高超声速风洞双体同步分离捕获轨迹试验技术

林敬周; 解福田; 钟俊; 邹东阳; 皮阳军

doi:10.7638/kqdlxxb-2022.0088

欢迎来到能源电力期刊网！

English Version 期刊登录

您当前的位置：

首页 >

文章列表页 >

高超声速风洞双体同步分离捕获轨迹试验技术

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

- 高超声速风洞双体同步分离捕获轨迹试验技术
- Dual-body synchronous captive trajectory test technique in hypersonic wind tunnel
- 空气动力学学报 2023年41卷第5期页码：77-86
- 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. 重庆大学机械传动国家重点实验室,重庆,400044
- 作者简介：
  
  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
  邹东阳*（1989-），男，博士，助理研究员，研究方向：多体空气动力学. E-mail： zoudongyang@cardc.cn
- 基金信息：
  
  国家数值风洞工程（ NNW）
- DOI：10.7638/kqdlxxb-2022.0088
  中图分类号： V211.74;V411.7
- 纸质出版：2023
- 稿件说明：
移动端阅览
林敬周, 解福田, 钟俊, 等. 高超声速风洞双体同步分离捕获轨迹试验技术[J]. 空气动力学学报, 2023, 41(5): 77−86.

LIN Jingzhou, XIE Futian, ZHONG Jun, et al. Dual-body synchronous captive trajectory test technique in hypersonic wind tunnel[J]. 2023, 41(5): 77-86.
林敬周, 解福田, 钟俊, 等. 高超声速风洞双体同步分离捕获轨迹试验技术[J]. 空气动力学学报, 2023, 41(5): 77−86. DOI： 10.7638/kqdlxxb-2022.0088

LIN Jingzhou, XIE Futian, ZHONG Jun, et al. Dual-body synchronous captive trajectory test technique in hypersonic wind tunnel[J]. 2023, 41(5): 77-86. DOI： 10.7638/kqdlxxb-2022.0088.

摘要

为了更准确地模拟质量与体积相当的高超声速飞行器多体分离过程，在国内首次研发了高超声速风洞双体同步捕获轨迹试验技术。通过将风洞前室总温总压信号及模型天平测力信号等的数据采集、实时气动及动力学解算、上/下机构联动组合控制、上/下机构运动分配四项关键功能融为一体的设计方式，建立了

1 m高超声速风洞双体同步分离试验平台。结合两级入轨空天飞行器标模的多体分离特性研究，开展了马赫数6条件下典型状态的双体CTS（captive trajectory system）试验验证。验证结果表明建立的高超声速风洞双体同步捕获轨迹试验技术较好地获得了飞行器两级分离轨迹及气动特性，纵向气动力试验精度优于4.8%、力矩优于6.2%，纵向捕获轨迹预测精度优于8.7%，可以满足高超声速飞行器两级分离过程中均有较大位姿变化的多体分离模拟。

Abstract

In order to accurately simulate the multi-body separation process of hypersonic vehicle with equivalent mass and volume

a dual-body synchronous captive trajectory test technique in the hypersonic wind tunnel is developed for the first time. Based on this technique

the dual-body synchronous separation test platform of the hypersonic wind tunnels is established in the four-in-one design mode

which combines four key functionalities together

i.e.

data acquisition of the total pressure and total temperature of the wind tunnel settling chamber

the forces from the balance mounted on the models

etc.

real-time aerodynamic and dynamic calculations

linkage combination control of the upper/lower mechanism

and motion distribution of the upper/lower mechanism. Taking advantages of the standard model of TSTO (Two-Stage-to-Orbit)

the test verification of typical states of the dual-body CTS (Captive Trajectory System) at Mach 6 is carried out in the Φ1m hypersonic wind tunnel. The verification results show that the established dual-body synchronous separation test technique in the hypersonic wind tunnel can well obtain the two-stage separation trajectory and the aerodynamic characteristics of the hypersonic aircraft. The test accuracy is better than 4.8% for the aerodynamic forces in the longitudinal direction

higher than 6.2% for the moments

and more than 8.7% for the longitudinal captive trajectory. The new test technique can meet the requirement of multi-body separation simulations with large position and attitude changes during the two-stage separation process of hypersonic aircraft.

关键词

Keywords

references

中国人民解放军总装备部军事训练教材编辑工作委员会. 高超声速气动力试验[M]. 北京: 国防工业出版社, 2004.

BORDELON W, FROST A, REED D. Stage separation wind tunnel tests of a generic TSTO launch vehicle[C]// 21st AIAA Applied Aerodynamics Conference, Orlando, Florida. Reston, Virginia: AIAA, 2003: 4227. doi: 10.2514/6.2003-4227

LIU J, XU C G, GUO Z. Numerical simulation on the stage-separation flow fields of the multi-stage rocket[J]. Journal of Propulsion Technology, 2002, 23(4): 265-267. (in Chinese)[知网中文][知网英文]

ZHANG W P, FENG Z P. Numerical simulation of flow field and thermal analysis for stage separation of multistage missile[J]. Journal of Propulsion Technology, 2003, 24(3): 240-243. (in Chinese)[知网中文][知网英文]

GAO L H, ZHANG B, QUAN X B, et al. Coupled numerical simulation for the later period of the stage separation of a multi-stage rocket[J]. Journal of Propulsion Technology, 2010, 31(2): 129-133, 152. (in Chinese)[知网中文][知网英文]

JIANG Z H, XUE F, LU W, et al. Critical problems of unsteady wind tunnel test technique on multi-bodies separation[J]. Acta Aerodynamica Sinica, 2019, 37(5): 715-721. (in Chinese)[万方]

SONG W, AI B C. Multibody separation dynamics: Review [J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(9): 025950 (in Chinese).

LI Z F. Special test technology in wind tunnel [M]. Beijing: Aviation Industry Press, 2010 (in Chinese).

中国人民解放军总装备部军事训练教材编辑工作委员会. 高速风洞试验[M]. 北京: 国防工业出版社, 2003: 266-291.

YUN Q L. Experimental aerodynamics [M]. Beijing: National Defense Industry Press, 1991 (in Chinese).

BILLINGSLEY J P, BURT R H, BEST J T. Store separation testing techniques at the Arnold Engineering Development Center. Volume 3. Description and Validation of Captive Trajectory Store Separation Testing in the Von Karman Facility[R]. Defense Technical Information Center, 1979. doi: 10.21236/ada068319

BUCHANAN T D, CROSBY W A. Captive trajectory system test planning information for AEDC supersonic wind tunnel (A) and hypersonic wind tunnels (B) and (C)[R]. Defense Technical Information Center, 1983. doi: 10.21236/ada136439

WOODS W C, HOLLAND S D, DIFULVIO M. Hyper-X stage separation wind-tunnel test program[J]. Journal of Spacecraft and Rockets, 2001, 38(6): 811-819. DOI:10.2514/2.3770[LinkOut]

PINIER J, NISKEY C. Ares I and Ares I-X stage separation aerodynamic testing[C]// 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Orlando, Florida. Reston, Virginia: AIAA, 2011: 169. doi: 10.2514/6.2011-169

LORAN WINGFIELD I. Staging evaluation of a two-stage-to-orbit vehicle at Mach 8[C]// 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference, Kyoto, Japan. Reston, Virginia: AIAA, 2001: 1815. doi: 10.2514/6.2001-1815

GARCON F, TARAVEL P, RAFFIN J C. Recent developments in captive trajectory systems of the ONERA Modane wind tunnels[C]// 39th Aerospace Sciences Meeting and Exhibit, Reno, NV. Reston, Virginia: AIAA, 2001: 579. doi: 10.2514/6.2001-579

J A THAIN, R LAFRANCE. F18 External stores grid measurement testing in the IAR/NRC 1.5m blowdown wind tunnel[C]. Ankara: AGARD FDP Symposium on Aerodynamics of Store Integration and Separation CP-570, 1995.

BREITSAMTER C, LASCHKA B, ZAEHRINGER C, et al. Wind tunnel tests for separation dynamics modeling of a two-stage hypersonic vehicle[C]// 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference, Kyoto, Japan. Reston, Virginia: AIAA, 2001: 1811. doi: 10.2514/6.2001-1811

UEMATSU T, ASO S, TANI Y. Supersonic flight separation simulation for TSTO launch vehicles considering shock wave interaction reduction[C]// 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee. Reston, Virginia: AIAA, 2012: 253. doi: 10.2514/6.2012-253

HUANG X H, LUO X F, YU Z S. Design development of a new captive trajectory simulation system in FL-24 wind tunnel[J]. Acta Aerodynamica Sinica, 2008, 26(2): 145-149. (in Chinese)[知网中文][知网英文]

ZHOU R, HUANG X H, ZHANG Z Y, et al. A captive trajectory system using double closed-loop velocity control[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(6): 1522-1529. (in Chinese)[知网中文][知网英文]Doi:10.7527/S1000-6893.2013.0432

YU Z S, WANG F X, LUO X F. Investigation of two special CTS test techniques[J]. Experiments and Measurements in Fluid Mechanics, 2004, 18(4): 49-53. (in Chinese)[知网中文][知网英文]

ZHAO Z L, LONG Y S, YU L, et al. Hypersonic wind tunnel interference force test of sub-munition reentry separation[J]. Experiments and Measurements in Fluid Mechanics, 2004, 18(3): 32-35. (in Chinese)[知网中文][知网英文]

LEI J M, WU J S, XIAO Y B. Aerodynamic interference wind tunnel experiment investigation for dispenser and submunition[J]. Acta Armamentarii, 2005, 26(4): 535-539. (in Chinese)

QIN Y M, TIAN X H, DONG J G, et al. Investigation on aerodynamic characteristics at stage separation of tandem layout vehicle[J]. Journal of Experiments in Fluid Mechanics, 2014, 28(1): 38-43. (in Chinese)[知网中文][知网英文]Doi:10.11729/syltlx20130016

WANG Y J, WU J F, TAO Y, et al. Hypersonic experimental investigation on interference and stage separation of a multi-body system[J]. Journal of Aerospace Power, 2010, 25(4): 902-906. (in Chinese)[知网中文][知网英文]

WANG Z J, WU Y Z, LIN J Z. Wind tunnel test on effect of the jet flow interaction on stage separation of launch vehicle[J]. Journal of Experiments in Fluid Mechanics, 2009, 23(2): 15-19. (in Chinese)[知网中文][知网英文]

LIN J Z, CAO C, WU Y S, et al. Experimental investigation on interstage thermal environment with multi-jets interaction in wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2012, 26(3): 1-5, 31. (in Chinese)[知网中文][知网英文]

LIN J Z, WANG X, ZHONG J, et al. Investigation and application of high Mach number multi-body separation test technique[J]. Journal of Propulsion Technology, 2020, 41(4): 925-933. (in Chinese)[知网中文][知网英文]

TANG W, LIU S S, YU L, et al. Conceptual design of TBCC based TSTO configurations for stage seperation investigation[J]. Acta Aerodynamica Sinica, 2019, 37(5): 698-704, 721. (in Chinese)[知网中文][知网英文]Doi:10.7638/kqdlxxb-2018.005

LIN J Z. China's first hypersonic wind tunnel dual CTS test capability formed in CARDC[J]. Journal of Experiments in Fluid Mechanics, 2021, 35(1): 126. (in Chinese)[知网中文][知网英文]

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

基于嵌入式神经网络数据预测的多体分离安全评估平台

基于PSP/TSP测量的TSTO标模级间分离气动干扰特性试验分析

一种用于TSTO级间分离CFD计算的网格动态优化技术

华中科技大学Φ 0.5 m马赫6 Ludwieg管风洞设计与流场初步校测

个体间距对多扑翼气动噪声的影响特性