气体质量引射对钝锥俯仰特性的影响

doi:10.7527/S1000-6893.2024.30822

Abstract

Abstract:

Using the coupled wind tunnel test technology of ablation gas mass injection and motion， we study the influence of gas injection on the aerodynamic characteristics such as dynamic stability of blunt cone model. The test was conducted at Mach number 6.0， and the injected gases were air， argon， and helium， respectively. The test results show that the increase in the mass flow rate of the injected gas produces a small amount of nose-down pitching moment； the coupling of the mass flow rate of the injected gas with the periodically changing model motion leads to different pitching dynamic derivatives with an obvious change pattern； a constant mass flow rate of the injected gas corresponds to invariant pitching dynamic stability of the model， and the results are consistent with those without injected gases.

Key words: blunt cone, ablation, mass injection, dynamic stability, wind tunnel test

CLC Number:

V211.78

Bin LIANG, Junbo ZHAO, Zengliang FU, Jiajian ZHOU, Ping ZHOU, Shiyu ZHANG, Weiqi SUN. Effect of gas mass injection on pitching characteristics of blunt cone[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(3): 130822.

Figures/Tables 11

Fig.1

Fig.2

Fig.3

Fig.4

Table 1

Fig.5

Table 2

Results of test without wind

状态	气体	$Q 1 ¯$ /（g·s^-1）	$Q 2 ¯$ /（g·s^-1）	C_m_无风	C_无风
无引射		0	0	3.75×10^-7	-0.007 43
引射流量不变	空气	0.5	1.0	6.07×10^-8	-0.007 49
引射流量不变	空气	1.2	2.4	3.88×10^-8	-0.007 44
引射流量周期变化	空气	0.5	1.0	1.05×10^-6	-0.007 44
	氩气	0.65	1.2	3.95×10^-7	-0.007 61
	氦气	0.07	0.14	2.10×10^-6	-0.007 65

Table 2

Fig.6

Fig.7

Fig.8

Table 3

Comparison of pitching moment coefficients under different test conditions

状态	气体	$Q 1 ¯$ /（g·s^-1）	$Q 2 ¯$ /（g·s^-1）	$Δ C m ¯$
无引射		0	0	0
引射流量不变	空气	0.50	1.00	-1.99×10^-4
引射流量不变	空气	1.20	2.40	-4.47×10^-4
引射流量周期变化	空气	0.50	1.00	-1.93×10^-4
	氩气	0.65	1.20	-2.73×10^-4
	氦气	0.07	0.14	6.46×10^-6

Table 3

References 29

1	ERICSSON L. Transition effects on slender vehicle stability and trim characteristics［C］‍∥‍11th Aerospace Sciences Meeting. Reston： AIAA， 1973.
2	CHANG S. Effects of ablation on hypersonic aerodynamic stability characteristics［C］‍∥3rd and 4th Aerospace Sciences Meeting. Reston： AIAA， 1966.
3	PATE S R. Measurements and correlations of transition Reynolds numbers on sharp slender cones at high speeds［J］. AIAA Journal， 1971， 9（6）： 1082-1090.
4	杨云军，沈清，詹慧玲，等. 高超声速小钝锥边界层非对称转捩研究［J］. 宇航学报， 2008， 29（1）： 34-39.
	YANG Y J， SHEN Q， ZHAN H L， et al. Investigation on asymmetric transition about hypersonic boundary layer over a slight blunt cone［J］. Journal of Astronautics， 2008， 29（1）： 34-39 （in Chinese）.
5	陈坚强，涂国华，张毅锋，等. 高超声速边界层转捩研究现状与发展趋势［J］. 空气动力学学报， 2017， 35（3）： 311-337.
	CHEN J Q， TU G H， ZHANG Y F， et al. Hypersnonic boundary layer transition： what we know， where shall we go［J］. Acta Aerodynamica Sinica， 2017， 35（3）： 311-337 （in Chinese）.
6	杨武兵，沈清，朱德华，等. 高超声速边界层转捩研究现状与趋势［J］. 空气动力学学报， 2018， 36（2）： 180-195.
	YANG W B， SHEN Q， ZHU D H， et al. Tendency and current status of hypersonic boundary layer transition［J］. Acta Aerodynamica Sinica， 2018， 36（2）： 180-195 （in Chinese）.
7	宋威，赵小见，鲁伟，等. 高超声速边界层转捩对旋转钝锥自由飞运动的影响［J］. 航空学报， 2017， 38（11）： 89-95.
	SONG W， ZHAO X J， LU W， et al. Effect of boundary layer transition on free flight motion of hypersonic spinning blunt cone［J］. Acta Aeronautica et Astronautica Sinica， 2017， 38（11）： 89-95 （in Chinese）.
8	楼洪钿. 气动静/动稳定性的相关性及粘性滞后时间的研究［J］. 空气动力学学报， 2000， 18（1）： 68-73.
	LOU H T. Study on aerodynamic static/dynamic stability correlation and viscous lag time［J］. Acta Aerodynamica Sinica， 2000， 18（1）： 68-73 （in Chinese）.
9	张石玉，赵俊波，付增良，等. 钝锥动态转捩风洞试验［J］. 实验流体力学， 2022， 36（6）： 61-66.
	ZHANG S Y， ZHAO J B， FU Z L， et al. Dynamic boundary layer transition wind tunnel test of blunt cone［J］. Journal of Experiments in Fluid Mechanics， 2022， 36（6）： 61-66 （in Chinese）.
10	CANDLER G V. Rate effects in hypersonic flows［J］. Annual Review of Fluid Mechanics， 2019， 51： 379-402.
11	莫凡，高振勋，蒋崇文，等. 高温化学非平衡效应对高超声速飞行器气动力/热影响的数值研究进展［J］. 中国科学（物理学力学天文学）， 2021， 51（10）： 22-37.
	MO F， GAO Z X， JIANG C W， et al. Progress in the numerical study on the aerodynamic and thermal characteristics of hypersonic vehicles： high-tempera-ture chemical non-equilibrium effect［J］. Scientia Sinica （Physica， Mechanica & Astronomica）， 2021， 51（10）： 22-37 （in Chinese）.
12	李瑾，苏伟，黄章峰，等. 质量引射对边界层稳定性的影响［J］. 航空动力学报， 2020， 35（2）： 280-293.
	LI J， SU W， HUANG Z F， et al. Effect of mass ejection on boundary layers stability［J］. Journal of Aerospace Power， 2020， 35（2）： 280-293 （in Chinese）.
13	姚从菊. 再入飞行器烧蚀层内热质传输过程的数值模拟［D］. 哈尔滨：哈尔滨工业大学， 2007： 9-16.
	YAO C J. Numerical simulation of heat and mass transfer in ablation layer of reentry vehicle［D］. Harbin： Harbin Institute of Technology， 2007： 9-16 （in Chinese）.
14	姜贵庆，刘连元. 高速气流传热与烧蚀热防护［M］. 北京：国防工业出版社， 2003.
	JIANG G Q， LIU L Y. Heat transfor of hypersonic gas and ablation thermal protection［M］. Beijing： National Defense Industry Press， 2003 （in Chinese）.
15	梁彬，赵俊波，付增良，等. 烧蚀气体质量引射风洞试验技术［J］. 实验流体力学， DOI： 10.11729/syltlx20230013 .
	LIANG B， ZHAO J B， FU Z L， et al. Experimental technique in wind tunnel for mass injection of ablative gas flow［J］. Journal of experiments in Fluid Mechanics， DOI： 10.11729/syltlx20230013 （in Chinese）.
16	SCHNEIDER S P. Hypersonic boundary-layer transition with ablation and blowing［J］. Journal of Spacecraft and Rockets， 2010， 47（2）： 225-237.
17	JOHNSON H， GRONVALL J， CANDLER G. Reacting hypersonic boundary layer stability with blowing and suction［C］∥47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston： AIAA， 2009.
18	JEWELL J， WAGNILD R， LEYVA I， et al. Transition within a hypervelocity boundary layer on a 5-degree half-angle cone in air/CO₂ mixtures［C］∥51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston： AIAA， 2013.
19	LEYVA I， LAURENCE S， BEIERHOLM A， et al. Transition delay in hypervelocity boundary layers by means of CO₂/acoustic instability interactions［C］∥47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston： AIAA， 2009.
20	MIRÓ MIRÓ F， PINNA F. Injection-gas-composition effects on hypersonic boundary-layer transition［J］. Journal of Fluid Mechanics， 2020， 890： R4.
21	WANG X W， ZHONG X L， MA Y B. Response of a hypersonic boundary layer to wall blowing-suction［J］. AIAA Journal， 2011， 49（7）： 1336-1353.
22	朱广生，姚世勇，段毅. 高速飞行器减阻降热流动控制技术研究进展及工程应用［J］. 航空学报， 2023， 44（15）： 1-16.
	ZHU G S， YAO S Y， DUAN Y. Research progress and engineering application of flow control technology for drag and heat reduction of high-speed vehicles［J］. Acta Aeronautica et Astronautica Sinica， 2023， 44（15）： 1-16 （in Chinese）.
23	沙心国，郭跃，纪锋，等. 高超声速圆锥边界层失稳条纹结构实验研究［J］. 空气动力学学报， 2020， 38（1）： 143-147.
	SHA X G， GUO Y， JI F， et al. Experimental study on instability streak structure over a hypersonic cone［J］. Acta Aerodynamica Sinica， 2020， 38（1）： 143-147 （in Chinese）.
24	李周复. 风洞特种试验技术［M］. 北京：航空工业出版社， 2010： 303-324.
	LI Z F. Wind tunnel special test technology［M］. Beijing： Aviation Industry Press， 2010： 303-324 （in Chinese）.
25	赵俊波，付增良，高清，等. 圆锥标模高超声速俯仰自由振动试验与分析［J］. 气体物理， 2018， 3（2）： 57-63.
	ZHAO J B， FU Z L， GAO Q， et al. Pitching free-oscillation test and analysis of hypersonic standard cone model［J］. Physics of Gases， 2018， 3（2）： 57-63 （in Chinese）.
26	范洁川. 风洞试验手册［M］. 北京：航空工业出版社， 2002： 430-440.
	FAN J C. Handbook of wind tunnel test［M］. Beijing： Aviation Industry Press， 2002： 430-440 （in Chinese）.
27	EAST R A， HUTT G R. Comparison of predictions and experimental data for hypersonic pitching motion stability［J］. Journal of Spacecraft and Rockets， 1988， 25（3）： 225-233.
28	赵俊波，付增良，梁彬，等. 再入弹头小不对称俯仰气动特性测量技术研究［J］. 实验流体力学， 2015， 29（5）： 55-59.
	ZHAO J B， FU Z L， LIANG B， et al. Research on the wind tunnel test techniques for micro-pitching-aerodynamics of re-entry body［J］. Journal of Experiments in Fluid Mechanics， 2015， 29（5）： 55-59 （in Chinese）.
29	刘小林，易仕和，牛海波，等. 激光聚焦扰动作用下高超声速边界层稳定性实验研究［J］. 物理学报， 2018， 67（21）： 221-232.
	LIU X L， YI S H， NIU H B， et al. Influence of laser-generated perturbations on hypersonic boundary-layer stability［J］. Acta Physica Sinica， 2018， 67（21）： 221-232 （in Chinese）.

气体	密度/（kg·m^-3）	相对分子量	比热比
空气（Air）	1.29	28.96	1.40
氦气（He）	0.18	4.00	1.66
氩气（Ar）	1.78	39.94	1.67

[1]	Lixiang WEI, Jinglei XU, Kuangshi CHEN, Shuai HUANG, Jianhui GE, Guangtao SONG. Scheme design and performance study of adjustable vector nozzle for wide-range hypersonic aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(8): 631086-631086.
[2]	Yaoying ZENG, Running WANG, Jiaqi HOU, Yulei ZHANG, Jiaping ZHANG, Hejun LI. Research progress of C/C composites resistant to extreme ablation environments [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(6): 531927-531927.
[3]	Xian YI, Jinghao REN, Qingren LAI, Yu LIU, Qiang WANG. Icing characteristics of full-scale multi-element configurations of large aircraft: Computation and experiment [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(5): 531575-531575.
[4]	Zhiqiang WAN, Shanshan ZHANG, Xiaozhe WANG, Liang MA, Ao XU, Zhigang WU, Chao YANG. Maneuver load analysis and alleviation technology of flexible aircraft: Review [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(3): 30279-030279.
[5]	Zhengwu CHEN, Yubiao JIANG, Xiangyu LU, Qiangbin LI. Aerodynamic noise test of open rotor in wind tunnel [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130425-130425.
[6]	Xueliang LI, Chuangchuang LI, Yahan ZHANG, Wei SU, Jie WU. Effect of distributed ablation pattern on hypersonic boundary-layer instability with a flat plate [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130464-130464.
[7]	Ming CAI, Limin GAO, Ruiyu LI, Bo OUYANG, Bo LIU. Establishment of standard model of linear cascade wind tunnel for subsonic compressor [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130547-130547.
[8]	Xiping KOU, Kaichun ZENG, Tao MA, Bo LU, Zhichun YANG. Model vibration mechanism and active control in wind tunnel test: Review [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(1): 30467-030467.
[9]	Pengpeng SUN, Ping’an LIU, Feng FAN, Wei ZENG. Aerodynamic interaction characteristics of coaxial rigid rotor⁃fuselage in hover condition [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 529284-529284.
[10]	Chang WANG, Long HE, Dongxia XU, Min TANG, Shuai MA, Ximing WU. Flow control drag reduction of hub on coaxial rigid rotor aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 529084-529084.
[11]	Weiguo ZHANG, Min TANG, Jie WU, Xianmin PENG, Guichuan ZHANG, Bowen NIE, Liangquan WANG, Chaoqun LI. Overview of wind tunnel test research on tiltrotor aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 530114-530114.
[12]	Bowen NIE, Liangquan WANG, Zhiyin HUANG, Long HE, Shipeng YANG, Hongtao YAN, Guichuan ZHANG. Flight dynamics modeling and control scheme design of compound high-speed unmanned helicopters [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 529848-529848.
[13]	Qichang CHEN, Zhiwei SHI, Weiyuan ZHANG, Linglong YAO, Shengxiang TONG. Aerodynamic layout and control strategy design and flight verification of a wing⁃foldable variant VTOL aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 629583-629583.
[14]	Liu LIU, Xianhong XIANG, Yufei ZHANG, Haixin CHEN, Chuang WEI, Jian ZHU, Pu YANG. A high lift-to-drag ratio unconventional blended-wing-body aerodynamic configuration with swallow tail [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 629630-629630.
[15]	Zhiting GAO, Zhuang MA, Yanbo LIU. Effect of CVD-SiC array structure on ablation resistance of ZrB₂/SiC coatings [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(3): 428842-428842.

Effect of gas mass injection on pitching characteristics of blunt cone

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 11

References 29

Related Articles 15

Recommended Articles

Metrics

Comments