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研究了以第二宇宙速度返回地球的载人探月飞船的再入制导律设计问题.针对基于落点分析的数值预测-校正算法不能有效满足再入过程的气动过载约束条件的问题,提出一种基于解析计算的常值气动过载算法与基于数值积分的预测-校正技术相结合的融合再入制导方案,在线生成了同时满足过载约束和落点精度要求的再入轨迹.数值仿真表明提出的制导算法不仅能满足达到高精度着陆的要求,还能满足气动过载约束要求.在一定的再入初始条件下,探月返回飞船可以不必采用逻辑复杂的阿波罗式跳跃再入方案.这一方案可为即将展开的载人探月活动制定月-地返回轨道和再入策略提供参考.
This paper studies the design of reentry guidance law of manned moon-going spacecraft returning to the Earth at the second cosmic velocity.Aiming at the problem that the numerical prediction-correction algorithm based on landing point analysis can not effectively meet the aerodynamic overload constraint conditions of reentry process, Based on the analytic computation of the common aerodynamic overloading algorithm and the numerical integration-based predictive-correction technique, the fusion reentry guidance scheme is used to generate the reentry trajectory on-line to meet the requirements of overload constraints and placement accuracy. Numerical simulations show that the proposed Guidance algorithm can not only meet the requirements of achieving high precision landing, but also meet the requirements of aerodynamic overload.Under certain initial conditions of reentry, the lunar return to spacecraft may not need to adopt the logic complex Apollo jump reentry scheme. It can provide a reference for setting forth a monthly return trajectory and reentry strategy for the forthcoming manned lunar exploration event.