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月球返回舱高速返回地球,再入动能非常大,使得月球返回舱的再入制导精度难于得到保证。采用传统的制导方法很难同时满足精度、航程、过载和热量等要求。针对以上不足,为了设计一种安全、有效且适合大范围航程的再入制导律,结合解析预测制导和数值预测制导的优点,设计了一种改进的月球返回再人制导律。具体方法是在阿波罗解析制导方法的基础上,通过在上升段和弹道段使用数值预测校正算法(NPC)提高了纵程能力。又将决策权提前至初始滚转段,并采用变化的常值阻力加速度。仿真结果表明,改进设计的制导律提高了航程能力和落点精度,降低了过载和总热量,使动态性能得到改善,改进方法可为月球返回再入制导优化设计提供依据。
The lunar return capsule returns to Earth at a high speed and the reentry kinetic energy is very large, making it difficult to guarantee the accuracy of reentry lunar return capsule guidance. The traditional guidance method is difficult to meet the accuracy, range, overload and heat requirements. In order to design a reentry guidance law that is safe, effective and suitable for a wide range of voyage, aiming at the above shortcomings, an improved lunar returning remanning guidance law is designed by combining the advantages of predictive guidance and numerical guidance. The specific method is based on the Apollo analysis guidance method, through the use of numerical predictive correction algorithm (NPC) in the ascending section and the ballistic section to improve the ability of the longitudinal. In turn, the decision-making power is advanced to the initial roll segment, and a constant constant acceleration acceleration is used. The simulation results show that the improved design of the guidance law improves the range capability and placement accuracy, reduces the overload and total heat, and improves the dynamic performance. The improved method can provide the basis for the lunar return reentry guidance optimization design.