高温燃气进入舵机舱过程仿真与流动机理分析

doi:10.7527/S1000-6893.2015.0055

Abstract

Abstract:

The phenomenon of hot gas exhausted from the rocket engine flowing into the control section in the burnout phase of a rocket engine is studied using computational fluid dynamics (CFD) method. A simplified simulation method is proposed without much loss in accuracy after analyzing the parameters of the actual trajectory of a missile, based on the aerodynamic theory that disturbance in supersonic flow will not propagate upstream, and it greatly reduce the time cost. The dynamic progress that the air in the control section is first pumped out and the hot gas is sucked in afterward recurred, and flow mechanism is found out: during the working stage of the rocket engine, the air in the control section is pumped out due to the low pressure at the base of the missile, and then along with the reduction in the total pressure in the combustion chamber during the descending stage of the rocket the Mach disk moves towards the base which results in the increase of the base pressure, and finally the hot gas flows into the control section which causes the burning of the circuit board and then the fracture of the missile in the end. Finally the cause of failure is revealed, and the improvement measures and detection method are proposed and then validated in flight tests, the reliability of thermal protection is solved.

Key words: rocket motors, missile, supersonic, unsteady flow, computational fluid dynamics

CLC Number:

V211.3

LI Bin, WANG Xuezhan, LIU Xianming. Numerical investigation and flow mechanism analysis of hot gas entering control section[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(9): 2840-2849.

References

[1] Fan H T, Lv C Q, Lin Z X. Design for air-to-air missile[M]. Beijing: National Defense Industry Press, 2007: 190 (in Chinese). 樊会涛, 吕长起, 林忠贤. 空空导弹系统总体设计[M].北京: 国防工业出版社, 2007: 190.
[2] Stein S, Thiokol M. Seal material selection, design and performance-advancements from the space shuttle booster redesign, AIAA-1989-2774[R]. Reston: AIAA, 1989.
[3] Fan H T. Air-to-air missile conceptual design[M]. Beijing: Aviation Industry Press, 2013: 160 (in Chinese). 樊会涛. 空空导弹方案设计原理[M]. 北京: 航空工业出版社, 2013: 160.
[4] Salita M. Unanticipated problems and misunderstood phenomena in and around solid rockets, AIAA-2011-5956[R]. Reston: AIAA, 2011.
[5] Loh H T, Smith-Kent R, Perkins F. Evaluation of aft skirt length effects on rocket motor base heat using computational fluid dynamics, AIAA-1996-2645[R]. Reston: AIAA, 1996.
[6] Shen C, Xia X L, Cao Z W, et al. Analysis of flow and heat characteristics of seal structure with gap and cavity under the impact of high speed airflow[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(1): 34-43 (in Chinese). 沈淳, 夏新林, 曹占伟, 等. 缝隙-腔体密封结构在高速气流冲击下的整体流动、传热特性分析[J]. 航空学报, 2012, 33(1): 34-43.
[7] Yan C. Application foundation of computational fluid dynamics[M]. Beijing: Beihang University Press, 2005: 24 (in Chinese). 阎超. 计算流体力学应用基础[M]. 北京: 北京航空航天大学出版社, 2005: 24.
[8] Anderson J D. Computational fluid dynamics: Basic and application[M]. Wu S P, Zhao L M, translated. Beijing: China Machine Press, 2007: 58 (in Chinese). Anderson J D. 计算流体力学: 基础与应用[M]. 吴颂平, 赵刘淼, 译. 北京: 机械工业出版社, 2007: 58.
[9] Menter F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal,1994, 32(8): 1598-1605.
[10] Pointwise Inc. Pointwise user mannual. Software Release Version 17.2 R1[Z]. American Pointwise Inc. 2014: 317-330.
[11] Lebedev A A. Flight dynamics for unmanned aerial vehicals[M]. Beijing: National Defense Industry Press, 1964: 225 (in Chinese). 列别捷夫 A A.无人驾驶飞行器的飞行动力学[M]. 北京: 国防工业出版社, 1964: 225.
[12] Xu M, An X M. The analyses and computational method of aerodynamic characteristics of aircraft[M]. Xi'an: Northwestern Polytechnical University Press, 2012: 109 (in Chinese). 徐敏, 安效民. 飞行器空气动力特性分析与计算方法[M]. 西安: 西北工业大学出版社, 2012: 109.
[13] Tong B G, Kong X Y, Deng G H. Gas dynamics[M]. Beijing: Higher Education Press, 2012: 192 (in Chinese). 童秉纲, 孔祥言, 邓国华. 气体动力学[M]. 北京: 高等教育出版社, 2012: 192.
[14] Wu Z N. Aerodynamics[M]. Beijing: Tsinghua University Press, 2008: 34 (in Chinese). 吴子牛. 空气动力学[M]. 北京: 清华大学出版社, 2008: 34.

[1]	Di WANG, Yan LENG, Long YANG, Zhonghua HAN, Zhansen QIAN. Atmospheric turbulence effects on sonic boom propagation based on augmented Burgers equation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626318-626318.
[2]	Yulin DING, Zhonghua HAN, Jianling QIAO, Han NIE, Wenping SONG, Bifeng SONG. Research progress in key technologies for conceptual-aerodynamic configuration design of supersonic transport aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626310-626310.
[3]	Yiran GU, Jiangtao HUANG, Shusheng CHEN, Deyuan LIU, Zhenghong GAO. Sonic boom inversion technology based on inverse augmented Burgers equation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626258-626258）.
[4]	Fangcheng SHI, Zhenxun GAO, Yuyan TIAN, Chongwen JIANG, Tiantian WANG, Chun-Hian LEE. Large eddy simulation of ideally expanded supersonic jet noise [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626266-626266.
[5]	Jianling QIAO, Zhonghua HAN, Yulin DING, Wenping SONG, Bifeng SONG. Effects of stratified atmospheric turbulence on farfield sonic boom propagation [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626350-626350.
[6]	Yahui SONG, Gaoyu FAN, Lixia QU, Yuelin ZHANG, Yue XU, Shuo HAN. Progress of aircraft sonic boom flight test measurement technology: Review [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626186-626186.
[7]	WU Qiang, XU Haojun, WEI Yang, PEI Binbin, XUE Yuan. Aerodynamics/flight dynamics coupling characteristics of aircraft under icing conditions [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 125566-125566.
[8]	QIN Chen, ZHANG Rongping, ZHANG Junlong, YUE Tingrui, WU Songling. Acoustic performance of an under-expanded supersonic jet with different impinging distances to an inclined plate [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 125857-125857.
[9]	XIAHOU Tangfan, CHEN Jiangtao, SHAO Zhidong, WU Xiaojun, LIU Yu. Model validation metrics for CFD numerical simulation under aleatory and epistemic uncertainty [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 25716-025716.
[10]	HOU Yingyu, LI Qi, JI Chen, LIU Ziqiang. Experimental design of aeroelastic load with supersonic low frequency and large buffeting [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 626454-626454.
[11]	CHEN Guangqiang, DOU Guohui, WEI Haogong, ZOU Xin, LI Qi, LIU Zhou, ZHOU Weijiang. Air data sensing technology of Mars probe [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 626619-626619.
[12]	XU Xin, JIA He, CHEN Yaqian, RONG Wei, JIANG Wei, XUE Xiaopeng. Influence mechanism of fabric permeability of canopy on aerodynamic performance of Mars parachute [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(12): 126289-126289.
[13]	ZHANG Liwen, SONG Wenping, HAN Zhonghua, QIAN Zhansen, SONG Bifeng. Recent progress of sonic boom generation, propagation, and mitigation mechanism [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(12): 25649-025649.
[14]	YUAN Jisen, SUN Jue, LI Lingyu, YU Shenghao, NIE Han, GAO Liangjie, HAN Zhonghua, QIAN Zhansen. Progress of supersonic aircraft laminar flow layout design and evaluation technologies [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526316-526316.
[15]	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.

Numerical investigation and flow mechanism analysis of hot gas entering control section

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments