超低轨卫星气动阻力计算与减阻设计研究综述

doi:10.7527/S1000-6893.2023.29796

Abstract

Abstract:

In recent years， Very Low Earth Orbit （VLEO） satellites have become a research hotspot in the field of space technology due to their great advantages in terms of Earth observation resolution， data transfer speed， and communication capacity over traditional satellites. In the VLEO environment， the atmospheric drag caused by collisions between atmospheric molecules and the satellite surface cannot be ignored， and has become not only a critical issue affecting the attitude control and orbit prediction of satellites， but also a key factor limiting the operational life of satellites. This paper starts with the fundamentals of satellite aerodynamic drag and discusses several key factors that determine aerodynamic drag， with a particular focus on the computational analysis of drag coefficients. The gas flow in the VLEO environment belongs to the regime of free molecular flow， where collisions between gas molecules can be neglected. The models for gas-surface interaction between gas molecules and the satellite surface play a crucial role in evaluating the drag coefficient. The fundamental characteristics and common calculation methods for free molecular flow are introduced and evaluated， followed by a focused review of several typical gas-surface interaction models. Furthermore， based on the computational analysis of aerodynamic drag characteristics of satellites， a review of the research progress in drag reduction configuration design is conducted， focusing on three aspects： increasing the aspect ratio， shape optimization， and lateral side smoothing. Finally， several key issues that require significant attention in the future of this field are also discussed.

Key words: Very Low Earth Orbit (VLEO), atmospheric drag, gas-surface interaction, free molecular flow, drag reduction design

CLC Number:

V211.25

Jun ZHANG, Yifan JIANG, Song CHEN, Shuaihui LI. Overview of aerodynamic drag calculation and reduction design for very low Earth orbit satellites[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(21): 29796.

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方法	Panel	RTP	TPMC	DSMC
分子与物面碰撞	√	√	√	√
分子间碰撞				√
表面遮挡		√	√	√
多次反射		√	√	√
计算效率	高	高	较高	低

研究	Park等^［93］	Walsh和 Berthoud^［94］	Yu和Fan^［91］	Walsh等^［95］	Hild等^［96］
头部形状优化	√	√	√	√	√
尾部形状优化		√		√	√
固定体积					√
轨道高度/km	200，300	250	200	200	350
年份	2014	2017	2020	2021	2022

1∶2 shape	Volume		C_D		1∶6 shape	Volume		C_D
1∶2 shape	Value/m³	Precentage reduction/%	Value	Precentage reduction/%	1∶6 shape	Value/m³	Precentage reduction/%	Value	Precentage reduction/%
	0.50	0	2.446	0		0.38	0	2.954	0
	0.45	10	2.168	11.4		0.34	10	2.480	16.0
	0.40	20	2.060	15.8		0.30	20	2.269	23.2
	0.35	30	1.992	18.6		0.26	30	2.114	28.4
	0.30	40	1.945	20.5		0.23	40	1.985	32.8
	0.25	50	1.926	21.2		0.19	50	1.933	34.6

Overview of aerodynamic drag calculation and reduction design for very low Earth orbit satellites

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