大型民机系统纵向Nz控制律设计

针对国内民机系统纵向稳定性较差、飞机纵向短周期模态响应稳定性不足等问题，以某大型民机为研究对象，基于特征结构配置方法，利用逆模型的思路确定控制系统前馈增益系数，并基于某典型配平状态点，利用线性模型设计该飞机纵向控制律。线性仿真分析中，利用俯仰角速率q响应准则评价控制方案效果。仿真结果表明，采用特征结构配置方法设计的纵向飞行控制律具有良好控制效果，可以改善系统飞行品质使其达到一级飞行品质要求，相比于经典控制理论，通过特征结构配置方法进行纵向Nz控制律设计可以一次性确定反馈增益系数，缩短控制律设计时间。

Longitudinal Nz Control Law Design for the Large Civil Aircraft System

Aiming at the problems of poor longitudinal stability of domestic civil aircraft system and insufficient longitudinal short period modal response stability of aircraft， this paper takes a large civil aircraft as the research object， studies the method based on characteristic structure configuration， and uses the idea of inverse model to determine the feedforward gain coefficient of control system. Besides， based on a typical trim state point， the longitudinal control law of the aircraft is designed by using the linear model. Through the linear simulation analysis， the quality effect of the control scheme is evaluated by using the pitch rate q response criterion. The simulation results show that the longitudinal flight control law designed by eigenstructure configuration method has good control effect and can improve the flight quality of the system to meet the requirements of the first level flight quality. Especially， compared with the traditional control theory， the feedback gain coefficient can be determined once and the design time of the control law can be shortened.