具有落角约束的弹道导弹再入末制导律设计

Design of the reentry terminal guidance law with constraint of impact angle for ballistic missile

摘要:

针对弹道导弹再入段带有终端落角约束的末制导问题,本文基于最新发展起来的模型预测静态规划技术,设计一种既可以精确地打击地面目标、又可以满足终端碰撞角要求的非线性次优制导律．本文针对弹道导弹打击地面静止目标和机动目标等飞行场景进行了数值仿真,仿真结果表明:采用该制导律可以使在整个再入飞行场景中控制能量较小．与其他具有落角约束的制导律相比,该制导律并没有对非线性运动模型采用线性化的假设,且其计算复杂性明显低于基于最优控制的终端角约束制导律．

Abstract:

For the reentry terminal guidance problem of ballistic missile with constraint of impact angle, a nonlinear suboptimal guidance law that not only precisely attacks the ground target, but also satisfies the requirement of the terminal angle is designed based on the model predictive static programming technology proposed recently. The flight scenes that the ballistic missile attacks against stationary targets and maneuvering targets are simulated in this paper. The simulation results show that the designed guidance law spends less energy than the APN law. Compared with other guidance laws with impact angle constraint, the designed guidance handles the nonlinear problem as it is (without linearization), and the computational complexity is significantly lower than the guidance law with the angle constraint based on optimal control theory.