超低轨卫星气动阻力特性

doi:10.16183/j.cnki.jsjtu.2021.014

摘要/Abstract

摘要：

以180~300 km超低轨卫星为研究对象,采用自由分子流模拟方法中可准确模拟三维复杂外形的直接模拟蒙特卡洛(DSMC)法研究了典型外形的气动阻力特性.通过不同速度率条件下圆球和平板的理论阻力系数及不同速度率下70° 钝体外形的气动实验数据与DSMC计算结果的比较, 验证了三维DSMC方法对外形和网格的适应性.针对几类典型的卫星外形的阻力特性进行了计算比较,得出压差阻力、剪切阻力、总阻力及无量纲阻力系数随高度和外形的变化特性.超低轨卫星通过外形的优化设计可降低阻力约10%,能够有效改善其在轨运行特性,且可降低对卫星自身相关系统的设计需求.

关键词: 超低轨, 卫星, 气动阻力, 直接模拟蒙特卡洛, 70° 钝体

Abstract:

Taking the 180~300 km ultra-low orbit satellite as the research object, the aerodynamic drag characteristics of the typical shapes were studied by using the direct simulation Monte Carlo (DSMC) method in the free molecular flow simulation method, which can accurately simulate the three-dimensional complex shapes. By comparing the theoretical drag coefficients of spheres and plates at different velocity rates and the aerodynamic experimental data of 70° bluff body shapes at different velocity rates with the DSMC calculation results, the adaptability of the three-dimensional DSMC method to shape and mesh is verified. The drag characteristics of several typical satellite shapes were calculated and compared, and the pressure difference drag, shear drag, total drag and dimensionless drag coefficients with altitude and shape were obtained. The optimized design of the shape of the ultra-low orbit satellite can reduce the drag by about 10%, which can effectively improve its on-orbit operation characteristics and reduce the design requirements of the own related systems of the satellite.

Key words: ultra-low orbit, satellite, aerodynamic drag, direct simulation Monte Carlo (DSMC), 70° blunt cone

中图分类号:

V211

王晓亮, 姚小松, 高爽, 刘国华. 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 Xiaoliang, YAO Xiaosong, GAO Shuang, LIU Guohua. Aerodynamic Drag Characteristics of Ultra-Low Orbit Satellites[J]. Journal of Shanghai Jiao Tong University, 2022, 56(8): 1089-1100.

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不同外形卫星的阻力和阻力系数

外形	体积/m³	侧面积/m²	截面积/m²	压差阻力/N	剪切阻力/N	总阻力/N	体积阻力系数 $C d v$	横截面阻力系数 $C d h$
圆柱	3.926991	15.70796	0.785398	1.25×10^-2	6.98×10^-3	1.95×10^-2	1.01927693	3.2303
八面	3.535534	15.30734	0.707107	1.12×10^-2	6.92×10^-3	1.81×10^-2	1.01422448	3.3288
六面	3.247595	15	0.649519	1.03×10^-2	6.72×10^-3	1.70×10^-2	1.00931267	3.4078
四面	2.5	14.14214	0.5	7.89×10^-3	6.26×10^-3	1.41×10^-2	0.99701373	3.6730

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s	理论阻力系数	大气密度×10¹¹/ (kg·m^-3)	温度T/K	截面积/m²	来流速度/ (m·s^-1)	DSMC 阻力/N	DSMC 阻力系数	误差/%
5	2.3155	3.11	976	0.0314159	3742.732	0.00001510	2.2077845	-4.65
6	2.2521	3.11	976	0.0314159	4491.278	0.00002126	2.1586418	-4.15
7	2.2094	3.11	976	0.0314159	5239.824	0.00002857	2.1312483	-3.54
8	2.1788	3.11	976	0.0314159	5988.371	0.00003692	2.1086354	-3.22
9	2.1559	3.11	976	0.0314159	6736.917	0.00004644	2.0956899	-2.79
10	2.1381	3.11	976	0.0314159	7485.463	0.00005711	2.0875266	-2.37

s	理论阻力系数	温度T/K	截面积/m²	来流速度/(m·s^-1)	DSMC阻力/N	DSMC阻力系数	误差/%
7	2.2736	976	0.04	5239.367901	0.00003693	2.1640565	-4.81806
8	2.2372	976	0.04	5987.849029	0.00004777	2.1431898	-4.20214
10	2.1872	976	0.04	7484.811287	0.00007353	2.1112999	-3.47019

计算参数	参数值
来流速度/(m·s^-1)	1502
马赫数	20.19
温度/K	13.32
大气密度/(kg·m^-3)	1.73×10^-5
气体分子密度/m^-3	3.72×10²⁰
大气压/(N·m^-2)	6.83×10^-2
平均分子自由程/m	1.59×10^-3
努森数	0.03176

迎角/(°)	实验轴向力系数	实验法向力系数	DSMC计算的轴向力系数	DSMC计算的法向力系数	轴向力系数误差/%	法向力系数误差/%
0	1.657000000	0	1.728949582	-0.000761428	4.34216	—
5	1.627769041	0.085193605	1.713213399	0.080889053	5.16964	-5.05270
10	1.613559729	0.149462371	1.687071032	0.153224730	4.46260	2.51726
15	1.567301431	0.212901910	1.639862485	0.227159406	4.51641	6.69674
20	1.530410268	0.292043509	1.576663946	0.302286986	2.51391	3.50752
30	1.402148382	0.435407757	1.421332598	0.457364525	-0.74490	5.04281

s	来流速度/(m·s^-1)	压差阻力/N	剪切阻力/N	总阻力/N	阻力系数
1	748.48	0.000001044	0.000001632	0.000002676	10.514151880
10	7484.8	0.000053760	0.000014030	0.000067790	2.663506561