可重复使用航天器再入飞行综合仿真模型研究

Integrated Entry Simulation Model for Reusable Launch Vehicle

提出并建立了一种可重复使用航天器(RLV)再入飞行综合制导/控制仿真模型。在精确的RLV非线性飞行动力学模型的基础上,综合考虑任务限制条件和舵面完好状况,建立飞行管理模块,实现了标称条件下飞行任务的管理、非标称条件下对制导/控制律的重构以及严重事故时任务中断策略的实施。仿真程序利用Stateflow技术,构筑状态转换器和算法公用接口,保证了便捷应用的能力。以某型RLV为例,在考虑到不同舵面故障的情况下,通过仿真结果表明,该方法便捷、有效。

A novel integrated guidance/control simulation model with high accuracy for reusable launch vehicle （RLV） was proposed. Based on the accurate nonlinear flight dynamics of RLV, the flight manager was established, featuring the flight corridor and effectors health status, which meets the requirement of nominal flight management, guidance/control reconfiguration under off-nominal conditions, and transitioning to an abort mode in response to a more serious situation. Afterwards, utilizing the finite state machine and algorithm interface via Stateflow technique, the convenience and applicability of implementation are enhanced remarkably. Integrated guidance/control reconfiguration in the presence of effector failures is presented to demonstrate the capacity of this proposed model.