火箭子级垂直回收布局气动特性及发动机喷管影响

贾洪印; 张培红; 赵炜; 周桂宇; 吴晓军

doi:10.7527/S1000-6893.2020.23995

航空学报 >

2021 , Vol. 42 >Issue 2: 623995 - 623995

DOI: https://doi.org/10.7527/S1000-6893.2020.23995

先进空间运输系统气动设计专栏

火箭子级垂直回收布局气动特性及发动机喷管影响

贾洪印 ,
张培红 ,
赵炜 ,
周桂宇 ,
吴晓军

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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

网络出版日期: 2020-08-03

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）

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

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

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Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received date: 2020-03-21

Revised date: 2020-07-13

Online published: 2020-08-03

Supported by

National Numerical Wind tunnel Projetct; National Key R&D Technology Project(18-H863-03-ZT-001)

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摘要

垂直回收可重复使用运载火箭是运载火箭发展的一个重要方向，大长细比的火箭子级垂直再入过程属于典型的非规则钝头体绕流，与传统低阻力流线体飞行器气动特性差异较大。采用风洞试验辅以数值仿真分析的方法，对基于栅格舵的火箭子级垂直回收构型基本气动特性和非规则钝头体绕流情况进行了研究，获得了发动机外露喷管和栅格舵对火箭子级垂直回收气动特性的影响规律，给出了火箭子级垂直回收布局设计建议。结果表明：火箭子级倒飞状态下肩部区域会在小迎角下产生大分离流动，外露发动机喷管左右两侧诱导出较强的分离涡结构，与火箭尾翼、肩部大分离流动相互作用；垂直回收构型在超声速下阻力会一直处于较高的水平，不同马赫数下压心移动量较大，倒飞时发动机外露喷管会产生较大的干扰静不稳定力矩，其量值与栅格舵提供的静稳定控制力矩基本相当，在火箭子级垂直回收方案设计时需要引起注意。

关键词： 火箭垂直回收; 非规则钝头体; 栅格舵; 气动布局; 气动特性

本文引用格式

贾洪印 , 张培红 , 赵炜 , 周桂宇 , 吴晓军 . 火箭子级垂直回收布局气动特性及发动机喷管影响[J]. 航空学报, 2021 , 42(2) : 623995 -623995 . DOI: 10.7527/S1000-6893.2020.23995

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.

Key words： rocket vertical recovery; irregular blunt body; grid fins; aerodynamic layout; aerodynamic characteristics

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