### 火箭子级垂直回收布局气动特性及发动机喷管影响

1. 中国空气动力研究与发展中心 计算空气动力研究所, 绵阳 621000
• 收稿日期:2020-03-21 修回日期:2020-07-13 发布日期:2020-08-03
• 通讯作者: 赵炜 E-mail:ethanuaa@163.com
• 基金资助:
国家数值风洞项目；国家科技支撑计划（18-H863-03-ZT-001）

### Aerodynamic characteristics of vertical recovery of rocket sub-stage and influence of engine nozzle

JIA Hongyin, ZHANG Peihong, ZHAO Wei, ZHOU Guiyu, WU Xiaojun

1. Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
• Received:2020-03-21 Revised:2020-07-13 Published:2020-08-03
• Supported by:
National Numerical Wind tunnel Projetct; National Key R&D Technology Project(18-H863-03-ZT-001)

Abstract: The vertical recovery reusable launch vehicle is an important direction in the development of launch vehicles. The vertical reentry process with a large slenderness ratio is a typical irregular flow around the blunt body, with aerodynamic characteristics significantly different from those of traditional low drag streamline body vehicles. In this paper, the basic aerodynamic characteristics of the vertical recovery configuration and the flow around the irregular blunt body based on the grid fins were studied by means of wind tunnel tests and numerical simulation analyses. The influence quantities of the exposed nozzles and grid fins on the vertical recovery aerodynamic characteristics of the rocket sub-stage were obtained, and the vertical recovery layout design suggestions were given. The results indicate that the shoulder region will generate large separation flow at a small angle of attack when the rocket sub-stage reenters into the air. A strong separation vortex structure will be induced on the left and right sides of the nozzles, which will interact with the tail of the rocket and the large separation flow produced by the shoulder. The resistance of the vertical recovery configuration will always be at a high level with the supersonic speed, and the movement of the pressure center will be large with different Mach numbers. The exposed nozzle of the rocket engine will produce a large disturbing static instability moment when flying backward, with its magnitude basically the same as the static stability control moment provided by the gird fins. Attention should be paid to the design of the vertical recovery scheme of the rocket sub-stage.