空天再入飞行器最优过渡段轨道设计方法研究

Research on Optimal Transition Trajectory Planning for Reentry Vehicle

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。

A method of the optimal transition trajectory planning is proposed for the problem of planning the transition trajectory of the reentry vehicle on condition that the reentry location and reentry angle are fixed.Firstly,on condition of a given braking position,the constraint of the velocity increment is transformed into flyout angle interval.Secondly,the formula to calculate the flyout angle by using known reentry angle is derived,and then the de-orbit thrust and the transfer time can be calculated.Finally,the optimal braking positions of the optimal transfer time and the optimal fuel consuming are calculated iteratively.The simulation result approves that the method proposed is simple and high real-time,which possesses high application value for the choice of the braking position and the de-orbit thrust calculation of reentry vehicle.