上层大气层飞行器气动布局优化设计

doi:10.7527/S1000-6893.2024.30164

Abstract

Abstract:

Optimization of the aerodynamic layout of square， hexagonal and circular upper atmosphere aircraft with different cross sections under constant volume was studied by using the test particle Monte Carlo （TPMC） method. The aspect ratio of the aircraft body with the minimum drag force is obtained. Based on this body， the auto-trim aerodynamic layout of the aircraft including the solar cell wing configuration is determined. Finally， the stability of the aircraft is analyzed. The results show that at the upper atmosphere of 250 km， the fraction of friction force in drag of the aircraft body is relatively large， increasing with the increase of the aspect ratio of the aircraft body. When the aspect ratio is 12.98， the total drag of the aircraft body is the smallest. The total drag force coefficient of the aircraft body varies linearly with its aspect ratio under constant volume， while the friction force coefficient and the pressure force coefficient remain constant. In three kinds of cross section shapes mentioned above， the total drag force of the square section is the greatest， followed by that of the hexagon and the circle. For the solar cell wing structure， the wing deflection angles of the aircraft inauto-strim state are 33.8° and 18° for the first solar section deflection configuration （Configuration 1） and the total three solar section deflection configuration （Configuration 2）， respectively. For the aircraft wing in auto-strim state， Configuration 1 is superior when considering the heat dissipation of the aircraft body. Regarding installation deviation， when the center of the aircraft is shifted to the bottom of the aircraft， it is in a statically unstable state， and when the center of mass is shifted to the head of the aircraft， it is in a statically stable state.

Key words: upper atmosphere, aircraft, auto-trim, aerodynamic, layout, static stability

CLC Number:

V411.3

Junhong LI, Fei HUANG, Xuhong JIN, Wenbo MIAO, Xiaoli CHENG. Aerodynamic layout optimization design of upper atmosphere aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(22): 130164.

Figures/Tables 19

Table 1

Fig.1

Table 2

Table 3

Fig.2

Table 4

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Table 5

Table 6

Fig.8

Fig.9

Table 7

Fig.10

Fig.11

Fig.12

References 25

1	MITRA S K. The upper atmosphere［M］. Royal Asiatic Society of Bengal Press， 1990： 1-5.
2	JIN X H， CHENG X L， HUANG Y Q， et al. Numerical analysis of inlet flows at different altitudes in the upper atmosphere［J］. Physics of Fluids， 2023， 35： 093605.
3	靳旭红，程晓丽，沈清，等.吸气式电推进系统进气道气体流动数值分析［J］.中国科学：物理学力学天文学，2024，54（3）： 150-161.
	JIN X H， CHENG X L， SHEN Q， et al. Numerical analysis of inlet flows in an atmosphere-breathing electric propulsion system （in Chinese）. Sci Sin-Phys Mech Astron， 2024， 54（3）： 150-161 （in Chinese）.
4	JIN X H， MIAO W B， CHENG X L， et al. Monte Carlo simulation of inlet flows in atmosphere-breathing electric propulsion［J］. AIAA Journal， 2024， 62（2）： 518-529.
5	周靖云，靳旭红，程晓丽，等. 气固相互作用对吸气式电推进系统进气道性能的影响研究［J］. 清华大学学报， 2024， 64（9）： 1536-1546.
	ZHOU J Y， JIN X H， CHENG X L， et al. Effects of gas-surface interaction on the inlet performance of an atmosphere-breathing electric propulsion system［J］. Journal of Tsinghua University （Sci & Technol）， 2024， 64（9）： 1536-1546 （in Chinese）.
6	沈清，黄飞，程晓丽，等. 飞行器上层大气层空气动力特性探讨［J］. 气体物理， 2021， 6（1）： 1-9.
	SHEN Q， HUANG F， CHENG X L， et al. On characteristics of upper atmosphere aerodynamics of flying vehicles［J］. Physics of Gases， 2021， 6（1）： 1-9 （in Chinese）.
7	OWENS J M ．Precision global strike： Is there a role for the navy conventional trident modification or the air force conventional strike missile： ADA518974 ［R］．Maxwell AFB： Air University， 2008.
8	唐绍峰，张静. 世界主要空天卫星研制情况及未来发展趋势［J］. 国际航空， 2017（466）： 30-37.
	TANG S F， ZHANG J. Development status and trend of the world’s major aerospace vehicles［J］. Space International， 2017（466）： 30-37 （in Chinese）.
9	徐慨，陈霄，董蛟. 国外航天侦察卫星的现状与发展［J］. 信息通信， 2015， 28（3）： 76-79.
	XU K， CHEN X， DONG J. Present situation and development of foreigspace reconnaissance satellite［J］. Changjiang Information & Communications， 2015， 28（3）： 76-79 （in Chinese）.
10	KONOUE K， YAMAKAWA S， IMAMURA S， et al. Development of super low altitude test satellite （SLATS）［C］∥63rd International Astronautical Congress 2012 （IAC 2012）， Naples： 2012.
11	CANUTO E. Drag-free and attitude control for the GOCE satellite［J］. Automatica， 2008， 44（7）： 1766-1780.
12	樊巍. 六连胜！谷神星一号“一箭双星”发射成功［EB/OL］.环球时报-环球网. （2023-07-22）［2024-08-28］. .
	FAN W. Six wins in a row！ Ceres 1” One arrow double star” launch success［EB/OL］. Global Times.（2023-07-22）［2024-08-28］（in Chinese）.
13	付毅飞. 我国超低轨通遥一体星座启动建设2030年将实现300颗组网运行［EB/OL］. （2023-07-12）［2024-08-28］..
	FU Y F. China’s ultra-low orbit remote intefration constellation started construction in 2030 will realize 300 networking operation［EB/OL］. Science and Technology Daily，（2023-07-12）［2024-08-28］. （in Chinese）.
14	WALSH J A， BERTHOUD L. Reducing spacecraft drag in very low earth orbit through shape optimization［C］∥The 7th European Conference for Aeronautics and Aerospace Sciences. Milan： EUCASS， 2017.
15	黄卫东，张育林，分布式卫星轨道构形的大气摄动分析及修正方法［J］. 宇航学报， 2005， 26（5）： 649-652.
	HUANG W D， ZHANG Y L. Analysis of atmospheric perturbation to distributed satellites orbit configuration and its modified method［J］. Journal of Astronautics， 2005， 26（5）： 649-652 （in Chinese）.
16	周伟勇，张育林，刘昆. 超低轨航天器气动力分析与减阻设计［J］. 宇航学报， 2010， 31（2）： 342-348.
	ZHOU W Y， ZHANG Y L， LIU K. Aerodynamics analysis and reduced drag design for the lower LEO spacecraft［J］. Journal of Astronautics， 2010， 31（2）： 342-348 （in Chinese）.
17	范才智，虞绍听. 超低轨道卫星构型参数设计方法： CN113591214B［P］. 2022-08-26.
	FAN C Z， YU S T. Design method of configuration parameters for ultra-low orbit satellite： CN113591214B［P］. 2022-08-26 （in Chinese）.
18	王晓亮，姚小松，高爽，等. 超低轨卫星气动阻力特性［J］. 上海交通大学学报， 2022， 56（8）： 1089-1100.
	WANG X L， YAO X S， GAO S， et al. Aerodynamic drag characteristics of ultra-low orbit satellites［J］. Journal of Shanghai Jiao Tong University， 2022， 56（8）： 1089-1100 （in Chinese）.
19	靳旭红，黄飞，程晓丽，等. 内外流一体化航天器气动特性分析与减阻设计［J］. 宇航学报， 2017， 38（1）： 10-17.
	JIN X H， HUANG F， CHENG X L， et al. Analysis of aerodynamic properties and drag-reduction design for spacecraft with an open orifice［J］. Journal of Astronautics， 2017， 38（1）： 10-17 （in Chinese）.
20	张俊，蒋亦凡，陈松，等.超低轨卫星气动阻力计算与减阻设计研究综述［J］. 航空学报， 2024， 45（20）： 029796.
	ZHANG J， JIANG Y F， CHEN S， et al. Overview of aerodynamic drag calculation and reduction design for Very Low Orbit satellites［J］. Acta Aeronautica et Astronautica Sinica， 2024， 45（20）： 029796 （in Chinese）.
21	靳旭红，黄飞，程晓丽，等. 超低轨航天器气动特性快速预测的试验粒子Monte Carlo方法［J］. 航空学报， 2017， 38（5）： 105-114.
	JIN X H， HUANG F， CHENG X L， et al. Test particle Monte Carlo method for rapid prediction of aerodynamic properties of spacecraft in lower LEO［J］. Acta Aeronautica et Astronautica Sinica， 2017， 38（5）： 105-114 （in Chinese）.
22	靳旭红，黄飞，程晓丽，等. 超低地球轨道卫星大气阻力预测与影响因素分析［J］. 清华大学学报（自然科学版）， 2020， 60（3）： 219-226.
	JIN X H， HUANG F， CHENG X L， et al. Atmospheric drag on satellites flying in lower low-earth orbit［J］. Journal of Tsinghua University （Science and Technology）， 2020， 60（3）： 219-226 （in Chinese）.
23	PICONE J M， HEDIN A E， DROB D P， et al. NRLMSISE-00 empirical model of the atmosphere： statistical comparisons and scientific issues［J］. Journal of Geophysical Research （Space Physics）， 2002， 107（A12）： 1468.
24	FUJITA K， NODA A. Rarefied aerodynamics of a super low altitude test satellite［C］∥ 41st AIAA Thermophysics Conference. Reston： AIAA， 2009.
25	JIANG Y F， ZHANG J， TIAN P， et al. Aerodynamic drag analysis and reduction strategy for satellites in Very Low Earth Orbit［J］. Aerospace Science and Technology， 2023， 132： 108077.

参数	数值
飞行高度h/km	250
来流密度ρ_∞/（kg·m^-3）	1.160 15×10^-10
来流分子量m	19.490 6
来流温度T_∞/K	1 234.78
来流速度u_∞/（m·s^-1）	7 750
壁面温度T_w/K	300
攻角α/（°）	0
侧滑角β/（°）	0

W/m	L/m	Φ/m
0.65	1.4	0.72
0.60	1.6	0.68
0.57	1.8	0.64
0.54	2.0	0.60
0.51	2.2	0.58
0.49	2.4	0.56
0.47	2.6	0.54
0.46	2.8	0.52
0.44	3.0	0.50
0.41	3.5	0.46
0.38	4.0	0.44
0.36	4.5	0.40
0.34	5.0	0.38
0.31	6.0	0.36
0.29	7.0	0.32
0.27	8.0	0.30

AR	F_D/mN	F_Df/mN	F_Dp /mN
1.9	4.040	0.942	3.10
2.35	3.716	1.01	2.71
2.8	3.474	1.06	2.41
3.3	3.291	1.12	2.17
3.8	3.147	1.18	1.97
4.3	3.038	1.23	1.81
4.85	2.948	1.28	1.67
5.45	2.877	1.33	1.55
6.05	2.821	1.38	1.44
7.6	2.728	1.49	1.24
9.3	2.675	1.59	1.08
11.1	2.653	1.69	0.963
12.95	2.651	1.78	0.869
17.05	2.673	1.95	0.723
21.5	2.727	2.11	0.62
26.25	2.797	2.25	0.546

AR	C_D	C_Df	C_Dp
1.9	2.78	0.075	2.13
2.35	2.93	0.075	2.13
2.8	3.08	0.075	2.13
3.3	3.24	0.075	2.13
3.8	3.41	0.075	2.13
4.3	3.59	0.075	2.13
4.85	3.77	0.075	2.13
5.45	3.96	0.075	2.13
6.05	4.16	0.075	2.13
7.6	4.70	0.075	2.13
9.3	5.27	0.075	2.13
11.1	5.88	0.075	2.13
12.95	6.52	0.075	2.14
17.05	7.89	0.075	2.14
21.5	9.39	0.075	2.14
26.25	11.01	0.075	2.15

部件	F_D/mN	F_Df/mN	F_Dp /mN
本体	2.53	1.66	86.7
太阳电池翼	5.66	5.42	24.3
飞行器	8.19	7.08	111.0

Aerodynamic layout optimization design of upper atmosphere aircraft

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 19

References 25

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Haifeng WANG, Kunpeng LIU, Hongxin JIANG, Chenxi DU. Aerodynamic optimization method of propeller multi⁃design points and variable pitch angle strategy [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 528831-528831.
[2]	Dazhi SUN, Xi CHEN, Weicheng BAO, Wei BIAN, Qijun ZHAO. Interferences of high-speed helicopter fuselage on aerodynamic and aeroacoustic source characteristics of propeller [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 529142-529142.
[3]	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.
[4]	Jiaqi LIU, Rongqian CHEN, Jinhua LOU, Xu HAN, Hao WU, Yancheng YOU. Aerodynamic shape optimization of high-speed helicopter rotor airfoil based on deep learning [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 529828-529828.
[5]	Changhao LIU, Yihua CAO, Xiaomeng MEI, Maosheng WANG, Guanglin ZHANG. Transport effectiveness evaluation of high⁃speed helicopters [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 530182-530182.
[6]	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.
[7]	Yubo MENG, Jingwei SHI, Li ZHOU, Yi ZHANG, Zhanxue WANG. Design method for multi-dimensional deflected serpentine nozzle with abnormal exit [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(8): 128930-128930.
[8]	Weikang HUANG, Zhuoran ZHANG, Xingya DA, Peibo YUAN, Huamin GAO. Thermal characteristics of dual drive motors for high speed counter⁃rotating ducted fan [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(8): 129048-129048.
[9]	Hua YANG, Shusheng CHEN, Zhenghong GAO, Quanfeng JIANG, Wei ZHANG. Rotor aerodynamic data fusion based on Bayesian framework [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(8): 128960-128960.
[10]	Yurou DAI, Jian LI, Xiaopeng XUE, Wei RONG. Aerodynamic characteristics of supersonic disk-gap-band parachute with different reefing ways [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(7): 128811-128811.
[11]	Jinzhao DAI, Haixin CHEN. Optimization design method of three⁃dimensional wave cancellation biplane derived by shock⁃wave morphology [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 628942-628942.
[12]	Pengbo SUN, Zhou ZHOU, Xu LI, Kelei WANG. Influence analysis and optimization of distribution-propulsion-wing parameters with target aerodynamic characteristics [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 629368-629368.
[13]	Junfu LI, Qing CHEN, Wei WANG, Zhonghua HAN, Yuting TAN, Yulin DING, Lu XIE, Jianling QIAO, Ke SONG, Junqiang AI. Design of low sonic boom high efficiency layout for advanced supersonic civil aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 629613-629613.
[14]	Shusheng CHEN, Muliang JIA, Yanxu LIU, Zhenghong GAO, Xinghao XIANG. Deformation modes and key technologies of aerodynamic layout design for morphing aircraft: Review [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 629595-629595.
[15]	Shengxiang TONG, Zhiwei SHI, Xi GENG, Lishuang WANG, Zhikun SUN, Qichang CHEN. Combinable samara aircraft and controlled separation technique [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 629590-629590.

布局	S_z/m²	S_y /m²
布局1	10.24	2.0
布局2	10.20	3.34