The invention relates to systems and methods for pitch axis envelope limiting of an aircraft. An example method of limiting an aircraft to a pitch axis envelope includes determining aircraft state limits associated with multiple pitch axis variables of an aircraft, determining predicted aircraft states, comparing the predicted aircraft states to the aircraft state limits to produce aircraft stateerrors, translating the aircraft state errors into a set of positive and negative limit elevator commands, selecting a highest priority positive limit elevator command, selecting a highest priority negative limit elevator command, limiting a primary pitch axis control law elevator command of the aircraft to a value that is less than or equal to the highest priority positive limit elevator commandand greater than or equal to the highest priority negative limit elevator command, and controlling the aircraft according to the primary pitch axis control law elevator command limited to the value.

    本发明涉及对飞行器进行俯仰轴包络限制的系统与方法。将飞行器限制在俯仰轴包络内的示例方法包括:确定与飞行器的多个俯仰轴变量相关联的飞行器状态限值;确定预测飞行器状态;将预测飞行器状态与飞行器状态限值进行比较以产生飞行器状态误差;将飞行器状态误差转换为正限值升降舵命令集和负限值升降舵命令集;选择最高优先级的正限值升降舵命令;选择最高优先级的负限值升降舵命令;将飞行器的主俯仰轴控制律升降舵命令限制为小于或等于最高优先级的正限值升降舵命令且大于或等于最高优先级的负限值升降舵命令的值;以及根据被限制为该值的所述主俯仰轴控制律升降舵命令来控制飞行器。


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    Title :

    Systems and Methods for Pitch Axis Envelope Limiting of an Aircraft


    Additional title:

    对飞行器进行俯仰轴包络限制的系统与方法


    Contributors:

    Publication date :

    2021-03-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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