Optimization of Hypersonic Rocket Sled Aerodynamic Characteristics and Wind Tunnel Tests

doi:10.7652/xjtuxb202405015

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Optimization of Hypersonic Rocket Sled Aerodynamic Characteristics and Wind Tunnel Tests

更新时间：2025-07-28

- Optimization of Hypersonic Rocket Sled Aerodynamic Characteristics and Wind Tunnel Tests
- Vol. 58, Issue 5, Pages: 156-166(2024)
- 作者机构：
  
  1. 西安交通大学机械工程学院,西安,710049
  2. 中国兵器工业试验测试研究院,西安,710100
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202405015
  CLC： V411
- Online First：10 May 2024，
  
  Published：2024
- 稿件说明：
移动端阅览
Optimization of Hypersonic Rocket Sled Aerodynamic Characteristics and Wind Tunnel Tests[J]. 2024, 58(5): 156-166.
DOI：

Optimization of Hypersonic Rocket Sled Aerodynamic Characteristics and Wind Tunnel Tests[J]. 2024, 58(5): 156-166. DOI： 10.7652/xjtuxb202405015.

摘要

为研究如何在不额外增加稳定装置的基础上提高超声速条件下火箭橇的在轨运行稳定性

基于数值分析方法开展了高超声速火箭橇气动特性优化设计

并通过风洞试验对优化后的橇体进行了不同工况下的气动特性研究。建立了基于SST湍流模型、N-S控制方程的火箭橇气动特性数值分析方法

通过经典双椭球模型对计算方法的准确性进行验证。基于气动特性数值分析方法开展橇体气动外形设计

对整流板俯仰角、侧偏角以及前、后滑靴的位置进行优化。通过风洞试验对优化后的橇体进行不同工况下的气动特性研究

分析马赫数、雷诺数以及轨道和地面效应的影响。研究结果表明:火箭橇高超声速气动特性数值分析方法的精度约为86.94%

可以用来模拟火箭橇在高超声速流场中的气动特性; 在Ma=5时

优化后的模型相较于优化前的模型

气动阻力减小了约23.57%

气动升力减小了约38.49%; 随着马赫数的增加

橇体阻力系数呈下降趋势

当Ma从4增加到6

橇体的阻力系数下降约19.98%; 橇体升力系数与俯仰力矩系数均随着雷诺数的增大而增加

Ma=5

当雷诺数从1.80×10

变化到3.60×10

时

橇体的阻力系数与俯仰力矩系数分别增加约8.95%和13.09%; 轨道和地面会导致橇体阻力系数、升力系数和俯仰力矩系数同时增加

其中俯仰力矩系数的变化最为显著

3组对比试验的俯仰力矩系数平均增量约为992%。该研究可为高超声速火箭橇设计提供数据支撑

具有一定的工程应用价值。

Abstract

To study how to improve the operational stability of a rocket sled on orbit under hypersonic conditions without using additional stabilizing devices

an optimization design of the aerodynamic characteristics of a hypersonic rocket sled is carried out based on numerical analysis methods

and the aerodynamic characteristics of the optimized sled are studied under differ

ent operating conditions through wind tunnel tests. Firstly

a numerical analysis method for the aerodynamic characteristics of rocket sleds based on SST turbulence model and N-S control equation is developed

and the accuracy of the calculation method is verified through the classical double ellipsoid model. Then

based on the numerical analysis method of aerodynamic characteristics

the aerodynamic shape design of the sled body is conducted

and elevation angle

lateral deviation angle of the rectifier board

and position of the front and rear slipper are optimized. Finally

the aerodynamic characteristics of the optimized sled body under different operating conditions are studied through wind tunnel tests

and the effects of Mach number

Reynolds number

and track and ground effects are analyzed. The accuracy of the numerical analysis method for hypersonic aerodynamic characteristics of rocket sleds is about 86.94%

which can be used to simulate the aerodynamic characteristics of rocket sleds in hypersonic flow fields. At Ma=5

the optimized model reduces aerodynamic drag by 23.57% and aerodynamic lift by 38.49% compared to the pre-optimized model. As the Mach number increases

the drag coefficient of the sled body shows a decreasing trend

for example

when the Mach number increases from 4 to 6

the drag coefficient of the sled body decreases by 19.98%. The lift coefficient and pitch moment coefficient of the sled body both increase with the increase of Reynolds number. At Ma=5

when the Reynolds number changes from 1.80×10

to 3.60×10

the drag coefficient and pitch moment coefficient of the sled increase by 8.95% and 13.09% respectively. The track and ground will lead to a simultaneous increase in the resistance coefficient

lift coefficient

and pitch moment coefficient of the sled body

with the pitch moment coefficient changing the most significantly. The average increment of pitch moment coefficient in the three comparative experiments is about 992%. The research can provide data

support for the design of hypersonic rocket sleds and has certain engineering application value.

关键词

Keywords

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