固体火箭主动段终端多约束能量管理制导方法

针对不同高度的单箭多轨道运载任务,提出了一种多级固体火箭上升段分步满足终端多约束的能量管理制导方法。火箭前期飞行通过程序指令控制基准弹道,以满足期望的高度与当地弹道倾角约束为目的将弹道优化转参数优化问题处理,减少了约束条件；后期飞行通过姿态交变机动的闭路能量管理制导方法,耗散多余能量控制飞行速度,达到了满足终端速度、高度、倾角等多约束条件的火箭不同高度入轨。仿真结果表明,该能量管理制导方法有效可行且在不同轨道运载任务中具有较好的适用性。

Energy management based guidance of solid rocket with multi constraints

For carrier missions on different orbits of solid rockets, the segmented ascent guidance with multiple terminal constraints is proposed based on energy management. Flight trajectory is controlled by program commands during the former segment, in which constraints can get reduced as a result of the transition from trajectory optimization to parameters optimization. Considering that increasing angle of attack can decrease velocity gain, the latter segment, the last stage of the rocket, adopts a closed loop energy management guidance to consume the redundant fuel. By alternating attitude the rocket achieves different orbits with terminal constraints of velocity, altitude and local trajectory angle. Simulation results indicate that the proposed guidance strategy shows theoretical feasibility as well as good adaptability in multiple carrier missions.