针对突防发动机轨控推力较小,难以产生在拦截器末制导段内成功突防所需的机动过载的实际情况,提出避开拦截器机动性能最强的末制导段,而选择在拦截器自由飞行段和末制导结束后实施“二次机动变轨”的突防方案,旨在解决弹道中段机动突防方案的有效性问题.建立了推力方向、推力持续时间等轨控发动机主要控制参数的优化规划模型,提供了基于遗传算法的规划决策算法技术.仿真结果验证了“二次变轨”机动突防方案的可行性,可将成功突防所需的机动过载降低1个数量级.%Aiming at the fact that the trajectory-control thrust of penetration motor is too small to bring the required maneuvering overload of successful penetration in the terminal guidance phase,the penetration program of "secondary maneuver change trajectory" was proposed in the freedom sliding phase and the ending guidance phase,instead of the terminal guidance phase of the most strong maneuver ability, for solving the validity of the midcourse maneuver penetration program. The optimal program model was bu-it,including the main control parameters of trajectory-control motor,such as direction and duration of thrust,and the programming and decision-making technique based on inherited algorithm were provided. The simulation results validate the feasibility of "secondary orbit varying" maneuver penetration program, which can reduce the required maneuvering overload of successful penetration by one order of magnitude.
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