Stage separation trajectory simulation test technique in high speed wind tunnel

QIAN Fengxue; GUO Peng; GAO Peng; LIU Qi; WANG Yuanjing; YI Guoqing

doi:10.11729/syltlx20200125

Volume 35 Issue 5

Nov. 2021

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Article Navigation > Journal of Experiments in Fluid Mechanics > 2021 > 35(5): 90-98

QIAN F X，GUO P，GAO P，et al. Stage separation trajectory simulation test technique in high speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2021，35（5）：90-98. doi: 10.11729/syltlx20200125

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Stage separation trajectory simulation test technique in high speed wind tunnel

doi: 10.11729/syltlx20200125

High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan　621000, China

Received Date: 2020-10-17
Rev Recd Date: 2020-11-14

Available Online: 2021-09-14

Publish Date: 2021-11-05

Abstract

Abstract

Stage separation trajectory capturing test technique in the FL-23 wind tunnel was developed for investigating the stage separation dynamics of future multi-stage launch vehicle systems. By making use of the tunnel's upper and lower attack angle support mechanism and modification of servo-motors, transmission mechanism and control modules, a upper rig with two degrees of freedom of alpha, x, a lower rig with three degrees of freedom of alpha, x and y, and a coupling motion control system were set up. For a two stage vehicle, the two stage models and their force balances could be mounted on the upper and lower rigs respectively, and the stage separation trajectory could be simulated in the wind tunnel under control of the stage separation test computer, with coordinated motion of the angle of attack of the fore stage model, the angle of attack of the aft stage model, and the relative position in x and y directions of the two stage models. Conclusions could be obtained from verification experiments and client experiments, namely, the upper driving mechanism of the stage separation test system could pitch from –15° to 15°, and move from 0 to 200 mm in the x direction. The lower driving mechanism could pitch from –11° to 49°, and move from 0 to 680 mm in the x direction and from 0 to 507 mm in y direction. And the system could be used to conduct the tests for force measurement, model injection experiment, grid force measurement and capture trajectory simulation.
- supersonic,
- stage separation,
- grid force measurement,
- trajectory simulation,
- aerodynamic interference,
- wind tunnel test

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References(27)

References

[1]	WASKO R A. Experimental investigation of stage separation aerody-namics[R]. NASA-TN-D-868, 1961.
[2]	BERNOT P T. Abort separation study of a shuttle orbiter and external tank at hypersonic speeds[R]. NASA-TM-X- 3212, 1975.
[3]	PAMADI B N,NEIRYNCK T A,HOTCHKO N J,et al. Simulation and analyses of stage separation of two-stage reusable launch vehicles[J]. Journal of Spacecraft and Rockets,2007,44(1):66-80. doi: 10.2514/1.17896
[4]	BONNEFOND T, KHARITONOV A M, BRODETSKY M D, et al. Separation of winged vehicles in supersonic[R]. AIAA 95-6092, 1995. doi: 10.2514/6.1995-6092
[5]	REUBUSH D. Hyper-X stage separation — background and status[R]. AIAA 99-4814, 1999. doi: 10.2514/6.1999-4818
[6]	BUNING P, WONG T C, DILLEY A, et al. Prediction of Hyper-X stage separation aerodynamics using CFD[R]. AIAA 2000-4009, 2000. doi: 10.2514/6.2000-4009
[7]	LIEVER P A, HABCHI S D, ENGELUND W C, et al. Stage sepa-ration analysis of the X-43A research vehicle[R]. AIAA 2004-4725, 2004. doi: 10.2514/6.2004-4725
[8]	REUBUSH D, MARTIN J, ROBINSON J, et al. Hyper-X stage separation — simulation development and results[R]. AIAA 2001-1802, 2001. doi: 10.2514/6.2001-1802
[9]	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
[10]	TARTABINI P, BOSE D, McMINN J, et al. Hyper-X stage separation trajectory validation studies[R]. AIAA 2003-5819, 2003. doi: 10.2514/6.2003-5819
[11]	BAHM C, BAUMANN E, MARTIN J, et al. The X-43A hyper-X Mach 7 flight 2 guidance, navigation, and control overview and flight test results[R]. AIAA 2005-3275, 2005. doi: 10.2514/6.2005-3275
[12]	BUNING P, GOMEZ R, SCALLION W. CFD approaches for simula-tion of wing-body stage separation[R]. AIAA 2004-4838, 2004. doi: 10.2514/6.2004-4838
[13]	ZHANG S J, ZHAO X. Computational studies of stage separation with an unstructured chimera grid method[R]. AIAA 2007-5409, 2007. doi: 10.2514/6.2007-5409
[14]	MURPHY K J, ERICKSON G, GOODLIFF S. Experimental stage separation tool development in NASA Langley's Unitary Plan Wind Tunnel[R]. AIAA 2004-4727, 2004. doi: 10.2514/6.2004-4727
[15]	MURPHY K J, BUNING P G, PAMADI B N, et al. Overview of transonic to hypersonic stage separation tool development for Multi-Stage-To-Orbit concepts[R]. AIAA 2004-2595, 2004. doi: 10.2514/6.2004-2595
[16]	PINIER J T. Ares I and Ares I-X stage separation aerodynamic testing[J]. Journal of Spacecraft and Rockets,2012,49(5):842-852. doi: 10.2514/1.A32220
[17]	PIZZICAROLI A, PAGLIA F, LAMBIASE E, et al. Vega launcher aerodynamics at separation of first stage[R]. AIAA 2007-5859, 2007. doi: 10.2514/6.2007-5859
[18]	秦永明,田晓虎,董金刚,等. 串联布局飞行器级间冷分离气动特性研究[J]. 实验流体力学,2014,28(1):38-43. doi: 10.11729/syltlx20130016 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. doi: 10.11729/syltlx20130016
[19]	李其畅, 凌忠伟, 蔡巧言, 等. 超声速级间分离与网格测力试验的研究[C]//第二届近代试验空气动力学会议论文集. 2009: 202-206. LI Q C, LIN Z W, CAI Q Y. Grid force experimental investigation for supersonic stage separation[C]//The Second Conference of Chinese Neoteric Experiment Aerodynamics. 2009: 202-206.
[20]	何彬华,凌忠伟,胡向鹏,等. FL-23风洞级间分离与网格测力试验系统[J]. 实验流体力学,2013,27(4):109-112. doi: 10.3969/j.issn.1672-9897.2013.04.020 HE B H,LING Z W,HU X P,et al. The stage separation and proximity matrix test in FL-23 wind tunnel[J]. Journal of Experi-ments in Fluid Mechanics,2013,27(4):109-112. doi: 10.3969/j.issn.1672-9897.2013.04.020
[21]	赵忠良,龙尧松,余立,等. 高超声速风洞子母弹分离干扰测力试验技术[J]. 流体力学实验与测量,2004,18(3):32-35. doi: 10.3969/j.issn.1672-9897.2004.03.007 ZHAO Z L,LONG Y S,YU L,et al. Hypersonic wind tunnel interference force test of sub-munition reentry separation[J]. Experi-ments and Measurements in Fluid Mechanics,2004,18(3):32-35. doi: 10.3969/j.issn.1672-9897.2004.03.007
[22]	吴继飞,王元靖,罗新福,等. 高超声速风洞多体干扰与分离试验技术[J]. 实验流体力学,2010,24(3):99-102. doi: 10.3969/j.issn.1672-9897.2010.03.021 WU J F,WANG Y J,LUO X F,et al. A test technique for multi-boby interference and separation in hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2010,24(3):99-102. doi: 10.3969/j.issn.1672-9897.2010.03.021
[23]	王元靖,吴继飞,陶洋,等. 高超声速多体干扰与分离试验[J]. 航空动力学报,2010,25(4):902-906. doi: 10.13224/j.cnki.jasp.2010.04.023 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. doi: 10.13224/j.cnki.jasp.2010.04.023
[24]	宋威,蒋增辉. 串联飞行器级间分离风洞自由飞试验[J]. 空气动力学学报,2017,35(5):687-692. doi: 10.7638/kqdlxxb-2016.0077 SONG W,JIANG Z H. Wind tunnel free-flight test for stage separation of tandem layout vehicle[J]. Acta Aerodynamica Sinica,2017,35(5):687-692. doi: 10.7638/kqdlxxb-2016.0077
[25]	王元靖,钱丰学,畅利侠,等. 超声速条件下多体干扰与分离试验研究[J]. 实验流体力学,2014,28(3):58-62. doi: 10.11729/syltlx20130003 WANG Y J,QIAN F X,CHANG L X,et al. Investigation on multi-body interference and separation by grid force measurement at supersonic condition[J]. Journal of Experiments in Fluid Mechanics,2014,28(3):58-62. doi: 10.11729/syltlx20130003
[26]	黄叙辉,罗新福,于志松. FL-24风洞新型捕获轨迹系统设计与发展[J]. 空气动力学学报,2008,26(2):145-149. doi: 10.3969/j.issn.0258-1825.2008.02.002 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. doi: 10.3969/j.issn.0258-1825.2008.02.002
[27]	李平,黄叙辉,周润,等. 2 m × 2 m超声速风洞CTS测控系统研制[J]. 实验流体力学,2015,29(4):95-100. doi: 10.11729/syltlx20140082 LI P,HUANG X H,ZHOU R,et al. Development of measurement and control system for CTS in 2 m × 2 m supersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics,2015,29(4):95-100. doi: 10.11729/syltlx20140082