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针对空天再入飞行器在再入角和再入点位置给定条件下的过渡段轨道设计问题,提出了一种最优过渡段轨道的设计方法。首先,在制动点给定的条件下,由制动脉冲最大限制求得初始航迹角的区间范围,然后详细推导了由给定再入角解析计算初始航迹角的公式,进而可由初始航迹角计算所需的离轨制动脉冲和转移时间。最后用一维搜索策略对转移时间最短和燃料消耗最小的最优制动点位置进行了迭代求解。仿真表明,该算法简单易行,具有很强的实时性,对于空天再入飞行器再入时最优过渡轨道的设计具有较高的工程应用价值。
Aiming at the orbit design of the transitional section of space reentry vehicle under given conditions of reentry angle and reentry point, a design method of the optimal transition section orbit is proposed. Firstly, under the conditions of the braking point, the range of the initial track angle is obtained by the maximum limitation of the braking pulse. Then, the formula for calculating the initial track angle from the given reentry angle is deduced in detail. Track angle calculation required derailment brake pulse and transfer time. Finally, a one-dimensional search strategy is used to solve the optimal braking point with the shortest transfer time and the lowest fuel consumption. The simulation shows that the proposed algorithm is simple and feasible and has strong real-time performance. It has high engineering value for the design of the optimal transitional trajectory when reentrying the spacecraft into space.