流体力学与飞行力学

基于爆炸激波管的火箭级间段强度考核和分离试验研究

  • 朱广生 ,
  • 刘瑞朝 ,
  • 周松柏 ,
  • 李林 ,
  • 王亚军 ,
  • 杨小龙 ,
  • 李斯戌 ,
  • 张延瑞
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  • 1. 中国运载火箭技术研究院, 北京 100076;
    2. 总参工程兵科研三所, 洛阳 471023;
    3. 北京宇航系统工程研究所, 北京 100076
朱广生 男, 博士, 研究员。主要研究方向: 飞行器设计。 Tel: 010-88531498 E-mail: ZGS_0128@163.com李林 男, 硕士, 副研究员。主要研究方向: 爆炸力学与试验技术。 Tel.: 0379-81876753 E-mail: lynn89002@sina.com

收稿日期: 2014-08-21

  修回日期: 2015-02-05

  网络出版日期: 2015-03-11

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

  • ZHU Guangsheng ,
  • LIU Ruichao ,
  • ZHOU Songbai ,
  • LI Lin ,
  • WANG Yajun ,
  • YANG Xiaolong ,
  • LI Sixu ,
  • ZHANG Yanrui
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  • 1. China Academy of Launch Vehicle Technology, Beijing 100076, China;
    2. The Third Engineer Scientific Research Institute of the Headquarters of the General Staff, Luoyang 471023, China;
    3. Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China

Received date: 2014-08-21

  Revised date: 2015-02-05

  Online published: 2015-03-11

摘要

为解决某型号火箭级间分离的相关技术难题、获得最佳的级间分离设计方案,采用了一种新型的试验方法:利用爆炸激波管进行火箭级间段的强度考核和级间分离试验。对试验系统、试验件、试验过程和试验结果等进行了详细论述。试验揭示了级间段内腔非定常压力的变化规律,考核了正式级间段壳体的承压能力,获得了级间分离压力和分离行程曲线等。对试验结果进行了理论分析,并与传统的地面火箭发动机"三合一"试验结果进行了对比。研究表明:利用爆炸激波管进行火箭级间段的强度考核和级间分离试验在理论上是合理的,试验结果与 "三合一"试验吻合较好,为类似试验提供了一种周期短、成本低、可重复性好的新试验手段。

本文引用格式

朱广生 , 刘瑞朝 , 周松柏 , 李林 , 王亚军 , 杨小龙 , 李斯戌 , 张延瑞 . 基于爆炸激波管的火箭级间段强度考核和分离试验研究[J]. 航空学报, 2015 , 36(7) : 2207 -2213 . DOI: 10.7527/S1000-6893.2015.0041

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.

参考文献

[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.
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