Direct Two-Impulse Transfers from a Low-Earth Orbit to High Circular Polar Orbits Around the Moon

被引：3

作者：

Tselousova, A. ^{[1
,2
]}

Shirobokov, M. ^{[1
]}

Trofimov, S. ^{[1
]}

机构：

[1] RAS, Keldysh Inst Appl Math, Moscow 125047, Russia

[2] Natl Res Univ, Moscow Inst Phys & Technol, Dolgoprudnyi 141701, Moscow Region, Russia

来源：

XLIII ACADEMIC SPACE CONFERENCE, DEDICATED TO THE MEMORY OF ACADEMICIAN S P KOROLEV AND OTHER OUTSTANDING RUSSIAN SCIENTISTS - PIONEERS OF SPACE EXPLORATION | 2019年 / 2171卷

关键词：

SCIENCE ORBITS; SATELLITES; PERTURBATIONS;

D O I：

10.1063/1.5133289

中图分类号：

P1 [天文学];

学科分类号：

0704 ;

摘要：

The research considers direct two-impulse transfers from a low-Earth orbit to circular polar lunar orbits with an altitude of 10-15 thousand km. Such orbits are candidates for placing a prospective lunar orbital station. A search is made for fast two-impulse transfers that are optimal in terms of delta-v. The calculations are performed in the ephemeris model of motion taking into account gravitational perturbations from the Sun and the Solar System planets according to the JPL DE430 ephemeris, as well as the solar radiation pressure force. The non-spherical gravitational field of the Moon is modeled as a spherical harmonic expansion up to the 8th degree and order based on the GRGM1200A model. A twostage scheme of trajectory optimization is used.

引用

页数：6

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