超低地球轨道卫星大气阻力预测与影响因素分析

靳旭红; 黄飞; 程晓丽; 王强; 王兵

doi:10.16511/j.cnki.qhdxxb.2019.26.030

清华大学学报（自然科学版） >

2020 , Vol. 60 >Issue 3: 219 - 226

DOI: https://doi.org/10.16511/j.cnki.qhdxxb.2019.26.030

专题：航空航天与工程力学

超低地球轨道卫星大气阻力预测与影响因素分析

靳旭红 ,
黄飞 ,
程晓丽 ,
王强 ,
王兵

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1. 中国航天空气动力技术研究院, 北京 100074;
2. 清华大学航天航空学院, 北京 100084

收稿日期: 2019-02-24

网络出版日期: 2020-03-03

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Atmospheric drag on satellites flying in lower low-earth orbit

JIN Xuhong ,
HUANG Fei ,
CHENG Xiaoli ,
WANG Qiang ,
WANG Bing

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1. China Academy of Aerospace Aerodynamics, Beijing 100074, China;
2. School of Aerospace Engineering, Tsinghua University, Beijing 100084, China

Received date: 2019-02-24

Online published: 2020-03-03

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摘要

为了对超低地球轨道卫星的大气阻力进行有效预测和分析，该文基于自由分子流试验粒子Monte Carlo方法，通过嵌入多种国际主流大气模型，开发了一套低地球轨道任意复杂外形航天器气动特性预测的通用三维并行软件，并以GOCE卫星为研究对象，计算并分析了该卫星的大气阻力特性，研究了大气模型参数、飞行高度、轨道纬度和经度等因素对大气阻力的影响规律。结果表明：随着高度的增加，阻力急剧减小，阻力系数却单调增大，卫星阻力的预测对大气模型的敏感性增强；轨道纬度和经度变化的影响主要体现在通过影响来流大气参数而间接影响阻力系数和卫星阻力，大气温度和组分影响阻力系数，而阻力系数和来流大气密度共同决定卫星阻力；随着轨道纬度和经度的变化，卫星阻力和阻力系数均呈现非单调的波动性变化。研究表明：JB2008和DTM-2013大气模型表现相近，而USSA-1976、Jacchia-1977和NRLMSISE-00大气模型计算出的阻力都较前两者偏高。

关键词： 低轨卫星; 大气密度模型; 轨道纬度; 轨道经度

本文引用格式

靳旭红 , 黄飞 , 程晓丽 , 王强 , 王兵 . 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 . DOI: 10.16511/j.cnki.qhdxxb.2019.26.030

Abstract

The test particle Monte Carlo method for flow in the free-molecular flow regime was integrated with various state-of-the-art atmospheric models in a general, three-dimensional code to calculate the atmospheric drag for user-defined spacecraft geometries of arbitrary complexity. Then, the code was applied to the geodetic GOCE satellite to evaluate the effects of flight altitude, orbit latitude and orbit longitude on the atmospheric drag to assess the sensitivity of the satellite drag on the atmospheric model. The results show that increasing the satellite height significantly reduces the atmospheric drag while increasing the drag coefficient. The results also illustrate the sensitivity of the satellite drag prediction to the atmospheric model. The orbit latitude and longitude affect the drag coefficients and the satellite drag indirectly by changing the atmospheric temperature and the molecular mass since the satellite drag is determined by the drag coefficient and the atmospheric density. Both the satellite drag and the drag coefficients are nonlinear functions of the orbit latitude and longitude. For the conditions considered here, two newer atmospheric models, JB2008 and DTM-2013, predict similar satellite drag forces with three older models, USSA-1976, Jacchia-1977 and NRLMSISE-00, yielding comparable but somewhat larger drag predictions.

Key words： satellites in low-earth orbit; atmospheric density model; orbit latitude; orbit longitude

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