272results about "Aircraft navigation control" patented technology

The invention discloses a new-configuration cross-medium aircraft based on blade tip jet rotors and a working method thereof, the aircraft has an air flight mode, an underwater navigation mode and a cross-medium mode, and comprises a fuselage; the main rotor system comprises an electric centrifugal compressor which is arranged on the fuselage in a jacking manner and a blade tip air injection main rotor blade which is connected with an air path of the electric centrifugal compressor; the auxiliary lift system comprises lift units arranged on the fuselage in a distributed mode, and the lift units can be independently controlled; in the air flight mode, the propeller tip jets air, the main rotor rotates, and the auxiliary lift system works to realize air flight; and in the underwater navigation mode, the blade tip jets air, the main rotor stops rotating, the blades on the single side are overturned around the fixed axis till the blade nozzles face the advancing rear portion, and the underwater water jet propulsion device is formed. The novel-configuration cross-medium aircraft disclosed by the invention adopts a distributed lift force layout, has relatively large take-off weight and good maneuverability, can realize continuous medium crossing, and is small in water entering and exiting impact.

A powertrain for an aerial vehicle may include a mechanical power source and an electric power generation device mechanically coupled to the mechanical power source. The powertrain further may include an electric motor electrically coupled to the electric power generation device. A first propulsion member may be mechanically coupled to the mechanical power source and configured to provide a first thrust force. The powertrain also may include a second propulsion member mechanically coupled to the electric motor and configured to provide a second thrust force. A vehicle controller may be provided and configured to at least partially control aerial maneuvering of the aerial vehicle, and cause supply of a first portion of the mechanical power to the first propulsion member and a second portion of the mechanical power to the electric power generation device based at least in part on at least one characteristic associated with maneuvering of the aerial vehicle.

The invention provides a torque transmission device and an aircraft. The torque transmission device comprises a base; the straight shaft penetrates through the base and can rotate around the axis of the straight shaft in the base; one end of the flexible shaft is fixedly connected with one end of the straight shaft, and the other end of the flexible shaft can be in transmission connection with an output shaft of a power output device; the driving gear is coaxially and fixedly connected with the straight shaft; wherein the output torque of the power output device can be transmitted to the straight shaft through the flexible shaft and then transmitted to the driving gear, and the driving gear is used for providing power for a device to be driven. The invention provides a torque transmission device which is suitable for more application scenes.

An emergency landing apparatus (100) for an aircraft and an associated method are provided. The emergency landing apparatus comprises: a housing (10) for ejection from the aircraft; a parachute (20), arranged for deployment from the housing, comprising a canopy (22); a rocket motor (30), positioned in the housing, arranged to provide upwards thrust to control descent of the aircraft during emergency landing of the aircraft; a rocket motor initiator (38), positioned in the housing, arranged to initiate the rocket motor; and one or more sensors for sensing ejection of the housing from the aircraft and for arming the rocket motor initiator in response to sensing ejection of the housing from the aircraft.

An aircraft may comprise propulsors. The propulsors may be integrated into an array of propulsors. An array of propulsors may be integrated in an airfoil of the aircraft. The aircraft may include a flow turning control system. The flow turning control system may include an end wall and one or more movable flaps. The flow turning control system may enable selective flow turning of the flow of propelled by the array of propulsors. The selective flow turning may include actuating the one or more movable flaps. The selective flow turning may achieve flow turning of over a trailing edge of a movable flap.

An electric vertical take-off and landing aircraft comprises a fuselage and a tilt wing. The tilt wing is tiltable relative to the fuselage in a range of tilt wing angles. Control surfaces are arranged at the tilt wings. The aircraft comprises a horizontal stabilizer with an elevator, in particular a stabilator, a vertical stabilizer with a rudder, in particular a fully movable stabilizer, at least one electric engine for powering main propellers arranged at the tilt wing and at least one software control device. The control device is configured to control at least the control surfaces , the main propellers and the tilt wing angle during hover and transition between hover and cruise flight.

The embodiments of the present invention provide a drone and a control method therefor, in which, by converting a motor signal to a motor control signal in a general situation, the drone is controlled so as to fly along a specific flight trajectory, a specific situation is recognized by measuring attitude on the basis of sensor data, the difference between an input value and an estimated input value is estimated as estimated disturbance, the input value being outputted from a policy-based reinforcement learning network which has undergone reinforcement learning so as to output the input value by receiving a desired current state, and the estimated input value being outputted from a Bayesian network trained so as to output the estimated input value by receiving the current state and the next state, and the drone is controlled so as to fly while maintaining attitude by adjusting the motor control signal in the specific situation by means of a control signal in which disturbance that can actually occur is canceled by subtracting the estimated disturbance from the input value.

An orbital maneuver apparatus includes a fluid supply arrangement, a main body, an actuation head, and a nozzle assembly. The main body includes an outer housing, an inner housing mounted in the outer housing such that the inner housing is arranged to rotate about a longitudinal direction of the main body, wherein the fluid supply tube extends in the inner housing of the main body and is stationary with respect to the outer housing. The actuation head is connected to the inner housing of the main body to rotate along with the inner housing. The nozzle assembly includes a first nozzle head and a second nozzle head which are in fluid communication with the fluid supply arrangement, and are both movably supported in the actuation cavity and are arranged to rotate correspondingly with the actuation head, and to further rotate about a transverse direction of the main body.

An aircraft may comprise propulsors. The propulsors may be integrated into an array of propulsors. An array of propulsors may be integrated in an airfoil of the aircraft. The aircraft may include a flow turning control system. The flow turning control system may include an end wall and one or more movable flaps. The flow turning control system may enable selective flow turning of the flow of propelled by the array of propulsors. The selective flow turning may include actuating the one or more movable flaps. The selective flow turning may achieve flow turning of over a trailing edge of a movable flap.

Example embodiment provides an aircraft with improved agility. The aircraft includes a main body, at least two wing assemblies, at least two motors, and a controller. The wing assemblies are attached to the main body. Each motor tilts one wing assembly with a tilting angle. The controller is connected with the motors for controlling the tilting angle of the wing assembly. Each wing assembly further includes a wing, a power plant, and a propeller that is driven by the power plant for providing propulsion. Each wing assembly tilts with an individual tilting angle, so that the aircraft can fly with improved agility. The power plants and propellers on the wings can each be controlled independently in synchronism with the tilting wings.

The invention relates to a trailing edge flap pneumatic structure for mechanical control and jet flow resistance reduction of an unmanned aerial vehicle. The trailing edge flap pneumatic structure comprises a deflection angle detection device, a jet flow spraying rod, a jet flow air supply pipe, a controller and a flight control plate. The two deflection angle detection devices are arranged at the two trailing edge flaps and used for detecting the deflection angles of the two trailing edge flaps; the two jet flow spray rods are transversely connected to the upper portions of the two wings and located in front of the two trailing edge flaps, and a plurality of backward jet flow holes are formed in the jet flow spray rods. An inlet of the jet flow air supply pipe is sequentially provided with a jet flow control electromagnetic valve and a jet flow meter and connected with a high-pressure air source, and the jet flow meter is used for detecting the air flow in the jet flow air supply pipe; an outlet of the jet flow air supply pipe is divided into two branches which are connected with the two jet flow spray rods; the controller is connected with the jet flow control electromagnetic valve; the flight control board is connected with the two deflection angle detection devices, the controller and the jet flow meter, and negative feedback control over the air flow of the jet flow air supply pipe based on the trailing edge flap deflection angle is formed.

The invention relates to a VTOL aircraft (1) with a tiltable propulsion unit (10), in particular a jet propeller, and to a method for operating such an aircraft (1) for executing a transition from a cruise flight mode to a hover mode of the aircraft (1). The VTOL aircraft (1) according to the invention comprises at least one propulsion unit (10) arranged in a rear region of a fuselage part of the aircraft and designed to generate thrust along a central axis (c) of the propulsion unit (10).It further comprises a tilting system designed to rotate the drive unit (10) about a rotation axis (r) from a horizontal state in a cruise mode of the aircraft to a vertical state in a hover mode of the aircraft and vice versa, wherein the drive unit (10) is arranged and designed such that, in a cruise mode of the aircraft, an air flow (30) entering the drive unit (10) comes from below the fuselage part on which the drive unit (10) is arranged, and during the transition from a cruise mode to a hover mode of the aircraft, or vice versa, the air flow (30) entering the drive unit (10) comes from above the fuselage part on which the drive unit (10) is arranged.

The invention relates to the technical field of inspection unmanned aerial vehicles, in particular to an anti-collision inspection unmanned aerial vehicle which comprises an unmanned aerial vehicle body and four motors, rotating shafts are fixed to the driving ends of the four motors, propellers are installed at the upper ends of the four rotating shafts, and the four motors are movably connected with the unmanned aerial vehicle body through telescopic suspension mechanisms; the telescopic suspension mechanism comprises a mounting plate fixed to one end of the motor and movably arranged on the outer side of the rotating shaft in a sleeving mode, and a sleeve fixed to the unmanned aerial vehicle body. The four motors are movably connected with the unmanned aerial vehicle body through the telescopic suspension mechanism, and meanwhile, when the unmanned aerial vehicle gets close to an obstacle, propellers can be driven to move towards the unmanned aerial vehicle body through a reversing mechanism and a gas tank located on the outer side of the unmanned aerial vehicle body; therefore, when the whole unmanned aerial vehicle is not in contact with the obstacle, the propeller can be far away from the obstacle, and the high-speed rotating propeller is prevented from colliding with the obstacle.

The invention relates to a VTOL aircraft which has (a) a cruising flight system having at least one airfoil, said airfoil being designed to generate dynamic lift during a cruising flight, and (b) a hovering flight system having at least one lift element and at least one stabilizing element, wherein (i) the lift element is designed to provide a lift force for a hovering flight, and (ii) the stabilizing element is designed to provide at least one stabilizing force, using a respective lever, with respect to a longitudinal axis, a transverse axis, and / or a vertical axis of the VTOL aircraft during the hovering flight and during a transition from the hovering flight to the cruising flight and during a transition from the cruising flight to the hovering flight.

A disclosed device allows a person to fly. A disclosed wearable flight system includes a plurality of propulsion assemblies including a left-hand propulsion assembly configured to be worn on a user's left hand and / or forearm and a right-hand propulsion assembly configured to be worn on a user's right hand and / or forearm. A further embodiment includes a body propulsion device that is configured to provide a net force along an axis defining a net body propulsion vector and a support device configured to support a user's waist or torso. The support device is configured to hold a user's body relative to the body propulsion device such that a line extending between center the of the user's head and the center of the user's waist extends, relative to the orientation of the net body propulsion vector during use, by a body propulsion elevation angle that is greater than zero.

The invention relates to an improved deflection flap for a vehicle with a fuselage featuring an airfoil profile. The deflection flap at the bow is two-part. It includes a device for raising and lowering it.

The invention provides a jet-propelled self-rotor device for an unmanned aerial vehicle, the jet-propelled self-rotor device comprises a supporting structure, a rotor mechanism is rotatably connected to the supporting structure, and the rotor mechanism comprises a pair of rotors and is used for providing lift force for a fuselage during rotation; spraying pipes are arranged at wingtips of the rotors, first guide pipes are arranged in the rotors, and the output ends of the first guide pipes communicate with the spraying pipes. The air slip ring mechanism comprises a fixed part and a rotating part, the fixed part is of a hollow structure, the input end of the fixed part is connected with an air source device, the rotating part is arranged on the rotor wing mechanism, rotationally connected with the fixed part and fixed to the input end of the first guide pipe, and an annular cavity is formed in the rotating part; the annular cavity communicates with the input end of the first catheter and the output end of the fixing part. By arranging the gas slip ring mechanism, the first guide pipe and the spray pipe, high-pressure gas can directly drive the rotor wings to rotate to generate lift force, so that the unmanned aerial vehicle can realize vertical take-off and landing and hovering, and the applicability of the self-rotor unmanned aerial vehicle in a complex environment or a specific task is improved.

The present application pertains to a VTOL aircraft with tandem rotors, each rotor comprising at least one hub connected to a rotational power source and brake units that control the rotation of the hubs, stopping them in predefined positions during flight, wherein each hub comprises a pair of opposing hinges incorporated into grips that have longitudinal cavities in which rotor blades are accommodated, sandwiched between bearings. Actuators move the blades through the grips until they are centred and locked or locked by the roots. Collective pitch mechanisms tilt the grips around the hinges, and the blade edges are interchangeable during flight. In helicopter mode, yaw is controlled by tail fans, and propulsion means generate a force in a direction parallel to the axis of symmetry of the aircraft.

The present invention relates to a locking system (40) for a tilting system (10) of an aircraft, in particular a VTOL aircraft, as well as to a tilting system (10) and an aircraft comprising the locking system (10) according to the invention. The locking system (40) comprises a locking element (41) which is designed and arranged to be movable in one direction with respect to a fastening element (1231) to which the locking element (41) is fastened, a ring element (1225) comprising at least one locking counter-element (44a, 44b) which is designed to receive the locking element (41) in a locked state of the locking system (40), a spring element (45) which is designed and arranged to apply a force to the locking element (41), wherein the locking counter-element (44a, 44b), the locking element (41) and the spring element (45) are designed such thatthat when a defined limit torque on the ring element (1225) is exceeded, the locking element (41) is pressed out of the locking counter-element (44a, 44b) due to a rotation of the ring element (1225) against the force of the spring element (45) in order to transfer the locking system (40) into an unlocked state.

The present invention provides a space intelligent flying robot in a microgravity-normal air environment, belonging to the field of flying robots. To achieve the goal of enabling the space intelligent flying robot in a microgravity environment to have independent control over position, posture, output force, and torque. The robot comprises a carrier main frame, an outer shell, a computing system disposed within the carrier main frame, a visual navigation system disposed in front of and behind the carrier main frame, a laser ranging module embedded in the outer shell, a power supply system disposed on the left and right sides of the carrier main frame, a power system embedded in the outer shell and within the carrier main frame, a gripping system disposed below the carrier main frame, and an interactive system disposed in front of and above the main frame. While realizing basic functions, the present invention also makes innovative designs in the robot architecture, optimizing the robot's performance in manipulation, control, perception, and real-time performance, and has high engineering application value and good engineering application prospects.

The present invention relates to a propulsion device comprising: a platform; a propulsion unit; support means arranged to hold and support the propulsion unit, said support means cooperating integrally with the platform via one or more suitable mechanical connections; a protruding means cooperating integrally with the platform via suitable mechanical connections; a central leg passing through the inertia centre of the propulsion device and cooperating integrally with the platform via suitable mechanical connections at its proximal end. In order to enable the propulsion device to land on a receiving surface that is relatively small in size relative to the propulsion device and / or has a moving surface, the protruding means and the central leg are arranged relative to each other so that the central leg can provide a first contact between the device and the surface receiving the device.

The application discloses a manned aircraft and relates to the technical field of aircraft equipment, and comprises a mounting frame, a first engine, a second engine and a third engine, wherein the first engine, the second engine and the third engine are arranged on the mounting frame, and the output directions of the first engine, the second engine and the third engine are the same; one first engine is arranged at the middle position of the mounting frame, four second engines are arranged at equal intervals in a circle on the periphery of the first engine, and two third engines are symmetrically arranged on the two sides of the four second engines; the axes of the first engine and the two third engines are in the same plane, and the jet ends of the first engine, the second engine and the third engine are respectively provided with an adjusting nozzle, so that the flight attitude control after the manned aircraft is realized.

The present invention relates to a system (30) for controlling actuators (TS) comprising a plurality of redundant servo units (FC-1, FC-2, FC-3) generating values ​​of the same magnitude (Δ1, Δ2, Δ3) from the same setpoint (Gsp) and the same measurement data (Gs1, Gs2, Gs3), the redundant servo units (FC-1, FC-2, FC-3) further communicating with each other (B) so that each redundant servo unit (FC-1, FC-2, FC-3) has access by reading the most recent values ​​of the variables (Δ1, Δ2, Δ3) generated by the redundant servo unit and implements a method for correcting each generated value by combining them. Thus, the present invention prevents discrepancies between these variables (Δ1, Δ2, Δ3). Such a system (30) may be equipped in a vehicle having a driver, passengers, and / or a load consisting of goods or cargo, and having one or more actuators controlled in this manner.

The invention belongs to the field of fan design, and particularly relates to a hydrogen combustion lift fan system which comprises a lift fan, a box type spray pipe, an output shaft, a main engine and a superconducting motor. The lift fan is coaxially and fixedly connected with the box type spray pipe, one end of the output shaft is connected with rotor blades of the lift fan, the other end of the output shaft is connected with the superconducting motor and the main engine, and the superconducting motor is coaxially arranged in the main engine. A liquid hydrogen tank is arranged on the outer side of the main engine, a rectifying support plate is arranged in the lift fan, and an ignition electric nozzle is arranged on a cartridge receiver of the lift fan; hydrogen in the liquid hydrogen tank can flow into the ignition electric nozzle after passing through the superconducting motor and the rectifying support plate, and is burnt and heated after ignition to generate thrust. The energy conversion mode of a traditional lift fan is optimized, the temperature of airflow behind the lift fan can be increased from 300 DEG C to 1000 DEG C or above, the lift amplification of the lift fan exceeds 150%, and the requirement of a power system for lift is met. According to the scheme, hydrogen for cooling the superconducting motor can be recycled.

This specification discloses a combined-power vertical take-off and landing autogyro aircraft and its control method, belonging to the field of aircraft technology. The aircraft includes: a fuselage and an engine mounted on the fuselage, a high-pressure gas storage tank, an air compressor, and a jet rotor; when the aircraft is hovering or taking off and landing vertically, the high-pressure gas in the high-pressure gas storage tank is ejected at high speed from the jet outlet at the end of the jet rotor through the air duct, driving the jet rotor to rotate at high speed to generate the required lift; during flight, the propeller of the engine rotates to drive the fuselage forward, and the oncoming airflow drives the jet rotor to rotate to generate the lift required for flight; the air compressor can couple the engine power to replenish the high-pressure gas storage tank. Compared with traditional aircraft, this aircraft uses compressed air in the high-pressure gas storage tank to drive the jet rotor to achieve vertical take-off and landing and hovering. The implementation method is simple and compact, the cost is low, the use and maintenance cost is low, and there is no high-temperature resistance requirement for the rotor, which can effectively make up for the shortcomings of autogyro aircraft.

The invention relates to the technical field of unmanned aerial vehicles, and discloses a telescopic air injection device, an active-disturbance-rejection control method and an unmanned aerial vehicle. A first air pipe is connected to a fuselage of the unmanned aerial vehicle through a gimbal frame mechanism; the second air pipe is coaxial with the first air pipe and is nested in the first air pipe; the third air pipe is coaxial with the second air pipe and is nested in the second air pipe; a rope, a first fixed pulley, a second fixed pulley, a third fixed pulley, a contraction driving winch and an extension driving winch; the contraction driving winch and the extension driving winch are connected to one end of the first air pipe, and the first fixed pulley is arranged at the other end of the first air pipe; the second fixed pulleys are arranged at two opposite ends of the second air pipe; the third fixed pulleys are arranged at two opposite ends of the third air pipe; the rope is sequentially wound around the first fixed pulley, the second fixed pulleys and the third fixed pulleys, the two ends of the rope are connected to the contraction driving winch and the extension driving winch correspondingly, and the controllable adjusting precision of the high-pressure airflow acting distance is improved.

A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.

The application discloses a single duct aircraft, which comprises a ring-shaped duct, a propeller and a propeller driving motor, the axis of the duct is vertically arranged, the propeller driving motor is a shaftless motor, the stator of the shaftless motor is fixed on the inner wall of the duct, and a plurality of blades of the propeller are fixed on the annular rotor of the shaftless motor. The propeller of the application is installed on the annular rotor of the shaftless motor, so that a support does not need to be installed in the duct, the internal resistance of the duct is small, the power of the duct aircraft is large, and the efficiency is high.

A vertical take-off and landing aircraft that includes a fuselage which has a nose end, a tail end, and a plurality of seats disposed in an interior of the aircraft with vertical takeoff and conventional aircraft ability. A pair of rear wings extend outwardly from opposing sides of the fuselage between a cockpit and the tail end, and a pair of front wings extend outwardly from opposing sides of the fuselage between the cockpit and the nose end. Each of the pair of rear wings and the pair of front wings includes an adjustably mounted turbine which includes a statically mounted fan pod, a duct rotatably connected to the fan pod, and an adjustable nozzle rotatably connected to the duct. The adjustable nozzle is adjusted to a variety of configurations ranging between a vertical position and a horizontal position via the duct.

------ Vector-Tripping Aircraft The present invention relates to a vector-tripping aircraft (1), comprising: a wing in the form of a wing (2); a tail in the form of at least one rear aileron (3) carried by said wing (2); and an engine assembly (4) connected to said wing (2) for thrusting the aircraft (1), characterized in that said engine assembly (4) is disposed in front of said wing (2) and is connected to it by at least one arm (6), and that it comprises at least one turbine (10) configured to create, in operation, a jet of air discharged towards said wing (2) by a steerable nozzle (11). Figure to be published with the abbreviation: Figure 1