The invention discloses a composite wing unmanned plane automatic pilot and a control method employed by the composite wing unmanned plane automatic pilot. Through the automatic pilot and the control guidance algorithm, a multi-shaft and fixed wing coordination control problem is solved, and full-state full-autonomous course flight of a composite wing unmanned plane is realized.

Composite wing unmanned plane automatic pilot and control method employed by composite wing unmanned plane automatic pilot

The invention provides a posture control device and control method for a vertical take-off and landing aircraft. The posture control device and control method are used for posture stabilization and control of the aircraft in vertical taken-off and landing/hovering modes. An air compressor located in a fuselage is adopted to serve as an independent air pressure source, air is guided from the air compressor to counter-acting force nozzles at the two ends and the tail of a wing correspondingly, and the posture of the aircraft in the vertical take-off and landing stages is controlled through the operating torque generated by changing the opening angles of the nozzles. Compared with the way that a thrust vector engine is directly adopted to control the posture or air is guided to nozzles from an air compressor of an engine to control the posture, the problems that thrust loss of the engine is caused when air is guided from the engine, and coupling of lifting force and required posture control operating force is caused are solved by the adoption of the method, and the reliability is higher.

Posture control device and control method for vertical take-off and landing aircraft

The invention discloses an automatic take-off control strategy design for a small unmanned helicopter, comprising steps of 1 determining whether a take-off order is responded, if yes, automatically starting up an engine and applying rotation speed stable control, 2 recording information of current longitude, height and yaw angle and solving mean values,3 if the step 2 determines that the rotation speed of the engine is stable, performing self-increscent on the collective pitch, 4 if the step 3 determines that the collective pitch reaches the pre-off-land collective pitch, performing plane position and posture control on the helicopter and continuously performing self-increment on the collective pitch until the helicopter is off the land, 5 if the step 4 determines that the helicopter is off the land, updating the collective pitch balancing value and invoking a vertical channel control law until the preset take-off height is approached, and if the step 5 determines that the take-off height is reached, and invoking a spot hovering control law to finish the take-off. The automatic take-off control strategy design for the small unmanned helicopter can improve the automatic take-off capability of the miniaturized unmanned helicopter and enhances the usage range, and is small in complexity and high in reliability.

Automatic take-off control strategy design of small unmanned helicopter

The invention discloses a multimodal flight conversion control method for a hybrid layout rotary-wing unmanned aerial vehicle, and relates to the technical field of flight control for unmanned aerial vehicles. Based on composite multimodal multipurpose aircrafts, the hybrid layout rotary-wing unmanned aerial vehicle comprises five types of flight modal; and aiming at a take-off/air-drop stage, a task arriving stage, a task executing stage, a task evacuating stage and a landing/recovery stage respectively, the multimodal flight conversion control method provides seven modal conversion modes and conversion opportunities. According to the multimodal flight conversion control method provided by the invention, the hybrid layout rotary-wing unmanned aerial vehicle can be reasonably converted among various modal types to meet different task requirements, and the multimodal flight capability and the multitask capability of the hybrid layout rotary-wing unmanned aerial vehicle can be sufficiently exerted; and the general land take-off and landing capability of the hybrid layout rotary-wing unmanned aerial vehicle can be sufficiently exerted, the flexible water-surface/carrier-borne/vehicle-mounted/airborne drop and other deployment modes of the hybrid layout rotary-wing unmanned aerial vehicle can be utilized, and the high-speed cruise capability and the low-altitude and low-speed capability of the hybrid layout rotary-wing unmanned aerial vehicle can be sufficiently exerted, so as to achieve the rapid arriving and evacuating as well as low-speed and low-altitude task executing capabilities of the hybrid layout rotary-wing unmanned aerial vehicle.

Multimodal flight conversion control method for hybrid layout rotary-wing unmanned aerial vehicle

The invention discloses a composite jump takeoff system for a heavy gyroplane with jump takeoff capability. The tail end of an output shaft of an engine is connected with a tail vectored thrusting duct through a sliding friction clutch; a first helical bevel gear is placed on the output shaft of the engine; a second helical bevel gear is engaged with the first helical bevel gear; an output end of the second helical bevel gear is connected with a third helical cylindrical gear through an electromagnetic clutch; the third helical cylindrical gear in a first path of transmission is engaged with a fourth helical cylindrical gear; the fourth helical cylindrical gear is connected with a fifth helical cylindrical gear through a spline shaft; the fifth helical cylindrical gear is engaged with a sixth helical cylindrical gear; the sixth helical cylindrical gear is connected with a main rotor through a main rotor shaft; the third helical cylindrical gear in a second path of transmission is connected with a seventh helical cylindrical gear through a spline shaft; the seventh helical cylindrical gear is engaged with an eighth helical cylindrical gear; and the eighth helical cylindrical gear is connected with a flywheel through an overrunning clutch. Through the adoption of the composite jump takeoff system for the heavy gyroplane with the jump takeoff capability, disclosed by the invention, the jump takeoff of the gyroplane can be achieved.

Composite jump takeoff system for heavy gyroplane with jump takeoff capability

The invention discloses a composite type multi-mode multi-purpose aircraft, and belongs to the technical field of overall design of aviation flight vehicles. The aircraft comprises a body of a fixed wing aircraft, a driving/autorotation rotor wing system, an expelling aero-engine and a flying control system, wherein the driving/autorotation rotor wing system comprises paddle hubs and paddles; the paddles are hollow, and guide tubes B are communicated with the inner parts of the paddles; an H2O2 catalysis decomposition engine is mounted at the tail end of each paddle; the H2O2 catalysis decomposition engines are connected with the guide tubes; the guide tubes are communicated with guide tubes A; the guide tubes A are connected with an H2O2 storage box. The aircraft disclosed by the invention has the property of vertical/short-distance lifting and suspension, or even can achieve certain back flying and side flying, and can also fly forwards at a high speed; due to adoption of paddle tip air injection driving/autorotation wings, no reaction torque is generated in any mode, and thus a tail rotor as well as a speed reduction transmission and control mechanism of an ordinary helicopter are canceled; the differential thrust for thrusting an aero-engine is adopted to control to achieve steadiness and control in flying direction at a low speed, the waste weight and the energy consumption are reduced, the cost is lowered, the complexity is alleviated, and the flying security in a complex environment is effectively improved.

Yan Kun

Papers

Composite type multi-mode multi-purpose aircraft

Multimodal flight conversion control method for hybrid layout rotary-wing unmanned aerial vehicle