Control crosslinking method of attitude and heading systems and flight control system

Abstract

The invention relates to a control crosslinking method of attitude and heading systems and a flight control system. The control crosslinking method is applied to the field of helicopter control. A horizon sensor and a gyro magnetic compass system which are arranged on the original helicopter are canceled, the two attitude and heading systems are added, the horizon sensor and the gyro magnetic compass system are replaced by the attitude and heading systems to provide the attitude and heading information for the flight control system, and the indication function of the gyro magnetic compass system and the horizon sensor is replaced by the attitude and heading systems. The control crosslinking method comprises installation of the attitude and heading systems, lead laying, ground energization and a flight test. According to the control crosslinking method of the attitude and heading systems and the flight control system, the use requirements of the flight control system can be met, meanwhile the stability and the reliability of the flight control system can be improved, the expansibility is achieved, troubleshooting of the flight control system is convenient, and meanwhile adaptive changes of the flight control system are not required.

Description

technical field [0001] The control cross-linking method of the attitude system and the flight control system of the present invention is applied in the field of helicopter control. Background technique [0002] The heading and attitude information required by the flight control system of a certain type of helicopter are provided by 2 sets of gyro magnetic compass systems and 2 sets of horizon. Using the above two systems to provide signals has the following defects: [0003] (1) The accuracy of the gyro magnetic compass system is low, and it is susceptible to external magnetic field interference, low anti-interference ability, low long-term accuracy, which is not conducive to maintaining the heading accuracy of the flight control system; [0004] (2) The accuracy of the horizon is low, which is not conducive to maintaining the attitude accuracy of the flight control system. At the same time, when the helicopter flies with a large slope, the output data of the two sets of hor...

AI Technical Summary

Problems solved by technology

[0003] (1) The accuracy of the gyro magnetic compass system is low, and it is susceptible to external magnetic field interference, low anti-interference ability, low long-term accuracy, which is not conducive to maintaining the heading accuracy of the flight control system;

[0004] (2) The accuracy of the horizon is low, which is not conducive to maintaining the attitude accuracy of the flight control system. At the same time, when the helicopter flies with a large slope, the output data of the two sets of horizons tend to be quite different, causing the flight control system to alarm and automatically disconnect. Make the flight control system unusable;

[0005] (3) Both systems have no self-test function. When the flight control system fails, the fault source cannot be quickly judged, so it is not conducive to the troubleshooting of the flight control system;

[0006] (4) The cross-linking signal is scattered and the integration level is low, which is not conducive to helicopter maintenance;

[0007] (5) Both the gyro magnetic compass system and the horizon instrument use foreign equipment, and there are difficulties in maintenance of the two sets of equipment, which is not conducive to long-term localization development;

[0008] Both systems can only output analog signals, which is not conducive to the realization of digitalization of helicopters

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