临近空间高速飞行器微量气动力试验及计算

doi:10.7527/S1000-6893.2022.27072

Abstract

Abstract:

Structural design and static calibration were developed for accurate measurement of micro aerodynamic wind tunnel tests in near space atmospheric environments. Then，the simple blunt cone model was used for the micro-aerodynamic force experiment verification，and the complex shape of the triangular lift body was adopted to explore the ability to measure the micro-aerodynamic force in thinner atmospheric environments. The results show that the repeatability accuracy of aerodynamic data of each balance load unit is better than 4.8% in the three times of the blunt cone shape verification test. In the exploration test，the triangular lift body adopts the lowest density state the wind tunnel can currently achieve，and the test results show that the micro-force balance performs well in the limit state. The numerical simulation results，compared with the experimental results，show that the aerodynamic forces of the blunt cone and the delta wing lift body are in good agreement with those measured by microbalance； for the simple blunt cone，the compressive resistance of the blunt surface is significantly higher than the frictional resistance under its test conditions，while the surface friction ratio of the complex delta wing body is equal to the piezoresistive，with much thinner test conditions.

Key words: near space, wind tunnel test, microbalance, aerodynamic force, high speed vehicles

CLC Number:

V411.3

Junhong LI, Xuhong JIN, Chunfeng LIU, Wenbo MIAO, Xiaoli CHENG. Microaerodynamic experiment and computation of near space high speed vehicles[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(6): 127072-127072.

Figures/Tables 25

Fig. 1

Fig. 2

Fig. 3

Table 1

Table 2

Fig. 4

Table 3

Fig. 5

Fig. 6

Fig. 7

Table 4

Table 5

Fig. 8

Fig. 9

Fig. 10

Fig. 11

Fig. 12

Fig. 13

Table 6

Fig. 14

Fig. 15

Fig. 16

Fig. 17

Table 7

Fig. 18

References 24

1	于登云. 新型航天器发展对力学学科的挑战［J］. 科学通报， 2015， 60（12）： 1085-1094.
	YU D Y. Mechanical challenges in advanced spacecraft development［J］. Chinese Science Bulletin， 2015， 60（12）： 1085-1094 （in Chinese）.
2	FREEMAN J D C， REUBUSH D E， MCCLINTON C R，et al. The NASA hyper-X program： NASA TM-1997-207243［R］. Washington， D. C.： NASA， 1997.
3	MORELLI E A， DERRY S D， SMITH M S. Aerodynamic parameter estimation for the X-43A（hyper-X）from flight data［C］∥ AIAA Atmospheric Flight Mechanics Conference and Exhibit. Reston： AIAA， 2005.
4	MARSHALL L A， BAHM C， CORPENING G P， et al. Overview with results and lessons learned of the X-43a Mach 10 flight［C］∥ AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Comference. Reston： AIAA， 2005.
5	马汉东. 高超声速技术项目“Hyper-X”气动研究方法学［J］. 力学与实践， 2014， 36（3）： 261-268， 277.
	MA H D. Methodology of aerodynamic research for hypersonic technical project“Hyper-X”［J］. Mechanics in Engineering， 2014， 36（3）： 261-268， 277 （in Chinese）.
6	BERRY S， DARYABEIGI K， WURSTER K， et al. Boundary layer transition on X-43A［C］∥ 38th Fluid Dynamics Conference and Exhibit. Reston： AIAA， 2008.
7	HANK J M. Air force research laboratory hypersonic propulsion research programs［C］∥ 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston： AIAA， 2007.
8	CANDLER G， JOHNSON H， ALBA C， et al. Analysis of modal growth on the leeward center plane of the X-51 vehicle： FRL-RB-WP-TM-2010-3001A［R］. Minnesota： University of Minnesota， 2010.
9	李建林. 临近空间高超声速飞行器发展研究［M］. 北京：中国宇航出版社， 2012.
	LI J L. Development survey of near space hypersonic vehicles［M］. Beijing： China Astronautic Publishing House， 2012 （in Chinese）.
10	WALKER S， SHERK J， SHELL D， et al. The DARPA/AF falcon program：the hypersonic technology vehicle #2 （HTV-2）flight demonstration phase［C］∥ 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston： AIAA， 2008.
11	WALKER S H， RODGERS F. Falcon hypersonic technology overview［C］∥ 13th AIAA/CIRA International Space Planes and Hypersonic Systems and Technologies Conference. Reston： AIAA， 2005.
12	聂万胜，罗世彬，丰松江，等. 近空间飞行器关键技术及其发展趋势分析［J］. 国防科技大学学报， 2011， 34（2）：107-113.
	NIE W S， LUO S B， FENG S J，et al. Analysis of key technologies and development trend of near space vehicle［J］. Journal of National University of Defense Technology， 2011， 34（2）： 107-113 （in Chinese）.
13	陈冰，郑勇，陈张雷，等. 临近空间高超声速飞行器天文导航系统综述［J］. 航空学报， 2020， 41（8）： 623686.
	CHEN B， ZHENG Y， CHEN Z L， et al. A review of celestial navigation system on near space hypersonic vehicle［J］. Acta Aeronautica et Astronautica Sinica， 2020， 41（8）： 623686 （in Chinese）.
14	余平，段毅，尘军. 高超声速飞行的若干气动问题［J］. 航空学报， 2015， 36（1）： 7-23.
	YU P， DUAN Y， CHEN J. Some aerodynamic issues in hypersonic flight［J］. Acta Aeronautica et Astronautica Sinica， 2015， 36（1）： 7-23 （in Chinese）.
15	叶友达，张涵信，蒋勤学，等. 近空间高超声速飞行器气动特性研究的若干关键问题［J］. 力学学报， 2018， 50（6）：1292-1310.
	YE Y D， ZHANG H X， JIANG Q X， et al. Some key problems in the study of aerodynamic characteristics of near-space hypersonic vehicles［J］. Chinese Journal of Theoretical and Applied Mechanics， 2018， 50（6）： 1292-1310 （in Chinese）.
16	李廷伟，张莽，赵文文，等. 面向稀薄流非线性本构预测的机器学习方法［J］. 航空学报， 2021， 42（4）： 524386.
	LI T W， ZHANG M， ZHAO W W， et al. Machine learning method for correction of rarefied nonlinear constitutive relations［J］. Acta Aeronautica et Astronautica Sinica， 2021， 42（4）： 524386 （in Chinese）.
17	程晓丽，苗文博，黄飞，等. 跨流域多物理效应新型实验与预测技术［R］. 北京：中国航天空气动力技术研究院， 2021.
	CHENG X L， MIAO W B， HUANG F， et al. New experiment and computation technology for multi-physical effects in multiple flow regime［R］. Beijing： China Academy of Aerospace Aerodynamics， 2021 （in Chinese）.
18	靳旭红，黄飞，程晓丽，等. Maxwell气固相互作用模型对稀薄高超声速凹腔绕流流动特征和热环境的影响［J］. 航空学报， 2021， 42（3）： 124118.
	JIN X H， HUANG F， CHENG X L， et al. Effect of Maxwell gas surface interaction models on flow characteristics and thermodynamic properties of rarefied hypersonic cavity flows［J］. Acta Aeronautica et Astronautica Sinica， 2021， 42（3）： 124118 （in Chinese）.
19	JIN X H， HUANG F， CHENG X L， et al. Monte Carlo simulation for aerodynamic coefficients of satellites in low-Earth orbit［J］. Acta Astronautica， 2019， 160（1）： 222-229.
20	刘春风，刘家骅. 微量天平测力技术［R］. 北京：中国航天空气动力技术研究院， 2021.
	LIU C F， LIU J H. Microbalance force measurement technology［R］. Beijing： China Academy of Aerospace Aerodynamics， 2021 （in Chinese）.
21	孙勇堂，赵之平，石运军，等. CAAA新建Φ1.2米常规高超声速风洞［C］∥ 中国力学大会，2017.
	SUN Y T， ZHAO Z P， SHI Y J， et al. New-built 1.2 diameter conventional hypersonic wind tunnel［C］∥ Chinese Mechanics Conference， 2017.
22	阎超. 计算流体力学方法及应用［M］. 北京：北京航空航天大学出版社， 2006.
	YAN C. Computational fluid mechanics and methods［M］. Beijing： Beihang University Press， 2006 （in Chinese）.
23	苗文博，罗晓光，程晓丽，等. 壁面催化对高超声速飞行器气动特性影响［J］. 空气动力学学报， 2014， 32（2）： 235-239.
	MIAO W B， LUO X G， CHENG X L， et al. Surface recombination effects on aerodynamic loads of hypersonic vehicles ［J］. Acta Aerodynamica Sinica， 2014， 32（2）：235-239 （in Chinese）.
24	LIOU M S. A further development of the AUSM+ scheme towards robust and accurate solutions for all speeds［C］∥ 16th AIAA Computational Fluid Dynamics Conference. Reston： AIAA， 2003.

工况	Ma	P₀/Pa	q/Pa	T₀/°C	Re/m^-1
1	8.014	1 216 384	5 538.1	291.7	4 322 697
2	8.014	1 219 124	5 550.6	327.4	3 897 376
3	8.014	1 219 881	5 554.0	331.3	3 856 281

工况	α/（°）	C_N	C_A	C_mz
1	-4	-0.092 34	0.177 85	0.057 45
	-2	-0.045 18	0.174 95	0.027 91
	0	-0.001 78	0.172 86	0.001 22
	2	0.043 69	0.174 81	-0.026 91
	4	0.095 82	0.182 53	-0.059 61
2	-4	-0.097 85	0.185 952	0.062 50
	-2	-0.047 19	0.180 981	0.030 14
	0	-0.000 73	0.178 416	0.000 51
	2	0.046 34	0.180 368	-0.029 50
	4	0.099 53	0.186 346	-0.063 70
3	-4	-0.098 36	0.185 31	0.061 98
	-2	-0.047 81	0.182 38	0.030 13
	0	-0.000 65	0.181 59	0.000 39
	2	0.046 87	0.183 91	-0.029 23
	4	0.100 03	0.187 78	-0.063 50

a/（°）	标准偏差S/%
a/（°）	C_N	C_A
-4	3.6	2.3
-2	1.6	4.0
0	0.7	4.6
2	1.9	4.8
4	2.5	1.7

α/（°）	C_N	C_A	C_mz
0	-0.267 09	0.338 78	0.200 56
2	-0.025 49	0.321 24	0.039 19
4	0.195 55	0.270 07	-0.113 04
6	0.352 90	0.236 15	-0.220 24

α/（°）	P_cx	P_cy	f_cx	f_cy
-4	0.142 43	-0.084 40	0.025 30	-0.003 18
-2	0.139 22	-0.040 10	0.024 40	-0.001 56
0	0.138 26	0	0.024 10	0
2	0.139 23	0.040 20	0.024 40	0.001 56
4	0.142 45	0.084 50	0.025 30	0.003 19

Microaerodynamic experiment and computation of near space high speed vehicles

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 25

References 24

Related Articles 15

Recommended Articles

Metrics

Comments

α/（°）	P_cx	P_cy	f_cx	f_cy
0	0.068 9	-0.225 51	0.233 931	-0.045
2	0.052 5	-0.084 5	0.219 908	0.025 9
4	0.044 2	0.039 7	0.210 442	0.097 7
6	0.053 2	0.303 829	0.199 762	0.041 9

[1]	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.
[2]	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.
[3]	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.
[4]	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.
[5]	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.
[6]	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.
[7]	Guangjia LI, Hongbo WANG, Kai ZHANG, Zhisheng YI. Lift enhancement and drag reduction technologies of solar powered unmanned aerial vehicles in near space: Review [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(5): 529644-529644.
[8]	Haixing LI, Feng ZHOU, Wei YAN, Feng BAI, Keliang ZHAO. Effects of roughness ice on aerodynamic performance of civil aircraft horizontal tail [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(2): 128657-128657.
[9]	Guiwei ZHANG, Zhaoqing LIU, Lei ZHU, Heng ZHANG, Wei TIAN, Weiguang LI, Zhichun YANG. Research progress of ground flutter simulation test technology [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(10): 29229-029229.
[10]	Lingsong XU, Yuan WU, Dongyu ZHU, Fukun ZHANG, Yu LIU. A wing pitch oscillation mechanism for FL⁃61 icing wind tunnel [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S2): 729296-729296.
[11]	Yu LIU, Mengjie QIN, Qiang WANG, Xian YI. Scaling law for salty sea spray icing wind tunnel test [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S2): 729297-729297.
[12]	Qiuming YANG, Yongfeng ZHU, Huawei CHEN, Xiaolin LIU. Anti-icing performance test investigation on hollowed patterning electric heating module [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S2): 729334-729334.
[13]	Shiqi GAO, Bo DING, Xuzhen XIE, Zheng LI, Lin CHEN, Shouyuan QIAN, Zihan JIAO, Guanghui BAI. Drag reduction mechanism using plasma synthetic jet in high⁃speed flow [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S2): 729373-729373.
[14]	Xianzhong GAO, Xiaolong DENG, Yujie WANG, Zheng GUO, Zhongxi HOU. General planning method for energy optimal flight path of solar⁃powered aircraft in near space [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(8): 27265-027265.
[15]	Xiaolong DENG, Xixiang YANG, Bingjie ZHU, Zhenyu MA, Zhongxi HOU. Simulation research and key technologies analysis of intelligent stratospheric aerostat Loon [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(8): 127412-127412.