飞机纵向控制中的法向过载设计

Design of Normal Acceleration Control of Aircraft Vehicle in Longitudinal Control Law

以某飞机为研究对象,通过在俯仰角速度控制回路上加上法向过载回路作为外回路,实现飞机纵向控制中的法向过载设计.反馈增益的设计则选用输出反馈线性二次型算法,该算法可以同时闭合所有反馈环节,设计出所需要的反馈系数.分析了选用法向过载控制回路的合理性.最后,分别给出了低空、中空、高空该控制回路的阶跃响应,验证了该控制规律的有效性和正确性.

In this paper, one aircraft is used as the study model. It can realize the normal acceleration control that the pitch rate feedback is regarded as inner-loop and the normal acceleration feedback is the outer-loop. LQR is used to design the feedback gain matrix ,whose advantage is that it can simultaneously close all the loops and obtain all feedback gains needed. Moreover, the practicability of the normal acceleration feedback is analyzed. Finally, the graphics of C-star response of control structure are given to approve the availability and the validity of the control law.