Fault tolerance flight control system and method based on control surface faults
A flight control system and rudder surface technology, applied in the general control system, control/adjustment system, attitude control, etc., can solve problems such as sudden changes in parameter values, failure to quickly identify faulty systems, and inability to guarantee controller control, etc., to reduce The effect of design difficulty
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[0033] The present invention will be further described below in conjunction with specific drawings and embodiments.
[0034] like figure 1 As shown, the aircraft has five main control surfaces, namely left aileron, right aileron, left elevator, right elevator and rudder. All control surfaces are completely independent, i.e. the ailerons (or elevators) can be deflected up, down independently or both ailerons (or two elevators) can be deflected in the same direction simultaneously. This configuration allows the ailerons to generate a pitching moment and the rudder to generate a rolling moment.
[0035] like figure 2 Shown: A fault-tolerant flight control system based on rudder surface failure, including:
[0036] The sensor arranged at the corresponding position of the aircraft body: output the measured parameter value; the sensor arranged at the corresponding position of the aircraft body includes: a gyroscope installed in the inertial navigation system of the aircraft body...
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