大气层外拦截弹中段制导研究

Research on Midcourse Guidance for Fuel-Exhaustion-Shutoff exo-Atmospheric Interceptor

大气层外拦截弹中制导的终端约束是拦截弹处于零控拦截流形上。针对目标与拦截弹引力加速度差的几种简化模型,推导了相应的零控拦截流形表达式,并进行了定量的精度分析。在此基础上,针对耗尽关机的固体燃料发动机,设计了基于剩余速度增量的制导律。通过构造虚拟剩余速度增量映射避免了剩余速度增量带来的计算奇异,并提高了制导精度对装药燃速偏差的鲁棒性。仿真表明,采用该制导律推力方向平稳,制导精度与相应的零控拦截流形精度相当且鲁棒性好。

The terminal constrain of the midcourse guidance for an exo-atmospheric interceptor is to be on the zero-effort-intercept manifold. The expression of the zero-effort-intercept manifold for several simplified model of the gravitational acceleration difference between the target and the interceptor was deduced, the quantitative precision analysis was also made. Then the guidance law based on the remaining velocity increment for an interceptor with fuel-exhaustion-shutoff solid rocket motor was put forward, and a virtual remaining velocity increment mapping was introduced to eliminate the singularity coming with the remaining velocity increment, and to improve the robustness of the guidance precision to the burning speed error of the fuel. Simulations have shown that, stable thrust and precision consistent with the corresponding zero-effort-intercept manifold come with the guidance law, and perfect robustness is also guaranteed.