一型自动飞控系统纵向操纵不对称的分析解决

Analysis and solution of the asymmetric longitudinal control for an Automatic Flight Control System

针对一型自动飞行控制系统在空中进行纵向操纵时出现的不对称现象，通过对飞行控制系统的理论分析，并充分利用飞行数据结合控制律的计算，确定了根本原因是由于存在初始升降速度，从而造成高度保持模态和俯仰操纵模态的计算基准出现差异。本文提出了对控制律中的俯仰角回零基准值进行修正以消除积分式控制律存在高度静差的解决方案，经验证能够有效解决操纵不对称问题。

For the asymmetry of longitudinal control of an automatic flight control system in the air, through the analysis of the theory of the flight control system, and make full use of flight data combined with the calculation of control law, determine the root cause is due to the initial vertical speed, resulting in altitude hold mode and pitch control mode calculation benchmark differed.Solution proposed in this paper is to modify the zero setting value of pitch angle to eliminate the steady-state error of altitude of the integral control law, verificated can effectively solve the problem of asymmetric control.