Spacecraft motion analysis about slowly rotating small body

Hu Tao Cui; Xue Yan Shi; Ping Yuan Cui; En Jie Luan

Spacecraft motion analysis about slowly rotating small body

Hu Tao Cui^*
, Xue Yan Shi
, Ping Yuan Cui
, En Jie Luan

^*Corresponding author for this work

School of Astronautics

Harbin Institute of Technology
China Natl. Space Admin.

Research output: Contribution to journal › Article › peer-review

2 Scopus citations

Abstract

The irregular sphere gravitational potential is given based on adapting to a tri-axial ellipsoid model of a small body, and the spacecraft orbital dynamics equation around a small body is established. According to the integral Jacobi constant, the spacecraft zero-velocity curves in the vicinity of the asteroid are described and feasible motion region is analyzed. Limited condition and periapsis radius corresponding to different eccentricity against impact surface are presented. Perturbation solutions of mean orbit elements are used. Effect of asteroid oblateness and ellipticity is analyzed. Lagrange perturbation equations based on mean orbit elements are used, a few partially frozen orbits are given, and the stability of frozen orbits is analyzed.

Original language	English
Pages (from-to)	16-20
Number of pages	5
Journal	Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica
Volume	25
Issue number	1
State	Published - Jan 2004

Keywords

Frozen orbit
Orbit stability
Slowly rotating small body
Zero-velocity curve

Cite this

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title = "Spacecraft motion analysis about slowly rotating small body",

abstract = "The irregular sphere gravitational potential is given based on adapting to a tri-axial ellipsoid model of a small body, and the spacecraft orbital dynamics equation around a small body is established. According to the integral Jacobi constant, the spacecraft zero-velocity curves in the vicinity of the asteroid are described and feasible motion region is analyzed. Limited condition and periapsis radius corresponding to different eccentricity against impact surface are presented. Perturbation solutions of mean orbit elements are used. Effect of asteroid oblateness and ellipticity is analyzed. Lagrange perturbation equations based on mean orbit elements are used, a few partially frozen orbits are given, and the stability of frozen orbits is analyzed.",

keywords = "Frozen orbit, Orbit stability, Slowly rotating small body, Zero-velocity curve",

author = "Cui, \{Hu Tao\} and Shi, \{Xue Yan\} and Cui, \{Ping Yuan\} and Luan, \{En Jie\}",

year = "2004",

month = jan,

language = "英语",

volume = "25",

pages = "16--20",

journal = "Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica",

issn = "1000-6893",

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TY - JOUR

T1 - Spacecraft motion analysis about slowly rotating small body

AU - Cui, Hu Tao

AU - Shi, Xue Yan

AU - Cui, Ping Yuan

AU - Luan, En Jie

PY - 2004/1

Y1 - 2004/1

N2 - The irregular sphere gravitational potential is given based on adapting to a tri-axial ellipsoid model of a small body, and the spacecraft orbital dynamics equation around a small body is established. According to the integral Jacobi constant, the spacecraft zero-velocity curves in the vicinity of the asteroid are described and feasible motion region is analyzed. Limited condition and periapsis radius corresponding to different eccentricity against impact surface are presented. Perturbation solutions of mean orbit elements are used. Effect of asteroid oblateness and ellipticity is analyzed. Lagrange perturbation equations based on mean orbit elements are used, a few partially frozen orbits are given, and the stability of frozen orbits is analyzed.

AB - The irregular sphere gravitational potential is given based on adapting to a tri-axial ellipsoid model of a small body, and the spacecraft orbital dynamics equation around a small body is established. According to the integral Jacobi constant, the spacecraft zero-velocity curves in the vicinity of the asteroid are described and feasible motion region is analyzed. Limited condition and periapsis radius corresponding to different eccentricity against impact surface are presented. Perturbation solutions of mean orbit elements are used. Effect of asteroid oblateness and ellipticity is analyzed. Lagrange perturbation equations based on mean orbit elements are used, a few partially frozen orbits are given, and the stability of frozen orbits is analyzed.

KW - Frozen orbit

KW - Orbit stability

KW - Slowly rotating small body

KW - Zero-velocity curve

UR - https://www.scopus.com/pages/publications/2342534504

M3 - 文章

AN - SCOPUS:2342534504

SN - 1000-6893

VL - 25

SP - 16

EP - 20

JO - Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica

JF - Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica

IS - 1

ER -

Spacecraft motion analysis about slowly rotating small body

Abstract

Keywords

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