姿态角单次调整的固体运载火箭耗尽关机能量管理方法

固体运载火箭传统耗尽关机制导方法姿态角调整次数过多,不利于控制系统设计。提出了姿态角单次调整的耗尽关机能量管理策略:以火箭的待增视速度方向为基准,通过计算火箭所需耗费的视速度,优化选取火箭的初、末姿态角;火箭以恒定角速率从初姿态角变为末姿态角,达到末姿态角时保持恒定,直至耗尽关机。仿真结果表明,新方法在满足火箭的终端速度约束条件下,视速度模量耗费百分比超过30%,且姿态角单向调整,有利于控制系统的工程设计。

Depleted Shutdown Energy Management Approach for Solid Launch Vehicle with Singular Attitude Angle Adjustment

Traditional depleted shutdown guidance approaches for solid launch vehicle have excessive attitude angle adjustment times, which lead to difficulties of the control system design. A depleted shutdown guidance method with singular attitude angle adjustment is proposed in this paper. The required apparent velocity is used as a reference, the initial and final values of the rocket attitude angle are chosen by computing the apparent velocity which is to be consumed. The attitude angle is changed from the initial value to the final value with a constant angle rate, and then the attitude is kept constant till depleted shutdown. The simulation results show that the proposed method with singular attitude angle adjustment satisfies the rocket"s terminal velocity constraint and that the percentage of consumed apparent velocity mode is more than 30%. Furthermore, the singular attitude angle adjustment strategy will benefit the control system design.