基于爆炸激波管的火箭级间段强度考核和分离试验研究

doi:10.7527/S1000-6893.2015.0041

Abstract

Abstract:

In order to solve the related technical problems of one rocket's stage separation and get the best design scheme of the separation, a new experimental method has been adopted, which is that the experiment of strength check and stage separation for the rocket's stage section is conducted by a blast simulator. The experiment system, experiment specimen, experiment procedures and experiment results are discussed in detail. The unsteady characteristic of the pressure in the stage section is presented and the load-bearing capacity of the stage section is qualified, meanwhile the stage separation pressure and the separation displacement of the section are obtained. Theoretical analyses for the experiment results are carried out and the comparisons with results of traditional rocket engine ground experiment (named as "three-in-one experiment") are made. Studies show that using the blast simulator to carry out the experiments of the strength qualification and stage separation for the rocket's stage section is reasonable in theory, and the experiment results have a good agreement with those of "three-in-one experiment" tally; for the similar experiment, a new, short period, low cost and good repeatability experiment method is presented.

Key words: blast simulator, rocket, stage section, strength check, stage separation

CLC Number:

V421
O383

ZHU Guangsheng, LIU Ruichao, ZHOU Songbai, LI Lin, WANG Yajun, YANG Xiaolong, LI Sixu, ZHANG Yanrui. Experimental research of strength check and stage separation for a rocket's stage section based on a blast simulator[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(7): 2207-2213.

References

[1] Chang X L, Hu K, Zhang Y X, et al. The overall structure and analysis of missile[M]. Beijing: National Defense Industry Press, 2010: 94-100 (in Chinese). 常新龙, 胡宽, 张永鑫, 等. 导弹总体结构与分析[M]. 北京: 国防工业出版社, 2010: 94-100.
[2] Li Z N, Zhang Y Z, Fang W G. Aircraft structures[M]. Beijing: Beihang University Press, 2005 (in Chinese). 郦正能, 张玉珠, 方卫国. 飞行器结构学[M]. 北京: 北京航空航天大学出版社, 2005.
[3] Yang T, Wang Z W, Zhang W H, et al. Mathematical analysis of stage-separation regulations of missile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2007, 27(2): 80-82 (in Chinese). 杨涛, 王中伟, 张为华, 等. 导弹级间分离特性的数学分析研究[J]. 弹箭与制导学报, 2007, 27(2): 80-82.
[4] Cicci D A, Qualls C, Landingham G. Two-body missile separation dynamics[J]. Applied Mathematics and Computation, 2008, 198(1): 44-58.
[5] 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). 刘君, 徐春光, 郭正. 多级火箭级间分离流动特性的数值模拟[J]. 推进技术, 2002, 23(4): 265-267.
[6] Huang S Y, Quan X B, Guo F M, et al. Numerical simulation of the initial stage flowfields for the stage separation of the multi-stage rocket[J]. Journal of Propulsion Technology, 2007, 28(2): 113-117 (in Chinese). 黄思源, 权晓波, 郭凤美, 等. 火箭级间热分离初始阶段流场的数值模拟[J]. 推进技术, 2007, 28(2): 113-117.
[7] Quan X B, Wu Y Y, Li Y. Numerical forecast of inter-stage flow field of multistage rocket during stage separation[J]. Missile and Space Vehicle, 2007(3): 6-8 (in Chinese). 权晓波, 武玉玉, 李岩. 多级火箭级间热分离流场的数值预测[J]. 导弹与航天运载技术, 2007(3): 6-8.
[8] 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 (in Chinese). 高立华, 张兵, 权晓波, 等. 火箭级间冷分离过程后期阶段的耦合数值模拟[J]. 推进技术, 2010, 31(2): 129-133.
[9] Gao L H, Zhang B, Quan X B, et al. Coupled numerical simulation of the multi-stage rocket stage separation[J]. Journal of Tsinghua University (Science and Technology), 2011, 51(4): 462-466 (in Chinese). 高立华, 张兵, 权晓波, 等. 火箭级间热分离过程耦合数值模拟[J]. 清华大学学报(自然科学版), 2011, 51(4): 462-466.
[10] Hu X P, Ling Z W, Gao P, et al. FL-23 test system of stage separation in the wind tunnel[C]//Proceedings of the 2nd Joint Symposium on Modern Aerodynamic Experiments. Beijing: Atomic Energy Press, 2009: 285-288 (in Chinese). 胡向鹏, 凌中伟, 高鹏, 等. FL-23风洞级间分离试验系统[C]//第二届近代实验空气动力学会议论文集. 北京: 原子能出版社, 2009: 285-288.
[11] Li Q C, Ling Z W, Cai Q Y, et al. Experimental research on supersonic stage separation and grid force test[C]//Proceedings of the 2nd Joint Symposium on Modern Aerodynamic Experiments. Beijing: Atomic Energy Press, 2009: 202-206 (in Chinese). 李其畅, 凌中伟, 蔡巧言, 等. 超声速级间分离与网格测力试验研究[C]//第二届近代实验空气动力学会议论文集. 北京: 原子能出版社, 2009: 202-206.
[12] Opalka K O. Large blast wave simulators(LBS) with cold gas drivers: computational design studies, AD-A181400[R]. Marland: US Army Ballistic Researoh Laboratory, 1987.
[13] Schraml S, Mermagen C. Experimental evaluation and numerical simulations of multi-driver shock tube flow, AD-A3071602[R]. Marland: US Army Ballistic Researoh Laboratory, 1996.
[14] Tang J Z. Experimental study on dynamic loading of shock wave on structure and equipment[J]. Experiments and Measurements in Fluid Mechanics, 2000, 14(3): 42-46 (in Chinese). 唐建曾. 冲击波对工程结构及装备的动载试验研究[J]. 流体力学实验与测量, 2000, 14(3): 42-46.
[15] Vigil M G. Nineteen-foot diameter explosively driven blast simulator, SAND2001-2164[R]. Albuquerque, NM: SandiaNational Laboratories, 2001.
[16] Ren H Q, Wang S H, Zhou S B, et al. Development and application of a large blast-wave simulator[C]//Proceedings of the 16th Chinese National Symposium on Shock Waves, 2014: 10-22 (in Chinese). 任辉启, 王世合, 周松柏, 等. 大型爆炸波模拟装置研制及其应用[C]//第十六届全国激波与激波管学术会议论文集, 2014: 10-22.
[17] Xin K, Liang S F, Song H M, et al. The key technology for increasing positive duration in a blast wave simulator[J]. Protective Engineering, 2013, 35(5): 9-13 (in Chinese). 辛凯, 梁仕发, 宋红民, 等. 爆炸波模拟装置延长冲击波正压作用时间的关键技术[J]. 防护工程, 2013, 35(5): 9-13.
[18] Huang J R, Wang X, Xu X Y, et al. An installation method of the damping structure for the pressure sensors in ground simulation experiment of spacecraft interstage sections[J]. Protective Engineering, 2013, 35(2): 20-23 (in Chinese). 黄家蓉, 王幸, 徐翔云, 等. 航天器级间段地面模拟试验压力传感器减振安装方法[J]. 防护工程, 2013, 35(2): 20-23.
[19] Huang J R, Wang X. A method for strain measurement with the three-weave system[J]. Protective Engineering, 2013, 35(4): 37-40 (in Chinese). 黄家蓉, 王幸. 一种三线制接线的应变测量方法[J]. 防护工程, 2013, 35(4): 37-40.
[20] Maegley W J, Carroll H R. MX missile thermal mapping and surface flow results[J]. Journal of Spacecraft and Rockets, 1982, 19(3): 199-204.

Experimental research of strength check and stage separation for a rocket's stage section based on a blast simulator

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	WANG Guangxu, TAN Yonghua, ZHUANG Fengchen, CHEN Jianhua, YANG Bao'e, HONG Liu. Suppression effect of injection intensity distribution on longitudinal combustion instability [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 126018-126018.
[2]	LIN Peng, ZHUANG Fujian, QU Linfeng, XU Yangyang, SU Yadong. Technological development in hypersonic nozzle design, manufacture and validation: A review [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 526160-526160.
[3]	LI Hangxing, HU Dike, WU Shaoqing. Optimization design of dynamic vibration absorbers for vibration and noise reduction of composite fairing [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(5): 225249-225249.
[4]	LIANG Tao, CUI Peng, CHENG Peng, LI Qinglian, ZHANG Bin, SONG Jie. Influence of pressure ratio on evolution of cavitation dynamic process in Venturi tube [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 125212-125212.
[5]	SHI Zhongjiao, ZHU Huajie, ZHAO Liangyu, LIU Zhijie. Adaptive decoupling control for a class of spinning rockets considering actuator dynamics [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 325068-325068.
[6]	LI Chaolong, XIA Zhixun, MA Likun, ZHAO Xiang, LUO Zhenbing, DUAN Yifan. Experiment on performance of solid rocket scramjet [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(12): 126075-126075.
[7]	LI Dong, LI Pingqi. Technological breakthroughs of LM-5 and future developments of China's launch vehicle [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(10): 527269-527269.
[8]	CUI Peng, SONG Jie, LI Qinglian, CHEN Lanwei, LIANG Tao, SUN Jun. Dynamic modeling and simulation analysis of LOX/RP1 variable thrust engines using motor pump: Part I-single condition analysis [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 124884-124884.
[9]	ZUO Linxuan, ZHANG Chenlin, WANG Xiao, LU Enwei, ZHU Wei. Requirement of hypersonic aircraft power [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(8): 525798-525798.
[10]	GUO Feng, ZHU Jianfeng, YOU Yancheng, XING Fei. Performance coupling analysis and optimal design of rocket-assisted turbine-based combined cycle engines [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(7): 124755-124755.
[11]	JIA Hongyin, ZHANG Peihong, ZHAO Wei, ZHOU Guiyu, WU Xiaojun. Aerodynamic characteristics of vertical recovery of rocket sub-stage and influence of engine nozzle [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(2): 623995-623995.
[12]	AN Ze, XIONG Fenfen, LIANG Zhuonan. Landing-phase guidance of rocket using bias proportional guidance and convex optimization [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(5): 323606-323606.
[13]	YANG Sizhi, GONG Chunlin, HAO Bo, WU Weinan, GU Liangxian. Ballistic trajectory correction algorithms of high-spin rocket based on impact point prediction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(2): 323421-323421.
[14]	TANG Liang, HU Jinhua, LIU Jiwu, LI Ping, ZHOU Lixin, YANG Baoe. Experimental study on oblique jet wall impingement and geometrical parameter modeling of liquid film [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(12): 124061-124061.
[15]	WU Lilong, CAO Xiaolong, WANG Jing, ZHOU Danjie, LUO Jinling. Pressure fluctuation laws test on interstage section of flight vehicle at transonic speeds [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(8): 122815-122815.