Aerodynamic mechanism of strong ground effect on horizontal boost run cross velocity domain

被引：0
|
作者：
Wang W. [1 ]
Zhao X. [1 ]
Yang L. [1 ]
Li H. [1 ]
Xiang Y. [1 ]
机构：
[1] School of Astronautics, Beijing Institute of Technology, Beijing
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2023年 / 44卷 / 21期
基金：
中国国家自然科学基金;
关键词：
cross velocity domain; horizontal boost sliding; internal vortex system; rocket sled; shock wave interference;
D O I：
10.7527/S1000-6893.2022.28247
中图分类号：
学科分类号：
摘要：
The rocket sled can realize supersonic speed in a short time with horizontal boost sliding，which is not only the major means of current high-speed ground dynamic tests，but also an important supporting carrier for the future reusable Single Stage to Orbit（SSTO）for the horizontal launch. Aiming at the key problems such as raising/lowering the head of the payload during separation from the sled and the sensor layout scheme design for rocket sled testing，we adopt the hypersonic standard model as the payload to study the aerodynamic mechanism of the rocket sled horizontal boost sliding system based on the high-precision turbulent numerical theory and the complex shock wave system interference theory. Analysis of the vortex system evolution，local flow field characteristics，and overall aerodynamic characteristics of the structure at the sliding speed across the speed domain reveals the influence mechanism of different connection schemes on the payload and the variation law of the structure surface pressure distribution. The results show that at a low Mach number，the pressure fluctuation in the low pressure region changes periodically，easy to cause aerodynamic vibration；at different Mach numbers，the location of the low pressure zone changes obviously，the region expands with high velocity，and the wake vortex is relatively stable；changing the connection distance and connection height can significantly change the vortex position in the low-pressure region. © 2023 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.
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