The embodiment of the invention discloses an attack angle protection control method for a large amphibious aircraft. The attack angle protection control method comprises the following steps: respectively carrying out amplitude limiting and filtering processing on signals used by an attack angle protection function; determining an attack angle protection maximum value and an attack angle protection starting value according to the Mach number and the flap configuration; calculating an attack angle protection weight coefficient and a control stability augmentation weight coefficient; performing instruction conversion on the filtered steering column displacement signal to obtain an attack angle increment instruction; calculating to obtain an attack angle protection integral branch instruction, an attack angle protection proportion branch instruction and an attack angle protection differential branch instruction; and integrating the attack angle protection integral branch instruction, the attack angle protection proportion branch instruction, the attack angle protection micro branch instruction and the control stability augmentation function instruction to obtain an attack angle protection elevator instruction. According to the technical scheme provided by the embodiment of the invention, the problem that the switching transient state is easily caused by instruction mutation in the process of taking a large value in the existing attack angle protection scheme is solved.
本发明实施例公开了一种大型水陆两栖飞机的迎角保护控制方法,包括:对迎角保护功能所使用信号分别进行限幅以及滤波处理;根据马赫数和襟翼构型确定迎角保护最大值和迎角保护启动值;计算迎角保护权重系数与控制增稳权重系数;对滤波后的驾驶杆位移信号通过指令转换得到迎角增量指令;计算得到迎角保护积分支路指令、迎角保护比例支路指令和迎角保护微分支路指令;将迎角保护积分支路指令、迎角保护比例支路指令、迎角保护微分支路指令与控制增稳功能指令进行综合得到迎角保护升降舵指令。本发明实施例提供的技术方案解决了现有迎角保护方案,极易在取大值的过程中因指令突变造成切换瞬态的问题。
Attack angle protection control method for large amphibious aircraft
一种大型水陆两栖飞机的迎角保护控制方法
2024-04-19
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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