotational speed, and limits an increase in a body (12) caused by the increase in the rotor rotational speed by adjusting a rudder angle of an elevator (17) when the determination section determines to limit supply of the surplus power to the battery. Accordingly, it is possible to prevent a decrease in ride comfort and the like, and to appropriately suppress overcharging of the battery.