Analysis on drag characteristics of ultra-low orbit satellite based on DSMC method

被引：0
|
作者：
Hang X. [1 ,2 ]
Li Y. [2 ]
Kong X. [3 ]
Chen Q. [2 ]
Fei Q. [2 ]
机构：
[1] School of Mechanical and Electronic Engineering, Nanjing Forest University, Nanjing
[2] Institute of Aerospace Mechanical Dynamics, Southeast University, Nanjing
[3] Shanghai Institute of Satellite Engineering, Shanghai
来源：
Dongnan Daxue Xuebao (Ziran Kexue Ban)/Journal of Southeast University (Natural Science Edition) | 2023年 / 53卷 / 03期
关键词：
direct simulation Monte Carlo(DSMC)method; drag characteristics; satellite; ultra-low orbit;
D O I：
10.3969/j.issn.1001-0505.2023.03.021
中图分类号：
学科分类号：
摘要：
To provide convincing loads for satellite structural design in engineering, the drag characteristics of a typical ultra-low orbit satellite was studied based on the direct simulation Monte Carlo(DSMC)method by using the model combining Maxwell's diffusion and specular reflection. The effects of the structural mesh density, the satellite nose cone, the slenderness ratio on the drag characteristics were analyzed. The accuracy was verified by comparing the simulation results with the literature results. The results show that the satellite drag is mainly composed of the pressure-difference drag on the inflow projective surface and the tangential frictional drag on the side surfaces of the satellite. For the typical ultra-low orbit satellite studied at the altitude of 268 km, pointed nose cone structures can slightly reduce the drag in flight with the same projective surface area. The drag increases by about 5% to 8% with the slenderness ratio increasing by 1. Changing the angle of attack of all-moving tails can generate the lift force with the lift-drag ratio of 0.10 to 0.34. © 2023 Southeast University. All rights reserved.
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页码：552 / 558
页数：6
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