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

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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

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