基于栅格舵和滑翔翼的垂直起降火箭再入返回气动特性  

An Analysis of Aerodynamic Characteristics of Reusable Rocket’s First Sub-Stage with Grid Rudder and Glider

作　　者：邓思超 汪小卫[1] 徐振亮[1] 吴胜宝[1] 王书廷[1] DENG Sichao;WANG Xiaowei;XU Zhenliang;WU Shengbao;WANG Shuting(Research and Development Department,China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]中国运载火箭技术研究院研究发展部,北京100096

出　　处：《深空探测学报（中英文）》2022年第5期483-491,共9页Journal Of Deep Space Exploration

基　　金：国家自然科学基金资助项目(52005514,62173301)。

摘　　要：针对基于栅格舵和滑翔翼的两种垂直起降火箭一子级再入返回段的气动特性进行了仿真分析,得到了两种构型一子级的气动特性,分析了其流动结构特征,并研究了气动特性随马赫数(Ma)和攻角的变化规律。结果显示:基于栅格舵构型的一子级轴向力系数和法向力系数随马赫数先增大后减小;基于滑翔翼构型的一子级在小攻角下轴向力系数和法向力系数在马赫数大于2后随马赫数增大而逐渐减小。通过对比可知,基于栅格舵构型一子级的静稳定性优于滑翔翼构型一子级,更适合于需要精确控制落点的重复使用任务;基于滑翔翼构型一子级的升阻比高于栅格舵构型,更适合于需要远距离滑翔的重复使用任务。The aerodynamic characteristics of the reentry stage of the first sub-stage of two vertical take-off and landing rockets based on grid rudder and glider are simulated and analyzed. The aerodynamic characteristics of the first sub-stage of two configurations are obtained. The flow structure characteristics of the sub-stage are analyzed, and the variation of aerodynamic characteristics with Ma number and angle of attack is studied. The results show that the axial and the normal force coefficient of the sub-stage with grid rudder first increase and then decrease with the Ma number. The axial and normal force coefficient of the substage based on glider configuration decrease gradually with the increase of Ma number when Ma number is above 2 at small angle of attack. By comparison, the static stability of the sub-stage with grid rudder configuration is better than the sub-stage with glide configuration,,which means that the sub-stage with grid rudder was more suitable for a mission requiring accurate control of the landing point. Meanwhile, the lift-drag ratio of the sub-stage with glider configuration is higher than that of the grid rudder configuration, indicating that the sub-stage with glider was more applicable for long distance gliding.

关 键 词：栅格舵 滑翔翼 一子级 可重复使用火箭 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]