摘要
针对地面助推水平发射的两级入轨空天飞行器,以一级可重复使用运载器气动特性和爬升弹道特性耦合研究为目标,基于二维三自由度弹道方程,通过计算较系统地分析了运载器升阻比对其分离点速度、高度、弹道倾角、动压、最大过载等一系列参数的影响,并与垂直爬升弹道进行了比较.计算结果表明升力爬升弹道较垂直爬升弹道可获得更高的分离点速度,且在小推重比条件下差别尤为明显.同时,通过提高升阻比,可有效提升分离点高度、减小分离点动压以及全弹道最大过载等,并可大幅拓宽分离点弹道倾角的调节范围.最后对地面助推水平发射方式及对应最佳弹道方案进行了讨论,并提出了气动布局设计的关键需求.
This study aims at climbing characteristics investigation of the first-stage reusable launch vehicle in small Two-Stage-To-Orbit (TSTO) systems adopting ground boosting, horizontal take-off strategy. On the basis of the two-dimensional, three degree of freedom ballistic equations, the impact of the lift-to-drag ratio of the vehicle on some key performance parameters, which include the velocity gain, the height gain, the trajectory inclination angle, the dynamic pressure, and the maximal overload, etc are systematically analyzed under different thrust-weight ratios. In addition, a comparison study by taking a vertical launch trajectory as a reference is carried out. The results clearly show that the velocity gain in the lift-assistance climbing trajectory is larger than that in vertical trajectory. Moreover, a high lift-to-drag ratio is not only propitious to elevate the height of separation, but also conducive to reduce the dynamic pressure as well as the maximal overload, especially in small thrust-weight ratio conditions. The adjustment range of the trajectory inclination angle is significantly extended due to a high lift-to-drag value simultaneously. Finally, both the advantage of the ground boosting launch strategy for vehicles using rocket engines and a rational ballistic are discussed based on the results. Furthermore, some critical requirements of aerodynamic configuration design are proposed.
作者
崔凯
徐应洲
李广利
肖尧
王浩祥
CUI Kai;XU YingZhou;LI GuangLi;XIAO Yao;WANG HaoXiang(LHD of Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China;School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China)
出处
《中国科学：技术科学》
EI
CSCD
北大核心
2019年第8期891-900,共10页
Scientia Sinica(Technologica)
基金
国家自然科学基金(批准号:11572333,11372324)
高温气体动力学国家重点实验室项目资助
关键词
可重复使用运载器
水平发射
两级入轨
弹道分析
升阻比
reusable launch vehicle
horizontal take-off
two-stage-to-orbit
ballistic analysis
lift-to-drag ratio
