Airplane angle-of-attack protection control method

Abstract

The invention discloses an airplane angle-of-attack protection control method. The airplane angle-of-attack protection control method comprises the steps of 1 collecting an airplane signal; 2 calculating a maximum angle-of-attack; 3 calculating an obtained angle-of-attack threshold; 4 calculating a driving rod vertical alarm displacement and an instruction angle-of-attack; 5 obtaining a differential branch signal, a proportion branch signal, an integration branch signal and an integration branch logic operation result; 6 outputting, controlling and stabilizing the larger one of the integration branch signal and the integration branch signal; 7 determining the value of step 6; 8 determining a gain so as to adjust a real angle-of-attack of the airplane; and 9 obtaining a yield value of the differential branch signal, the proportion branch signal and the integration branch signal when the airplane is in different states. Through adoption of the airplane angle-of-attack protection control method, a connectional initial lead of the angle-of-attack protection function can be reduced; the angle-of-attack protection function can be realized; and a good robustness is provided to the system.

Description

technical field [0001] The invention relates to the technical field of aviation flight control, in particular to an aircraft angle of attack protection control method. Background technique [0002] In the flight control system, the function of maintaining the angle of attack is the most important content of the boundary protection function. The currently used angle of attack limiter realizes the angle of attack limiting function by offsetting the pilot's control command through the angle of attack feedback. If the advance value of the angle-of-attack limit function is small, the feedback gain must be set to a large value. Although this can achieve the purpose of angle-of-attack limit, the robustness of the control law for large angle-of-attack is very poor, and the sensor signal has a slight error in the angle of attack. The limiting function will become worse or even fail, endangering flight safety. If the angle-of-attack limiting function is switched on in advance, the f...

AI Technical Summary

Problems solved by technology

If the advance value of the angle-of-attack limit function is small, the feedback gain must be set to a large value. Although this can achieve the purpose of angle-of-attack limit, the robustness of the control law for large angle-of-attack is very poor, and the sensor signal has a slight error in the angle of attack. The limiting function will become worse or even fail, endangering flight safety

If the angle-of-attack limiting function is switched on in advance, the feedback gain is set to be small, so although the angle-of-attack limiting function can be realized and the control system with a large angle of attack has certain robustness, the control law must be stabilized by the control by a large amount in advance. Switching to the high angle of attack control law, the pilot's effective command decreases, the stick force increases, and the pilot's burden increases

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