124results about "Aircraft navigation control" patented technology

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.

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.

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 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.

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 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.

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.

------ 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

A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude control motors is disposed in each cavity of the plurality of cavities.

This invention discloses a propulsion system for a cross-medium aircraft based on a tip-jet rotor and its operating method. The propulsion system includes a compressor, a ring motor, rotor blades, and a drive motor. The rotor blades have internal gas flow channels connected to the compressor's gas outlet. The drive motor drives the compressor to eject compressed air or pump water to provide lift or thrust. The ring motor is located at the connection between the compressor and the rotor blades, controlling the rotor blades to rotate around a fixed axis to achieve changes in collective pitch and cyclic pitch. This invention's propulsion system can provide power to the aircraft in both water and air media using different driving methods, solving the problems of unnecessary weight increase caused by equipping existing cross-medium aircraft with two independent propulsion systems, and the difficulty in achieving optimal efficiency simultaneously when the same propulsion system operates in both media using the same driving method. Furthermore, the rotatable blades can also serve as control surfaces underwater, enhancing the aircraft's underwater maneuverability.

The present invention relates to an aircraft (1) comprising: a main fuselage formed of a central wing (10), centered on a longitudinal axis (X10); two lateral wings (20) mechanically connected to the central wing (10); and at least one propulsion system (40); characterized in that the aircraft (1) comprises an electrical energy storage system (30) electrically connected to the propulsion system (40) and providing fully electric propulsion for the aircraft (1). Abstract figure: 1

An aircraft frame includes a fuselage, at least one boom and a wing structure including a first lifting surface having a first root portion located proximate the at least one boom and a first tip portion where at least a portion of the first tip portion is located forwardly from at least a portion of the first root portion, a second lifting surface having a second root portion located proximate the fuselage, and a second tip portion located spaced from the first tip portion where at least a portion of the second tip portion is located rearwardly from at least a portion of the second root portion, and a connector surface extending between the first and second tip portions.

An aircraft includes an onboard power supply, an empennage assembly, and a horizontal main wing each connected to a fuselage, and a vertical cross-wing arranged orthogonally with respect to the main wing. Flight control surfaces are arranged on the empennage assembly, vertical cross-wing, and horizontal main wing. A distributed propulsion system includes a first pair of propellers connected to the horizontal main wing and a second pair of propellers connected to the vertical cross-wing. Each of the propellers is connected to and powered by the power supply. Each propeller forms an acute canting angle with respect to an axis of the particular horizontal main wing or the vertical cross-wing to which the propeller is connected. The flight modes may include vertical takeoff and landing (VTOL), hover mode, rapid descent, and forward and backward flight modes. The propellers are unpowered during the rapid descent mode.

An aircraft having reverse thrust capabilities, the aircraft includes a fuselage, a plurality of flight components configured to enable the aircraft at a low-speed flight mode, a pilot control, a sensor, an energy source, and a flight controller configured to receive the aircraft datum from the sensor at an initial time, wherein the initial time occurs when at least a flight component of the plurality of flight components produces a positive thrust, initiate a reverse thrust command as a function of the aircraft datum at a subsequent time wherein the reverse thrust command causes the at least a flight component of the plurality of flight components to produce a negative thrust, and the subsequent time occurs temporally after the initial time, and command the at least a flight component of the plurality of flight components to enter a speed reversal region.

A disc-shaped, vertically launching and landing aircraft, featuring the following: - an apron that widens towards the underside; - a disc-shaped rotor positioned on the underside of the apron and rotating relative to the apron; and - a plurality of blades arranged standing on an upper surface of the rotor and positioned radially from the center of the rotor, - wherein a cutout is formed in each of the majority of wings and - wherein, as the rotor rotates, the centrifugal force causes an airflow along the wing rotating with the rotor, wherein the airflow is swirled in a spiral by an airflow passing over the wing cutout in a direction substantially orthogonal to the wing, wherein the airflow flows along the wing in a radial direction of the rotor while swirling in the spiral, and wherein the airflow being expelled downwards through the skirt causes an upward movement.

An aircraft (1) or drone for personal use, comprising a plurality of nozzles (N) distributed along a front wing (W) and in the rear of the aircraft (1), for discharging directional jets for controlling the attitude of the aircraft (1) in flight, and / or for discharging thrust jets designed to provide additional lift and / or additional thrust to the aircraft (1). Each nozzle (N) comprises a nozzle chamber (N1) and an outlet nozzle (N2) for the discharge of the jet. The aircraft (1) is equipped with a system (5) for generating a jet comprising a system (6) for supplying pressurized fuel to the chamber (N1) of the nozzle (N) and a system (7) for supplying combustion-supporting fluid under pressure to the chamber (N1) of the nozzle (N). The fuel supply system (6) comprises a plurality of electromagnetically driven injector devices (J), each associated with a respective nozzle (N); and a common rail (13) that receives the pressurized fuel from the high-pressure pump (11) and supplies it to the injector device (J). An electronic controller (E) maintains the pressure in the common rail (13) within a preset range of values and drives said injector means (J) independently of one another to inject pressurized fuel into the chamber (N1) of each nozzle (N) in order to obtain a mixture with a combustion-supporting fluid which initiates combustion by compression. The combustion causes an explosion which produces a jet of fluid at the outlet of the nozzle (N). The fuel supply system is configured according to the prior art known in the range of systems for supplying fuel to a diesel engine.

The invention relates to the technical field of aircraft design and control, in particular to an aerostat, a floating operation platform and floating operation equipment. The aerostat comprises a flight platform main body and a flight control system, wherein the platform main body is provided with a main lift force and attitude adjusting system and a jet flow micro-control system; the flight control system is configured to obtain state information of the aerostat; judging the motion state of the aerostat based on the state information; when it is judged that the system is in the state needing large-amplitude posture correction, the main lift force and posture adjusting system is controlled to work so as to conduct posture recovery; and controlling the jet flow micro-control system to work so as to accurately control the attitude and the position when the jet flow micro-control system is judged to be in a steady state needing precise displacement or attitude adjustment. According to the invention, decoupling of attitude and displacement of the unmanned aerial vehicle is realized, and high-precision and high-stability omnidirectional displacement control is realized on the premise of strictly maintaining a horizontal operation attitude.

An apparatus to determine take-off and landing times for a Rotary wing aircraft by the measurement and analysis of the atmospheric pressure changes around or within the aircraft. This may be done acco

An aircraft includes a fuselage and at least one primary wing having an upper surface, at least one recess in the upper surface and at least one conduit in fluid communication with the at least one recess. At least one ejector is disposed within the at least one recess and is configured to receive compressed air via the at least one conduit.

The invention provides an aircraft using a Gaussian electromagnetic propulsion device for air compression, the center of a saucer-shaped aircraft is an olive-shaped control center, an oxyhydrogen energy storage tank and an oxyhydrogen battery device are assembled in the olive-shaped aircraft life control center, and an aircraft body provides electric energy as required through an oxyhydrogen energy storage battery; two aircraft compressor blades are annularly stacked together in a big-end-up mode, a pair of electromagnetic propulsion coil sets is distributed on the edge of each of the upper compressor blade and the lower compressor blade of the aircraft, each pair of electromagnetic propulsion coil sets corresponds to a set of annular neodymium magnet guide rail, and the two sides of each guide rail are equally divided according to the sector radian of a circle. An inner arc and an outer arc of each equally-divided radian are each provided with a neodymium magnet, the neodymium magnets and electromagnetic coils matched with the neodymium magnets form an electromagnetic propeller, an electromagnetic propelling coil set on a gas compressor blade wheel enables two gas compressor blades to rotate oppositely after being powered on reversely, and power generation coils are additionally distributed on the outer edge of the large gas compressor blade wheel. Neodymium magnets distributed in an array shape are arranged at the positions, corresponding to the coils on the large compressor blade wheel, outside the aircraft body to form a generator device, and electric energy is generated along with rotation of the large compressor blade wheel. Three exhaust ports perpendicular to the exhaust direction are formed in the bottom of an annular pipe below the gas compressor, substances treated by the high-energy ionization accelerator are exhausted out of the aircraft through the exhaust ports, an exhaust port is also formed in the side face of the aircraft, and a direction adjuster is arranged in the aircraft. The attitude and direction of the aircraft are controlled through an electric hydraulic control valve, a direction regulator and a high-energy ionization acceleration device.

The invention relates to a disc-shaped manned aircraft with multiple bundled turbofan engines, which is mainly characterized in that a cockpit is taken as a center, the multiple turbofan engines are uniformly bundled and fixedly mounted around a main body bracket and the cockpit, and respective lift fans are driven to generate upward lift force; the bottom of the main body support is provided with a turbine shaft engine transmission turbine fan, the whole body is provided with a disc-shaped anti-collision net and a disc-shaped wind collection disc, the appearance of the whole body is in a flying saucer shape, the pneumatic layout of an existing saucer-shaped aircraft is improved, a flight control device is optimized, and the flight safety is improved; the flying saucer is reasonable in structural design, easy to manufacture, low in cost and safe and reliable to use, has novelty and creativity, and shows the basic structure of a modern flying saucer and the development direction of a future flying saucer.

A system is designed to control leading-edge vortex flow and liftoff on aircraft using supersonic jet (SSJs) positioned on the wing surface. Flight control inputs for flight attitude and status inputs from aircraft systems are processed to determine the necessary SSJ activation to influence the leading-edge vortex flow over the wing, achieving the desired flight attitude. The system can activate SSJs for specific durations, directions, and amount of activation levels. Additionally, the system can manage multiple SSJs to expel air in various directions, influencing the aircraft's roll, yaw, and pitch moments and change lift at trimmed pitch.

The invention belongs to the field of ducted fan design, and particularly relates to a ducted fan with a hydrogen combustion chamber, which comprises an outer casing, a fan rotor, a motor rotor, a motor stator, a hydrogen injection rod and an ignition electric nozzle, the fan rotor and the motor rotor are connected and are coaxially arranged in the outer casing; the motor stator is arranged at the rear end of the motor rotor, and the hydrogen injection rod is introduced from the outer end of the outer casing, enters the outer casing and can inject hydrogen to the rear end; a force transmission flame stabilizing support plate and an inner ring stabilizer are arranged in the outer casing, and the force transmission flame stabilizing support plate is arranged corresponding to an outer culvert of the outer casing. On the premise that the windward area and the length of the ducted fan are not changed through hydrogen with high combustion speed and high combustion efficiency, the thrust of the ducted fan is greatly improved through hydrogen combustion with the fan guide blades as supporting plates and the hydrogen combustion chamber with the inner cavity ignition design, and therefore the thrust of the whole combined power system meets the thrust requirement of an aircraft, and the thrust requirement of the aircraft is met. And rapid flight of the aircraft is realized.