扰流板对内埋导弹偏航姿态角的影响

doi:10.7527/S1000-6893.2013.0428

Abstract

Abstract:

A number of spoilers are designed in the leading edge of the weapons bay which may possibly control the flow and improve the yawing moment characteristic in the missile separating course so as to force the missile's head to reverse for the safety of the separation yawing. To study the problem, spoilers of different heights are built in the leading edge of the weapons bay through theoretical analysis and a wind tunnel test is conducted to measure the forces acting on the parts so as to study the spoilers' effect on the flow patterns in the bay and the missile's yawing moment characteristics. Furthermore, the spoilers' effect on the missile's yawing separation characteristics is analyzed, and the credibility of the separation yawing attitude angle characteristic analysis is validated by a track capture wind tunnel test. The result shows that designing spoilers with certain heights in the leading edge of the weapons bay can effectively control the flow patterns in the bay, improve the missile's yawing aerodynamic characteristic, and improve the separating yawing safety.

Key words: weapons bay, spoiler, flow control, wind tunnel test, separation characteristic, attitude angle

CLC Number:

GUAN Dehui, CAI Weimin. Spoiler’s Effect on the Yawing Attitude Angle of the Missile in the Bay[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(4): 942-947.

References

[1] Wu J F, Luo X F, Fan Z L. Flow control method to improve cavity flow and store separation characteristics[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(10):1840-1845.(in Chinese) 吴继飞, 罗新福, 范召林.内埋式弹舱流场特性及武器分离特性改进措施[J].航空学报, 2009, 30(10): 1840-1845.

[2] Feng Q, Cui X C. Study on integrated flow control for weapons bay of flying wing configuration aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(5): 781-787.(in Chinese) 冯强, 崔晓春.飞翼布局武器舱综合流动控制技术研究[J].航空学报, 2012, 33(5): 781-787.

[3] Yang D G, Fan Z L, Li J Q, et al. Studies on flow characteristics of cavity by numerical simulation and wind tunnel test[J]. Acta Aerodynamica Sinica, 2009, 27(3): 378-383.(in Chinese) 杨党国, 范召林, 李建强, 等.弹舱流动特性数值模拟及风洞试验研究[J].空气动力学学报, 2009, 27(3): 378-383.

[4] Li J, Li T, Zhang Q F. The mechanism and control of a open cavity flow[J]. Journal of Experiments in Fluid Mechanics, 2008, 22(1): 80-83.(in Chinese) 黎军, 李天, 张群峰.开式流动舱体的流动机理与控制[J]. 实验流体力学, 2008, 22(1): 80-83.

[5] Wu J F, Tao Y, Fan Z L, et al. Analysis of the effect of the modification at the trailing edge on cavity flow characteristics[J]. Acta Aerodynamica Sinica, 2010, 28(2):197-202.(in Chinese) 吴继飞, 陶洋, 范召林, 等.后缘修型对空腔流场特性影响分析[J].空气动力学学报, 2010, 28(2): 197-202.

[6] Luo X F, Fan Z L. The firs modern experimental aerodynamics of corpus//Experimental Investigation on Internal Weapon bay Flow Characteristics and Its Flow Control. Beijing: Atomic Press, 2007.

[7] Zhang N, Alvi F S, Alkislar M B, et al.Aeroacoustic properties of supersonic cavity flow and their control, AIAA-2003-3101. Reston: AIAA, 2003.

[8] Raman G, Kibens V. Active flow control using integrated powered resonance tube actuators, AIAA-2001-3024. Reston: AIAA, 2001.

[9] Grove J E, Birkbeck R M, Kreher J M. Acoustic and separation characteristics with bay leading edge blowing, AIAA-2000-1904. Reston: AIAA, 2000.

[10] Smith B R, Welterlen T J, Maines B H, et al. Weapons bay acoustic suppression from rod spoilers, AIAA-2002-0662. Reston: AIAA, 2002.

[11] Cattafesta L, Williams D R, Rowley C W, et al. Review of active control of flow induced cavity resonance, AIAA-2003-3567. Reston: AIAA, 2003.

[12] Liu Y. Fluid dynamica analysis on missile launching and separating from weapon bay. Nanjing: Nanjing University of Aeronautics and Astronautics, 2010.(in Chinese) 刘瑜. 内埋式弹舱武器发射分离过程研究.南京: 南京航空航天大学, 2010.

[13] Zhang B B. Numerical simulation and control of cavity flow. Nanjing: Nanjing University of Aeronautics and Astronautics, 2011.(in Chinese) 张宝兵. 空腔流动的机理模拟与控制. 南京: 南京航空航天大学, 2011.

[14] Wang W. Aerodynamic studies and simulation of missiles internal. Harbin: Harbin Engineering University, 2011.(in Chinese) 王巍. 导弹内埋气动特性研究与仿真. 哈尔滨: 哈尔滨工业大学, 2011.

[15] Huang X H, Luo X F, Yu Z S. Design & development of a new captive trajectory simulation system in FL-24 wind tunnel[J]. Acta Aerodynamica Sinica, 2008, 26(2): 145-149.(in Chinese) 黄叙辉, 罗新福, 于志松.FL-24风洞新型捕获轨迹系统设计与发展[J].空气动力学学报, 2008, 26(2): 145-149.

[16] Yu Z S, Wang F X, Luo X F. Investigation of two special CTS test techniques[J].Experiments and Measurements in Fluid Mechanics, 2004, 18(4): 49-53.(in Chinese) 于志松, 王发祥, 罗新福. 两种特殊CTS试验技术的研究[J]. 流体力学试验与测量, 2004, 18(4): 49-53.

Spoiler’s Effect on the Yawing Attitude Angle of the Missile in the Bay

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Shanjie XU, Hongqiang LYU, Zhongchen LIU, Yan LENG, Xuejun LIU. Data analysis of sonic boom test based on probability model [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626269-626269.
[2]	Zhongchen LIU, Zhansen QIAN, Xuefei LI, Yan LENG, Dapeng GUO. Wind tunnel test techniques for exhaust nozzle plume effects on near-field sonic boom [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626952-626952.
[3]	Jun SHU, Dongguang XU, Zhirong HAN, Si LI, Xiong HUANG. Hybrid wing design of icing wind tunnel supercooled large droplet icing test [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(1): 627182-627182.
[4]	Yating FENG, Hui ZHANG. Aerodynamic drag reduction device based on rear wind energy harvesting [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 180-191.
[5]	Kai LUO, Yonghai WANG, Qiu WANG, Jiwei LI, Zheng LI, Chunsheng NIE, Zheng LI. Plasma-actuated flow control test in high enthalpy shock tunnel [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 89-96.
[6]	Xudong ZHANG, Zheng LI, Hao DONG, Siyuan GAO, Zubi JI, Kaixin LI, Guanghui BAI. Drag reduction characteristics of opposing plasma synthetic jet in hypersonic flow [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 115-123.
[7]	Zheng LI, Cong XU, Jian ZHANG, Mengmeng LI, Yilei MA, Guanghui BAI. Reverse jet flow control by plasma synthetic jet actuator in high speed flow field [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 225-232.
[8]	Zhengxue MA, Zhenbing LUO, Aihong ZHAO, Yan ZHOU, Wei XIE, Qiang LIU, Yinxin ZHU, Wenqiang PENG. Reverse jet characteristics of plasma synthetic jet in hypersonic flow field [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 192-203.
[9]	Kai LUO, Qiu WANG, Jinping LI, Wei ZHAO. Magnetohydrodynamic flow control of double-cone under high temperature real gas effect [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 76-88.
[10]	LIU Chuanzhen, MENG Xufei, LIU Rongjian, BAI Peng. Experimental and numerical investigation of hypersonic performance of double swept waverider [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 126015-126015.
[11]	HAN Luyang, WANG Bin, PU Liang, CHEN Qing, ZHENG Haibin. Research progress on mechanism and related problems of energy deposition drag reduction technology [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 26032-026032.
[12]	LIU Qiang, TU Guohua, LUO Zhenbing, CHEN Jianqiang, ZHAO Rui, YUAN Xianxu. Progress in hypersonic boundary layer transition delay control [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 25357-025357.
[13]	LIU Jun, LUO Xinfu, WANG Xiansheng. Experiment on influence of leading-edge shape on aerodynamic characteristics of cavity model [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 125235-125235.
[14]	ZHOU Yan, LUO Zhenbing, WANG Lin, XIA Zhixun, GAO Tianxiang, XIE Wei, DENG Xiong, PENG Wenqiang, CHENG Pan. Plasma synthetic jet actuator for flow control: Review [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 25027-025027.
[15]	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.