Stage separation trajectory simulation test technique in high speed wind tunnel
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摘要: 针对多级航天器级间分离研究的地面试验需求,在高速风洞中发展了能够同时模拟前、后级运动的级间分离试验技术。利用风洞的上、下迎角机构,配置电机、传动系统和控制系统,建立了可变迎角和x向位移的上驱动机构,以及可变迎角、x向位移和y向位移的下驱动机构。分别将多级航天器的前、后级模型及测力天平与风洞上、下驱动机构连接,在级间分离计算机控制下,可开展前级迎角、后级迎角、前后级x向和y向相对位置协同模拟的轨迹模拟试验。调试和应用结果表明:上驱动机构可实现迎角–15°~15°、x向0~200 mm范围内的受控运动;下驱动机构可实现迎角–11°~49°、x向0~680 mm、y向0~507 mm范围内的受控运动;系统可用于常规测力试验、投放试验、网格测力试验和轨迹捕获试验。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.
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表 1 飞行器质量特性
Table 1. Mass properties of aircrafts
质量m/kg 转动惯量Iz /(kg·m2) 前级 500 618 后级 500 103 表 2 分离初始条件
Table 2. Initial conditions of stage separation
初始马赫数 初始高度/
km弹道倾角/
(°)分离迎角/
(°)分离速度/
(m·s–1)3.0 10 –70 0 10 -
[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/syltlx20130016QIN 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.1672-9897.2013.04.020HE 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.1672-9897.2004.03.007ZHAO 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.1672-9897.2010.03.021WU 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.2010.04.023WANG 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-2016.0077SONG 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/syltlx20130003WANG 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.0258-1825.2008.02.002HUANG 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/syltlx20140082LI 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