Low-altitude, near-polar and near-circular orbits around Europa

被引：32

作者：

Carvalho, J. P. S. ^{[1
,2
]}

Elipe, A. ^{[3
,4
]}

Vilhena de Moraes, R. ^{[1
,2
]}

Prado, A. F. B. A. ^{[5
]}

机构：

[1] Univ Estadual Paulista, UNESP, BR-12516410 Guaratingueta, SP, Brazil

[2] Univ Fed Sao Paulo, Inst Ciencia & Tecnol, UNIFESP, BR-12331280 Sao Jose Dos Campos, SP, Brazil

[3] Univ Zaragoza, IUMA, Ctr Univ Def Zaragoza, E-50009 Zaragoza, Spain

[4] Univ Zaragoza, IUMA, Grp Mecan Espacial, E-50009 Zaragoza, Spain

[5] INPE, Div Space Mech & Control, BR-12227010 Sao Jose Dos Campos, SP, Brazil

来源：

ADVANCES IN SPACE RESEARCH | 2012年 / 49卷 / 05期

基金：

巴西圣保罗研究基金会;

关键词：

Planetary satellites; Artificial satellite; Frozen orbits; ANALYTICAL-MODEL; FROZEN ORBITS; 3RD BODY; LUNAR; PERTURBATION; INCLINATION;

D O I：

10.1016/j.asr.2011.11.036

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The dynamics of orbits around planetary satellites, taking into account the gravitational attraction of a third-body and the non -uniform distribution of mass of the planetary satellite, is studied. The Hamiltonian considered is explicitly time-dependent. Conditions for frozen orbits are presented. Low-altitude, near-polar orbits, very desirable for scientific missions to study planetary satellites such as the Jupiter's moon Europa, are analyzed. Lifetimes for these orbits are computed through the single and double averaged method. Comparison between the results obtained by the single and double averaged method is presented. The single-averaged model is more realistic, since it does not eliminate the term due to the equatorial ellipticity of the planetary satellite as done by the double-averaged problem. Considering the single-averaged method, we found unstable frozen orbits where the satellite does not impact with the surface of Europa for at least 200 days. We present an approach using the unaveraged disturbing potential to analyze the effects of these terms in the amplitude of the eccentricity. (C) 2011 COSPAR. Published by Elsevier Ltd. All rights reserved.

引用

页码：994 / 1006

页数：13

共 35 条

[11] Analytical theory of a lunar artificial satellite with third body perturbations [J].

De Saedeleer, Bernard .

CELESTIAL MECHANICS & DYNAMICAL ASTRONOMY, 2006, 95 (1-4) :407-423

[12]

Domingos RD, 2008, ADV ASTRONAUT SCI, V130, P1571

[13] Frozen orbits about the moon [J].

Elipe, A ;

Lara, M .

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 2003, 26 (02) :238-243

[14] EXTENSION OF THE SOLUTION OF KEPLERS EQUATION TO HIGH ECCENTRICITIES [J].

FERNANDES, SD .

CELESTIAL MECHANICS & DYNAMICAL ASTRONOMY, 1994, 58 (03) :297-308

[15]

Giacaglia G. E. O., 1970, Celestial Mechanics, V3, P3, DOI 10.1007/BF01230432

[16]

Jun-Yong C., 2005, CHIN J GEOPHYS, V48, P303

[17] Recent gravity models as a result of the lunar prospector mission [J].

Konopliv, AS ;

Asmar, SW ;

Carranza, E ;

Sjogren, WL ;

Yuan, DN .

ICARUS, 2001, 150 (01) :1-18

[18]

Kovalevsky J., 1967, INTRO CELESTIAL MECH, P126

[19] SECULAR PERTURBATIONS OF ASTEROIDS WITH HIGH INCLINATION AND ECCENTRICITY [J].

KOZAI, Y .

ASTRONOMICAL JOURNAL, 1962, 67 (09) :591-&

[20]

Kozai Y., 1963, PASJ, V15, P301

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