运载火箭姿态控制多速率陀螺融合方法

Multi-rate Gyro Fusion Method for Launch Vehicle Attitude Control

针对柔性火箭姿态测量中弹性信号会严重影响姿控系统设计和稳定性的问题,提出基于遗传算法的速率陀螺融合方法。首先,以降低姿控回路摆角指令传递函数的弹性峰值为目标,提出多速率陀螺融合方法的目标函数;其次,将多速率陀螺融合方法转化为多约束非线性规划问题,采用遗传算法求解多速率陀螺融合方法;最后,研究多速率陀螺融合方法对火箭姿态控制回路弹性信号的影响,以及对火箭控制器性能的影响。仿真结果表明:多速率陀螺融合方法可以有效减弱火箭姿态控制回路中的弹性信号,提高火箭控制器的性能,以增强火箭姿控系统的稳定性,降低火箭控制器设计难度。

In order to solve the problem that the elastic signal in the attitude measurement of flexible rocket will seriously affect the design and stability of the attitude control system, a multi-rate gyro fusion method based on the genetic algorithm is proposed in this paper. First, the objective function of the multi-rate gyro fusion method is presented to reduce the elastic peak value of the swing angle instruction transfer function of the attitude control loop, by which the multi-rate gyro fusion method is transformed into a multi-constraint nonlinear programming problem. Then, the genetic algorithm is used to solve the multi-rate gyro fusion method, and the effects of the multi-rate gyro fusion method on the elastic signal of the attitude control loop and the performance of the rocket controller are studied. The simulation results show that the multi-rate gyro fusion method can effectively reduce the elastic signal in the attitude control loop of the rocket and improve the performance of the rocket controller. The stability of the rocket attitude control system is improved, and the difficulty in the rocket controller design is reduced.