System and method for multi-power integrated flight control applied in micro air vehicle

Abstract

The invention provides a system and method for multi-power integrated flight control applied in a micro air vehicle. The system comprises a flight control computer, a flight parameter sensor, a PID controller, a yaw propeller power system, a posture propeller power system and a main propeller power system, wherein an output end of the flight parameter sensor is connected to an input end of the flight control computer, and an output end of the flight control computer is separately connected to the yaw propeller power system, the posture propeller power system and main propeller power system by the PID controller. The system and method provided by the invention have the advantages that (1) a layout manner of a main propeller, a posture propeller and a yaw propeller is applied, so that a load of the posture propeller can be effectively reduced during a flight course, efficiency of a power system of the air vehicle can be effectively increased, and flight duration of the air vehicle can be increased; and (2) integrated control is carried out to the multiple sets of power systems of the air vehicle, so that the problem that lift force of the main propeller of the air vehicle is unstable and the problem about reverse torque balance of the main propeller can be solved, and finally autonomous flight of the multi-rotor air vehicle with the new layout can be realized.

Description

technical field [0001] The invention belongs to the technical field of aircraft flight control systems, and in particular relates to a multi-power fusion flight control system and method applied to micro aircraft. Background technique [0002] The multi-rotor aircraft can achieve fixed-height and fixed-point hovering through multi-rotor drive, and can quickly change the attitude of the fuselage in the hovering state. It has good maneuverability and can carry loads to complete flight tasks. [0003] In the prior art, a conventional multi-rotor aircraft is mainly driven by a plurality of identical independent driving devices. For example, for a hexa-rotor aircraft, six identical rotors are used for driving, and the six rotors are evenly distributed around the main body of the aircraft. The functions of the rotors arranged around the main body of the aircraft include providing lift and attitude control. [0004] Due to various limitations, the multi-rotor aircraft with the abo...

AI Technical Summary

Problems solved by technology

[0004] Due to various limitations, the multi-rotor aircraft with the above-mentioned conventional layout has the disadvantage of low flight efficiency, which cannot guarantee the long-term stable flight of the multi-rotor aircraft

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