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基于改进的Gauss伪谱法,研究了探月返回器跳跃式再入轨迹优化设计问题。首先给出了探月返回器再入轨迹优化问题的三维模型。然后针对探月返回器配平攻角飞行的特点,考虑到实际倾侧角反转机动不可能瞬时完成,对单一控制变量倾侧角的变化范围进行合理限制,并以总吸热量为性能指标,设计了满足过载和驻点热流约束的小升力体大航程跳跃式再入轨迹。最后基于该优化算法,将返回器在各相同初始条件下发生跳跃和不发生跳跃时的最大航程进行比较,并求解得到在不同升阻比和存在不同程度大气密度偏差时不发生跳跃的再入轨迹最大航程和过载峰值,以分析跳跃式轨迹在扩大小升力体再入航程方面的优势。
Based on the improved Gauss pseudospectral method, the optimization design of the jump-over trajectory of lunar reflector is studied. At first, a three-dimensional model of the trajectory reentry trajectory of lunar probe is given. Considering the fact that the actual tilting angle reversal maneuver can not be completed instantaneously, the variation range of the tilting angle of the single control variable is reasonably limited. Based on the characteristics of the total heat absorption, In order to meet the overload and stagnation point heat flow restriction of large lift body jump re-entry trajectory. Finally, based on this optimization algorithm, the maximum voyage of the reflector with or without jump under the same initial condition is compared and the reentry without jump in different lift-drag ratio and different degrees of atmospheric density deviation is obtained The maximum range and overload peaks of the trajectory are analyzed to analyze the advantage of the leaping trajectory in expanding the re-entry range of the small lift body.