Drop-test of the model in the wind tunnel is an effective way to investigate the supersonic store separation issues. The choice of similarity parameters is the key factor that influences the test accuracy. In the study of supersonic store separation with initial ejection velocity, the light model method is usually employed to achieve kinematics and dynamic similarity parameters of the model, but the gravity of the model cannot be accurately modelled. To investigate the effects of gravity on the store release test results, the CTS (Captive Trajectory System) test technique is employed. The test results for full-size actual flight parameters and reduced-size similarity parameters for light model method are compared. Results show that in the release procedure, the missile positions and attitudes are strongly coupled, and the vertical descending velocity would affect the variation of the missile attitudes. Under the similar parameters for the light model method, the descending velocity is relatively slow. The virtual gravity correction method is able to approximately modify the descending displacement, whereas it is not suitable for missile attitude revision. Moreover, the attitudes would affect the descending displacement. In the regime of store release safety, the test results under similar parameters which achieved by the light model method tends to be more riskier than employing the actual flight parameters.
[1] 吴继飞, 罗新福, 徐来武, 等. 内埋武器分离特性及其改进方法研究[J]. 空气动力学学报, 2014, 32(6):814-819. WU J F, LUO X F, XU L W, et al. Investigation on internal weapon separation characteristics and flow control methods[J]. Acta Aerodynamica Sinica, 2014, 32(6):814-819(in Chinese).
[2] 张俊祥, 冯金富, 于心一, 等. 一种改善内埋式弹舱气流特性的方法[J]. 弹箭与制导学报, 2011, 31(6):165-168. ZHANG J X, FENG J F, YU X Y, et al. A new method for improving cavity flow[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2011, 31(6):165-168(in Chinese).
[3] 史爱明, 叶正寅, 杨永年. 内埋式弹舱舱门气动载荷计算分析研究[J]. 航空计算技术, 2007, 37(3):5-6. SHI A M, YE Z Y, YANG Y N. Calculation and analysis for aerodynamic loads acting on interior weapon cabin's door[J]. Aeronautical Computing Technique, 2007, 37(3):5-6(in Chinese).
[4] SRINIVASAN A. Analysis of unsteady bay shear layer effects on store separation characteristics:AIAA-2009-0546[R]. Reston:AIAA,2009.
[5] HAIGERMOSER C, VESELY L, NOVARA M, et al. Time-resolved PIV applied to cavity unsteady flows:AIAA-2007-3432[R]. Reston:AIAA,2007.
[6] STEVEN J B, JUSTIN L W, BRIAN O M P. Particle image velocimetry of a three-dimensional supersonic cavity flow:AIAA-2012-0030[R]. Reston:AIAA,2012.
[7] 杨俊,李骞, 谢云恺, 等. 超声速内埋武器分离数值研究[J]. 弹箭与制导学报, 2018, 35(4):171-174. YANG J, LI Q, XIE Y K, et al. Numerical studies on store separation from a weapon bay at supersonic speed[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2018, 35(4):171-174(in Chinese).
[8] STEPHEN R, PERILLO. Challenges and emerging trends in store separation engineering air force seek eagle office perspective:AIAA-2009-0101[R]. Reston:AIAA,2009.
[9] ROBERT L, STALLINGS J R. Store separation from cavities at supersonic flight speeds[J]. Spacecraft, 1983, 20(2):129-132.
[10] JOHNSON R A. Store separation trajectory deviations due to unsteady weapons bay aerodynamics:AIAA-2008-0188[R]. Reston:AIAA,2008.
[11] SHIPMAN J, ARUNAJATESAN S, CAVALLO P A, et al. Flow control for enhanced store separation:AIAA-2007-1239[R]. Reston:AIAA,2007.
[12] 唐上钦, 黄长强, 翁兴伟. 考虑气动干扰的导弹内埋式发射弹道研究[J]. 弹箭与制导学报, 2013, 33(3):138-142. TANG S Q, HUANG C Q, WENG X W. The study on trajectory of missile separating from cavity with aerodynamic interference considered journal of projectiles[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2013, 33(3):138-142(in Chinese).
[13] 薛飞, 金鑫, 王誉超, 等. 内埋武器高速投放风洞试验技术[J]. 航空学报, 2017, 38(1):120114. XUE F, JIN X, WANG Y C, et al. Wind tunnel test technique on high speed weapon delivery from internal weapons bay[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(1):120114(in Chinese).
[14] 李周复. 风洞特种试验技术[M]. 北京:航空工业出版社, 2010:88-161. LI Z F. Wind tunnel special tests technique[M]. Beijing:Aviation Industry Press, 2010:88-161(in Chinese).
[15] REED J F. A comparison between transonic wind-tunnel and full-scale store separation characteristics[J]. Engineering Notes, 1969, 6(3):281-283.
[16] VEAZEY D. Current AEDC weapons separation testing and analysis to support flight testing:AIAA-2004-6847[R]. Reston:AIAA,2004.
[17] 蒋增辉, 宋威, 鲁伟, 等. 高速风洞投放模型试验技术的关键问题及应用领域[J]. 空气动力学学报, 2016, 34(6):744-749, 802. JIANG Z H, SONG W, LU W, et al. Critical problems and applied fields of drop-model testing technique in high speed wind tunnel[J]. Acta Aerodynamica Sinica,2016,34(6):744-749, 802(in Chinese).
[18] 蒋增辉, 宋威, 贾区耀, 等. 多体分离风洞自由飞试验[J]. 空气动力学学报, 2016, 34(5):581-586. JIANG Z H, SONG W, JIA Q Y, et al. Wind tunnel free-flight test for multi-bodies separation[J]. Acta Aerodynamica Sinica, 2016, 34(5):581-586(in Chinese).
[19] 张召明. 飞机外挂物投放低速风洞试验技术研究[J]. 南京航空航天大学学报, 2003, 35(3):318-321. ZHANG Z M. Experimental research of jettison of aircraft external store in low speed wind tunnel[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2003, 35(3):318-321(in Chinese).
[20] 蔡国华. 载机投放外挂物低速风洞模拟技术[J]. 空气动力学学报, 1999, 17(4):477-483. CAI G H. Research of experimental techniques about dropping test of external stores in the low speed wind tunnel[J]. Acta Aerodynamica Sinica, 1999, 17(4):477-483(in Chinese).
[21] 恽起麟. 风洞试验[M]. 北京:国防工业出版社, 2000:555-568. YUN Q L. Wind tunnel testing[M]. Beijing:National Defense Industry Press, 2000:555-568(in Chinese).
[22] 宋威, 鲁伟, 蒋增辉, 等. 内埋武器高速风洞弹射投放模型试验关键技术研究[J]. 力学学报, 2018, 50(6):1346-1355. SONG W, LU W, JIANG Z H, et al. The crucial technique investigation of wind-tunnel drop-model testing for the supersonic internal weapons[J]. Chinese Journal of Theoretical and Applied Mechanic, 2018, 50(6):1346-1355(in Chinese).
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