空天飞行器整体式救生座舱的稳定减速与分离特性数值模拟

doi:10.7527/S1000-6893.2020.24059

Abstract

Abstract: The integral escape module concept integrates the seat and the cockpit in order to obtain an independent aerodynamic configuration after ejection. A maximum protection can be offered for the crew from high-speed wind blast. Therefore, the integral escape module will be one of the important approaches for the design of the escape system for the aerospace vehicle. In this study, we first conduct numerical simulation of an integral escape module to evaluate its basic aerodynamic performance. Then a rigid brake parachute scheme is proposed to improve the stability and deceleration efficiency of the integral escape module. Finally, the unsteady computational method with a dynamic chimera grid technique is applied to the simulation of the escape process. The numerical results reveal a lack of static stability of the single integral escape module. However, both static and dynamic stability can be significantly improved by using the brake parachute combination scheme in the wide flight envelop of Ma=0.3~4.0. With the growth of Mach number, the stability increases at subsonic speed, while decreases at supersonic speed. The dynamic stability can be further improved by reducing the flying altitude to increase the dynamic pressure at high Mach numbers (e.g. Ma=4.0). In the wide flight envelope, the ejection escape trajectory of the integral escape module shows that the module combined with the brake parachute can be safely separated from the aerospace vehicle assisted by the ejection force and rocket thrust, with its attitude converging gradually.

Key words: integral escape modules, wide speed range, stability, brake parachute, chimera grid

CLC Number:

V244.21

LIU Yuan, CHEN Chuan, QIAN Zhansen. Numerical simulation of stable deceleration and safe separation of integral escape module for aerospace vehicles[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(12): 124059-124059.

References

[1] 李锐. 航空救生装备的发展[J]. 航空科学技术, 1995, 19(1):20-23. LI Y. Development of aviation life-saving equipment[J]. Aeronautical Science & Technology, 1995, 19(1):20-23(in Chinese).
[2] 韩梦珍. 国外航空救生技术现状及展望[J]. 航空科学技术, 2003(2):22-25. HAN M Z. Present status and prospects for foreign aviation life-support technology[J]. Aeronautical Science & Technology, 2003(2):22-25(in Chinese).
[3] HUFFORD G S, HABCHI S D. Validation of CFD methodology for ejection seat applications:AIAA-94-0751[R]. Reston:AIAA, 1994.
[4] KENZAKOWSKI D C, YORK B, DASH S. Computational simulation of ejection seat aerodynamics with rocket propulsive effects:AIAA-97-2253[R]. Reston:AIAA, 1997.
[5] United States Air Force Research Laboratory. 4th generation escape system technologies demonstration phase Ⅱ Final report:MDC-97-K-0154[R]. Washington, D.C.:ARFL, 1998.
[6] ELSON M, LINGARD J S. Object orientated ejection seat model:AIAA-1997-1548[R]. Reston:AIAA, 1997.
[7] AOKI S, LEE J, MASUYA G, et al. Experimental Investigation of an Ejector-Jet[C]//Aerospace Sciences Meeting & Exhibit. Reston:AIAA, 2003:AIAA-2003-188.
[8] 张大林, 魏涛, 姜南. 弹射座椅系统外高速流场的数值模拟[J]. 南京航空航天大学学报, 2009, 41(2):202-206. ZHANG D L, WEI T, JIANG N. Numerical simulation of high speed flow field around ejection system[J]. Journal of Nanjing University of Aeronautics and Astronautics, 2009, 41(2):202-206(in Chinese).
[9] 王一丁, 童明波, 闫家益, 等. 某型飞机弹射座椅穿盖弹射试验与数值模拟[J]. 南京航空航天大学学报, 2013, 45(3):336-340. WANG Y D, TONG M B, YAN J Y, et al. Test and numerical simulation of through canopy ejection for aircraft[J]. Journal of Nanjing University of Aeronautics and Astronautics, 2013, 45(3):336-340(in Chinese).
[10] 李锋, 姚富宽. 某型飞机弹射救生分离特性仿真[J]. 飞机设计, 2016, 36(1):61-67, 73. LI F, YAO F K. Numerical simulation of ejection occupant/seat separation aerodynamic characteristics of an aircraft[J]. Aircraft Design, 2016, 36(1):61-67, 73(in Chinese).
[11] 陈德华. 高速风洞航空弹射座椅大攻角大侧滑角试验技术研究[J]. 实验流体力学与测量, 1999(13):49-53. CHEN D H. A study of experimental technology for ejection seat at high angles of attack and high angles of side-slip in the high speed wind tunnel[J]. Experiments and Measurements in Fluid Mechanics, 1999(13):49-53(in Chinese).
[12] 王辉, 李力. 弹射座椅试验研究[J]. 实验流体力学与测量, 2002(3):40-45. WANG H, LI L. The research of ejection seat test[J]. Experiments and Measurements in Fluid Mechanics, 2002(3):40-45(in Chinese).
[13] 郁嘉, 林贵平, 吴铭. 弹射座椅减速性能的数值仿真计算[J]. 航空学报, 2006,27(6):1033-1038. YU J, LIN G P, WU M. Numerical simulation of deceleration performance of ejection seat[J]. Acta Aeronautica et Astronautica Sinica, 2006,27(6):1033-1038(in Chinese).
[14] 郁嘉, 林贵平, 毛晓东. 弹射救生数值仿真及不利姿态下救生性能分析[J]. 航空学报, 2010, 31(10):1927-1932. YU J, LIN G P, MAO X D. Numerical simulation of ejection seat and analysis of performance under adverse attitudes[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(10):1927-1932(in Chinese).
[15] 郁嘉, 毛晓东, 林贵平, 等. 风对弹射座椅救生性能的影响[J]. 航空学报, 2013, 34(4):727-740. YU J, MAO X D, LIN G P, et al. Impact of wind on ejection seat escape performance[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(4):727-740(in Chinese).
[16] 刘富, 童明波, 宋杰, 等. 带稳定板装置弹射座椅偏航稳定性能研究[J]. 空气动力学学报, 2010, 28(2):203-208. LIU F, TONG M B, SONG J, et al. Research of yaw-stabilization performance of ejection seat with stabilization fins[J]. Acta Aerodynamica Sinica, 2010, 28(2):203-208(in Chinese).
[17] 吴亮, 吴铭. 火箭弹射座椅运动稳定性能数值仿真研究[J]. 科技资讯, 2015, 13(10):4, 6. WU L, WU M. Numerical simulation study on dynamic stability for rocket ejection seat[J]. Science and Technology Information, 2015, 13(10):4, 6(in Chinese).
[18] 毛晓东, 林贵平, 郁嘉. 弹射座椅不利姿态控制规律设计[J]. 北京航空航天大学学报, 2016, 42(3):426-434. MAO X D, LIN G P, YU J. Design of control law for ejection seat under adverse attitudes[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(3):426-434(in Chinese).
[19] 张明环, 吴铭, 吴亮. 弹射座椅姿态控制算法研究[J]. 西北工业大学学报, 2015, 33(4):609-614. ZHANG M H, WU M, WU L. Researching attitude-control algorithm of ejection seats[J]. Journal of Northwestern Polytechnical University, 2015, 33(4):609-614(in Chinese).
[20] 魏涛, 张大林. 高速气流吹袭防护气动特性的数值模拟[J]. 南京航空航天大学学报(英文版), 2009, 26(4):268-273. WEI T, ZHANG D L. Numerical simulation on aerodynamic characteristics of windblast protection at high speed[J]. Transactions of Nanjing University of Aeronautics and Astronautics, 2009, 26(4):268-273(in Chinese).
[21] 高林星. 密闭式弹射座椅气动特性分析[D]. 南京:南京航空航天大学, 2018:46-67. GAO L X. Aerodynamic analysis of ejection capsule[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2018:46-67(in Chinese).
[22] DONALD W, JOHNSON. Status report of a new recovery parachute system for F111 aircraft crew escape module[C]//9th Aerodynamic Decelerator and Balloon Technology Conference. Reston:AIAA, 1986:AIAA-86-2437.
[23] SHANE J S. Design and testing of an energy-absorbing crewseat for the F/FB-111 aircraft:NASA CR-3916[R]. Washington, D.C.:NASA, 1985.
[24] CHARLEVILLE J L. The F-111 crew module development[C]//3rd Aerodynamic Deceleration Systems Conference. Reston:AIAA, 1970:AIAA-70-1210.
[25] 封文春, 周卫国, 关焕文. 整体座舱弹射救生技术分析[J]. 飞机工程, 2008(3):14-17. FENG W C, ZHOU W G, GUAN H W. Analysis of the integrated crew escape module ejection technology[J]. Journal of Aircraft Engineering, 2008(3):14-17(in Chinese).
[26] LI H M, REN Y J, QIAN Z S, et al. Implementation of three different transition methods and comparative analysis of the results computed by OVERSET software:AIAA-2016-3491[R]. Reston:AIAA, 2016.
[27] LIU Y, WANG L, QIAN Z S. Numerical investigation on the assistant restarting method of variable geometry for high Mach number inlet[J]. Aerospace Science and Technology, 2018, 79:647-657.
[28] 刘愿, 钱战森, 向先宏. 外并联式TBCC进气道模态转换风洞试验及模型典型影响因素分析[J]. 实验流体力学, 2019,33(5):18-27. LIU Y, QIAN Z S, XIANG X H. An analysis on typical influencing factors of wind tunnel experimental model of over-under TBCC inlet mode transition[J]. Journal of Experiments in Fluid Mechanics, 2019,33(5):18-27(in Chinese).
[29] LI X F, QIAN Z S. Applications of overset grid technique to CFD simulation of high Mach number multi-body interaction/separation flow[J]. Procedia Engineering, 2015, 99:458-476.
[30] 朱自强, 吴子牛, 李津, 等. 应用计算流体力学[M]. 北京:北京航空航天大学出版社, 2001:104-109. ZHU Z Q, WU Z N, LI J, et al. Application of computational fluid dynamics[M]. Beijing:Beihang University Press, 2001:104-109(in Chinese).
[31] 徐世坤. 弹射座椅中的稳定技术[J]. 航空科学技术, 1997(5):22-24. XU S K. Stabilization technology for ejection seats[J]. Aeronautical Science & Technology, 1997(5):22-24(in Chinese).

Numerical simulation of stable deceleration and safe separation of integral escape module for aerospace vehicles

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Bian LI, Lili QU, Yuping GAO. Methods for J0613-0200 steering a cesium clock [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(3): 526500-526500.
[2]	Chen ZHANG, Hao ZHANG. Lunar-gravity-assisted low-energy transfer from Earth into Distant Retrograde Orbit (DRO) [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 326507-326507.
[3]	Jiahong NIU, Haonan JIA, Fajun YI, Zujun PENG, Wei CHEN. Low-pressure thermal stability and high-temperature electrical conductivity of dense amorphous SiCN [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 152-159.
[4]	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.
[5]	LI Yingjie, ZHAO Guang, WU Xueshen, LI Jian, YUAN Wei, MEI Qing. Review of research on self-excited vibration of aviation spline-rotor system [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 625532-625532.
[6]	DENG Tian, LI Jiazhou, CHEN Wei. Breakup mechanism of viscous liquid transverse jet [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 125130-125130.
[7]	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.
[8]	LI Qiang, WAN Bingbing, YANG Kai, ZHU Tao. Experimental research on characteristics of pressure and heat flux fluctuation in hypersonic cone boundary layer [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(2): 124956-124956.
[9]	MENG Xufei, BAI Peng, LI Dun, WANG Rong, LIU Chuanzhen. Effect of dihedral wings on hypersonic performance of double swept waverider [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(2): 124998-124998.
[10]	WU Cihang, YAN Jianguo, QIAN Xianyun, GUO Yiming, QU Yaohong. Predefined-time attitude stabilization control of receiver aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(2): 324996-324996.
[11]	NIE Han, SONG Wenping, HAN Zhonghua, CHEN Jianqiang, DUAN Maochang, WAN Bingbing. Automatic transition prediction for natural-laminar-flow wing design of supersonic transports [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526342-526342.
[12]	XU Jiakuan, WANG Yuxuan, ZHANG Yang, QIAO Lei, LIU Jianxin, BAI Junqiang. Progress in amplification factor transport models in subsonic and transonic boundary layers [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526734-526734.
[13]	WANG Meng, LI Yujun, ZHAO Ronghuan, ZHONG Hongjie. Transition detection technique for wide speed range by means of on-line heating coating [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526820-526820.
[14]	FENG Lihao, WEI Lingyun, DONG Lei, WANG Jinjun. Active flow control for coupled motion instability of flying-wing aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(10): 527353-527353.
[15]	SUN Xiaofeng, DONG Xu, ZHANG Guangyu, WANG Zhuo, SUN Dakun. Progress review of application of eigenvalue theory to stability prediction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(10): 527408-527408.