亚轨道飞行器再入轨道设计方法研究  

Research on Entry Trajectory Design of Sub-orbital Vehicle

作　　者：回睿姣[1] 李新国[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《科学技术与工程》2012年第8期1836-1840,共5页Science Technology and Engineering

摘　　要：由于亚轨道飞行器再入过程持续时间短等特点,使得用于航天飞机的标准轨道法不适用于亚轨道飞行器。因此研究了基于插值的返回轨道生成算法。在传统的三段关于能量线性的阻力剖面的基础上提出改进算法。该算法先根据返回轨道约束、平衡滑翔约束确定阻力剖面上界和下界,后引入三次曲线使其平滑。最后,一维搜索出合适的纵程参数,通过插值得到最终的标准轨道。While the space shuttle trajectory planner works well over a large part of the entry corridor for orbital entry, it is not suitable for suborbital, because of the short duration of suborbital. An interpolation-based feasible drag design method was displayed. Constraint boundaries were derived through denoting constraints to drag vs. energy space. The lower and upper drag profiles were obtained by using cubic segment. Finally, the desired nominal drag is taken as a weighted combination of a lower and an upper drag profile.

关 键 词：亚轨道飞行器 再入 轨道设计 

分 类 号：V412.44[航空宇航科学与技术—航空宇航推进理论与工程]