摘要：【中文】本发明是关于一种采用角加速度提供阻尼的飞行器过载回路设计方法，属于飞行器控制技术领域，其特点在于采用角加速度计测量飞行器的偏航角加速度为过载外回路提供阻尼，再采用加速度计测量飞行器的线加速度得到侧向过载，并与期望过载指令相比较，得到过载误差信号。对过载误差信号进行两次积分组成过载误差综合积分信号以消除过载指令与姿态指令之间的转换静差问题。再引入飞行器姿态角加速度信号的非线性变换信号、偏航角速率的比例信号以及飞行器角速度信号的二次非线性变换信号组成过载回路的阻尼信号，输出给姿态稳定回路，即可实现过载跟踪的控制目标。该方法解决了传统过载控制的静差问题与阻尼不足问题。 【EN】The invention relates to a method for designing an aircraft overload loop by adopting angular acceleration to provide damping, which belongs to the technical field of aircraft control and is characterized in that an angular accelerometer is adopted to measure the yaw angular acceleration of an aircraft to provide damping for an overload outer loop, then the accelerometer is adopted to measure the linear acceleration of the aircraft to obtain lateral overload, and the lateral overload is compared with an expected overload instruction to obtain an overload error signal. And integrating the overload error signal twice to form an overload error comprehensive integral signal so as to eliminate the problem of conversion static difference between the overload instruction and the attitude instruction. And then introducing a nonlinear transformation signal of the aircraft attitude angular acceleration signal, a proportional signal of the yaw rate and a secondary nonlinear transformation signal of the aircraft angular velocity signal to form a damping signal of an overload loop, and outputting the damping signal to an attitude stabilization loop, so that the control target of overload tracking can be realized. The method solves the problems of static error and insufficient damping of the traditional overload control.