RLV离轨制动耗尽关机制导方法研究

Research on depleted shutdown guidance approach of reusable launch vehicle deorbit

针对使用固体火箭发动机的航天器离轨制动问题,提出了将速度增益制导与随机剩余燃料耗散相结合的混合制导方法。根据再入接口条件,给出了基于标准推力的剩余视速度模量预测与能量管理模型;重点推导了连续推力条件下飞行器能量与动量矩的变化特性,并据此得出了通过控制攻角方向切换来控制能量的随机剩余燃料耗散方法。仿真结果表明,推力偏差为15%、随机剩余燃料质量为120 kg时,再入点参数仍能保持较高精度。研究结论可为在轨航天器的离轨制动耗尽关机制导问题提供参考方案。

To address the deorbit problem of solid rocket-powered spacecraft,a depleted shutdown hybrid guidance method including energy dissipation and closed-loop guidance was presented.According to entry interface conditions,the models of surplus apparent velocity module prediction and energy management were given based on standard thrust assumption.Given continuous thrust,features of spacecraft energy and angular momentum were analyzed,based on which,a random surplus fuel dissipation approach was proposed via switching the direction of the angle of attack to achieve energy control.Simulations indicate that under the conditions of 15％ thrust error and 120 kg random surplus fuel,the guidance method still possesses high precision.The conclusions could provide reference for the implementation of depleted shutdown guidance of the real spacecraft deorbit.