Attitude correction control system and method of a four-rotor aircraft

Abstract

The invention discloses an attitude correction control system and method of a four-rotor aircraft. The control system comprises a flight control main controller, a flight attitude acquisition module,a driving module, a wireless communication module, a GPS module, a power management module and a camera module. The flight attitude acquisition module, the driving module, the wireless communication module, the GPS module, the power management module and the camera module are connected with the flight control main controller. An unmanned aerial vehicle attitude control system comprises a sensor data resolving and processing system, a motor rotating speed control system and a wireless data communication system. According to the invention, cascade PID closed-loop control is carried out on the attitude of the four-rotor aircraft, so that the PWM duty ratio for controlling the rotating speed of the motor is adjusted; and meanwhile, the four-rotor aircraft feeds back the position information obtained from the GPS module and current attitude data of the aircraft to a remote control terminal through a wireless transceiving module, so that the operator checks the current flight state of the aircraft in real time and thus descending processing is performed timely in an abnormal state of the flight to minimize the losses.

Description

technical field [0001] The invention relates to a comprehensive control system for the flight attitude of a quadrotor aircraft, in particular to a control method for comprehensively feeding back the data to the four motors of the quadrotor after collecting and processing the attitude data of the quadrotor aircraft. Background technique [0002] In quadrotor aircraft technology, the design of flight control system has always been one of the concerns of many researchers in the field of control. The position change of quadrotor aircraft needs to be obtained through attitude adjustment, and there is a strong coupling relationship between attitude and position. To design the position and speed control of quadrotor aircraft, the accuracy of attitude control must first be improved. It can be seen that attitude control is a quadrotor The core part of the aircraft system design determines the flight state and flight performance of the quadrotor aircraft. At present, the most commonl...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the unstable flight attitude of the quadrotor aircraft is easily disturbed by the external force during the flight attitude control process.

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