Wind tunnel drop model test of nose cap separation of supersonic vehicle
-
摘要: 采用风洞投放模型试验方法对稠密大气层内超声速飞行器两瓣罩旋转分离的运动特性进行研究，试验复现了飞行器两瓣罩旋转分离的整个动态运动过程，并得到飞行器头罩分离后两瓣罩运动轨迹和姿态角的变化规律，试验马赫数Ma=1.5。研究表明：飞行器两瓣罩在预置弹簧力作用下张开一定角度，气流进入两瓣罩腔内后压力迅速升高，高动压气流会对两瓣罩在分离过程中的受力情况产生重要影响，当两瓣罩根部与弹体间的铰链在临界解锁角η0分离进入"自由飞行"阶段后，两瓣罩的运动轨迹和姿态角主要由气动力控制；弹体飞行迎角α=0°时，上下两瓣罩的运动轨迹和姿态角基本对称，弹体飞行迎角α=-5°时，上下瓣罩的运动轨迹和姿态角明显不对称性，弹体迎角α对两瓣罩分离特性影响比较显著。Abstract: This paper studies the motion characteristic of the nose cap revolving separation of the supersonic vehicle in the stiff atmosphere by the wind tunnel drop model test and acquiares the law of the centroid distance and pitch angle variance for the two part nose cap when the nose cap separate. The experiment Mach number is Ma=1.5. The study shows that when the nose cap splays out by the intrinsic constringent spring, the high dynamic pressure afflux into the antrum of the two nose cap and makes the nose cap go round and round by caudal gemel. Then the mantle break away from the forebody when the rotate angle arrive at the preconcerted angle, the aerodynamic force is several orders of magnitude greater than the inertial force, the nose cap trajectory is absolutely controlled by the aerodynamic force and the mantle statement changes violently. The two nose cap have a symmetrical motion distance and pitch angle in the angle of attack α=0°, however, the separate characteristic is unsymmetrical in the angle of attack α=-5°. The angle of attack for the supersonic vehicle has a prominent effect on the motion characteristic for the two nose cap. The study can provide an according and reference for the nose cap separation precept and flighting control system.
-
图 5 迎角α=0°，β=0°头罩分离序列图像
Figure 5. The sequence photo of nose-cap separation in α=0°, β=0°
图 6 迎角α=0°时上下瓣罩运动轨迹与俯仰角时间历程
Figure 6. History of distance and pitch angle for two nose cap centroid in α=0°
图 7 迎角α=-5°，β=0°头罩分离序列图像
Figure 7. The sequence photo of nose-cap separation in α=-5°, β=0°
-
[1] 朱学昌, 李浩远, 喻天翔, 等.低空高速飞行器整流罩分离技术研究现状和展望[J].固体火箭技术, 2014, 37(1):12-17. http://www.wenkuxiazai.com/doc/70855b5aa6c30c2259019ef1.htmlZhu X C, Li H Y, Yu T X, et al. Research status and prospects for low-altitude and high speed fairing separation technique[J]. Journal of Solid Rocket Technology, 2014, 37(1):12-17. http://www.wenkuxiazai.com/doc/70855b5aa6c30c2259019ef1.html [2] 范庆志, 孙秦.飞行器头罩分离技术及设计方案分析研究[J].机械设计与制造, 2008, (9):8-10. http://d.wanfangdata.com.cn/Periodical/jxsjyzz200809004Fan Q Z, Sun Q. The research of aircraft shroud separation technology and design project analysis[J]. Machinery Design Manufacture, 2008, (9):8-10. http://d.wanfangdata.com.cn/Periodical/jxsjyzz200809004 [3] 刘君, 王巍, 郭正, 等.稠密大气层内火箭头罩动态分离过程数值模拟[J].弹道学报, 2006, 18(3):34-38. http://www.cqvip.com/QK/92261X/200603/22996105.htmlLiu J, Wang W, Guo Z, et al. Numerical simulation of the detaching process for rocket mantles in low altitude[J]. Journal of Ballistics, 2006, 18(3):34-38. http://www.cqvip.com/QK/92261X/200603/22996105.html [4] 王巍, 刘君, 白晓征.非结构动网格技术及其在超声速飞行器头罩分离模拟的应用[J].空气动力学学报, 2008, 26(1):131-135. http://www.wenkuxiazai.com/doc/c0ebe14d3b3567ec102d8ab7.htmlWang W, Liu J, Bai X Z. DUM research and apply to solve the fairing separating form hypersonic vehicle[J]. Acta Aerodynamic Sinica, 2008, 26(1):131-135. http://www.wenkuxiazai.com/doc/c0ebe14d3b3567ec102d8ab7.html [5] 李盾. 三维非结构直角网格NS方程计算及抛罩分离过程的数值模拟研究[D]. 北京: 中国航天空气动力技术研究院, 2006. [6] 赵晓慧. 巡航导弹锥形头罩分离仿真分析[D]. 长沙: 国防科学技术大学, 2009. http://cdmd.cnki.com.cn/Article/CDMD-90002-2010165460.htmZhao X H. Design and simulation for the separation of a taper nose cap from a cruise missile[D]. Changsha:National University of Defense Technology, 2009. http://cdmd.cnki.com.cn/Article/CDMD-90002-2010165460.htm [7] 曾江. 导弹抛整流罩过程建模与仿真[D]. 长沙: 国防科学技术大学, 2005. http://cdmd.cnki.com.cn/Article/CDMD-90002-2005144130.htmZeng J. The modeling and simulation of the process of casting radoms of rocket[D]. Changsha:National University of Defense Technology, 2005. http://cdmd.cnki.com.cn/Article/CDMD-90002-2005144130.htm [8] 徐敏, 刘振.基于多块嵌套结构动网格的拦截弹防热保护罩的二维分离模拟[J].计算力学学报, 2007, 24(3):375-378. http://www.cnki.com.cn/Article/CJFDTotal-LTJX201503008.htmXu M, Liu Z. Two-dimensional simulations about the separation of the interceptor missile shroud covers based on moving multi-block chimera structure grids[J]. Chinese Journal of Computational Mechanics, 2007, 24(3):375-378. http://www.cnki.com.cn/Article/CJFDTotal-LTJX201503008.htm [9] Chamberlain R, Baltar J. Time accurate calculation of hypersonic shroud separation[R]. AIAA-93-0317, 1993. doi: 10.2514/6.1993-317 [10] Chamberlain R. Time accurate calculation of the HEDI shroud separation event[R]. AIAA-92-2775, 1992. doi: 10.2514/6.1992-2775 [11] Schwaniger A J, Murphree H I. Description of a mathematical model and computer simulation of separation of the nose cap from the solid rocket booster[R]. NASA-TM-82511, 1982. https://www.researchgate.net/publication/23883281_Description_of_a_mathematical_model_and_computer_simulation_of_separation_of_the_nose_cap_from_the_solid_rocket_booster [12] Wong K J, Van Dam C P. Numerical study on the effect of tip-cap shape on wing aerodynamic characteristics[R]. AIAA-95-0042, 1995. doi: 10.2514/6.1995-42 [13] Lawrence R, Leonard Z, Allwine J. Hypersonic shroud separation testing and modelling capabilities at the naval surface warfare center hypervelocity wind tunnel#9[R]. AIAA-94-2495, 1994. http://www.researchgate.net/publication/269060450_Hypersonic_shroud_separation_testing_and_modelling_capabilities_at_the_Naval_Surface_Warfare_Center_hypervelocity_wind_tunnel_9 [14] Resch L, Hedlund E, Decesaris C. Hypersonic shroud separation testing at the naval surface warfare center hypervelocity wind tunnel#9[R]. AIAA-92-2752, 1992. doi: 10.2514/6.1992-2757 [15] Resch L, Decesaris C, Hedlund E. The naval surface warfare center hypervelocity wind tunnel 9 hypersonic shroud separation testing capability[R]. AIAA-92-0676, 1992. doi: 10.2514/6.1992-676 [16] Lumb S B, Robert W C. Transient aerodynamics of a high dynamic pressure shroud separation for a ground-based interceptor missile[R]. AIAA-92-2820, 1992. doi: 10.2514/6.1992-2820 [17] Michael S H, John H, Matthew M, et al. Development and application of a new ground test capability to conduct full-scale shroud and stage separation studies at duplicated flight conditions[R]. AIAA-2005-696, 2005. doi: 10.2514/6.2005-696 [18] Michael S H, Timothy P W, Gregory J S, et al. Experimental and numerical studies on hypersonic vehicle performance in the LENS shock and expansion tunnels[R]. AIAA-2006-0125, 2006. doi: 10.2514/6.2006-125 [19] 鲍国华.风洞特种实验[M].西安:西北工业大学出版社, 1990:123-126. [20] 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):744-750. http://kns.cnki.net/KCMS/detail/detail.aspx?filename=kqdx201606009&dbname=CJFD&dbcode=CJFQJiang 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 Aerodynamic Sinica, 2016, 34(6):744-750. http://kns.cnki.net/KCMS/detail/detail.aspx?filename=kqdx201606009&dbname=CJFD&dbcode=CJFQ -
下载:
点击查看大图
图(8)
计量
- 文章访问数: 238
- HTML全文浏览量: 135
- PDF下载量: 16
- 被引次数: 0
