基于PSP/TSP测量的TSTO标模级间分离气动干扰特性试验分析

解福田; 张庆虎; 林敬周; 彭迪; 陈磊

doi:10.7638/kqdlxxb-2022.0196

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基于PSP/TSP测量的TSTO标模级间分离气动干扰特性试验分析

研究专栏——高超声速多体分离试验技术与计算分析 | 更新时间：2026-05-28

- 基于PSP/TSP测量的TSTO标模级间分离气动干扰特性试验分析
- Experimental analysis of interference characteristics of TSTO stage separation based on PSP/TSP measurement
- 空气动力学学报 2023年41卷第5期页码：98-108
- 作者机构：
  
  1. 中国空气动力研究与发展中心超高速空气动力研究所,绵阳,621000
  2. 上海交通大学机械与动力工程学院,上海,200240
- 作者简介：
  
  解福田（1980-），男，硕士，高级工程师，研究方向：高超声速风洞试验技术. E-mail：wuhuiyuanming@sina.com
  林敬周（1976-），女，硕士，研究员，研究方向：多体空气动力学. E-mail：jingzhou.lin@cardc.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0196
  中图分类号： V211.74;V411.7
- 纸质出版：2023
- 稿件说明：
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解福田, 张庆虎, 林敬周, 等. 基于PSP/TSP测量的TSTO标模级间分离气动干扰特性试验分析[J]. 空气动力学学报, 2023, 41(5): 98−108.

XIE Futian, ZHANG Qinghu, LIN Jingzhou, et al. Experimental analysis of interference characteristics of TSTO stage separation based on PSP/TSP measurement[J]. 2023, 41(5): 98-108.
解福田, 张庆虎, 林敬周, 等. 基于PSP/TSP测量的TSTO标模级间分离气动干扰特性试验分析[J]. 空气动力学学报, 2023, 41(5): 98−108. DOI： 10.7638/kqdlxxb-2022.0196

XIE Futian, ZHANG Qinghu, LIN Jingzhou, et al. Experimental analysis of interference characteristics of TSTO stage separation based on PSP/TSP measurement[J]. 2023, 41(5): 98-108. DOI： 10.7638/kqdlxxb-2022.0196.

摘要

两级入轨空天飞行器（TSTO）并联级间分离存在复杂的气动干扰现象，理解气动干扰特性对分离安全性设计和评估具有重要意义。本文在

0.5 m高超声速风洞中开展了基于压敏漆（PSP）与温敏漆（TSP）试验技术的级间气动干扰特性研究，解决了有遮挡条件下的压敏漆与温敏漆测量难题，获得了马赫数6条件下不同级间距的高分辨率大面积连续压力和温度分布特性。研究表明：轨道级头部激波直接入射至助推级壁面，与边界层相互干扰，诱导流动分离；入射激波与分离激波在级间区域会产生多次反射，形成三维复杂波系结构；随着分离距离增大，级间流场呈现从缝隙流到小通道流再到大通道流的流动特征，级间高压高温干扰区则呈现从前往后移动且峰值减弱的特点，这也是改变两级气动力/力矩特性、影响分离过程中两级位姿变化的主要因素。

Abstract

There are complex aerodynamic interference phenomena in parallel stage separation of TSTO (two-stage-to-orbit) vehicles. Understanding the aerodynamic interference characteristics is of great significance for the separation safety design and evaluation of TSTO. In this study

the aerodynamic interference characteristics of the inter-stage flow has been studied in the

0.5 m hypersonic wind tunnel based on the test techniques of pressure sensitive paint (PSP) and temperature sensitive paint (TSP). By solving the difficulty of PSP and TSP measurement under shielding

we obtained a large area of

continuous pressure and temperature distribution in high resolution at Mach number 6 for different separation distances. The results show that the head shock wave of the orbit stage directly hits on the surface of the booster stage model

then generates flow separation and multiple reflections between the stages

forming three-dimensional complex shock wave structures. With the increase of the separation distance

the flow field between the two stages presents flow features from small channel flow to large channel flow. The movement of the high pressure and high temperature interference zone between the two stages moves from front to back

with its peak value weakened

which is the main reason for the change of the aerodynamic/torque characteristics of the two stages as well as their pose variation during the separation process.

关键词

Keywords

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