低升阻比飞行器月球返回再入轨迹特性分析  

Trajectory characteristics analysis of low lift-drag-ratio vehicle for lunar return entry

作　　者：崔乃刚[1] 赵彪[1] 郭继峰[1] 黄荣[1] 王平[2] 

机构地区：[1]哈尔滨工业大学航天工程系,哈尔滨150001 [2]中国空间技术研究院载人航天总体部,北京100094

出　　处：《哈尔滨工业大学学报》2013年第7期24-28,共5页Journal of Harbin Institute of Technology

基　　金：哈尔滨工业大学航空宇航博士点人才培养与创新研究专项基金资助项目(2010B918022)

摘　　要：月球返回再入轨迹特性与低地球轨道再入轨迹特性具有鲜明的不同,为研究此问题,推导建立了再入问题的数学模型并进行了飞行仿真试验,然后对比分析了低升阻比飞行器月球返回再入的轨迹特性.仿真实验表明,再入角对纵程、热流和过载影响显著,较小的再入角能够改善热流和过载环境;倾侧角翻转对纵程、热流和过载均无明显影响,但对横程影响显著,为纵侧向解耦制导提供了依据;最大峰值热流总是出现在一次峰值过载之前,且随着再入速度减小呈明显减小趋势.据此,再入飞行器在初始下降段实现充分有效的减速后迅速跃出大气,可以改善热流环境.The trajectory characteristics of lunar return reentry are determined by cosmic velocity dynamics. The model of reentry problem is established. Based on the trajectory characteristics analysis of lunar return reentry, we obtained the following conclusions. First, entry angle has a significant effect on downrange, heating rate and g-load. A small entry angle can significantly improve heating and g-load environment. Second, bank reversal has no significant effect on downrange, heating rate and g-load, but has a significant effect on cross-range, which provides a basis for the vertical and lateral decoupling guidance. Third, the maximum heating rate always appears before the first peak g-load, and decreases with the decreasing of entry velocity. Thus, it requires the vehicle to achieve decelerating adequately and effectively in the initial descent phase and then skip out of the atmosphere to improve the heating environment.

关 键 词：低升阻比 月球返回 再入飞行器 轨迹特性 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]