Impulsive orbit control for spacecraft around asteroid

Hu Tao Cui; Ping Yuan Cui; En Jie Luan

Impulsive orbit control for spacecraft around asteroid

Hu Tao Cui^*
, Ping Yuan Cui
, En Jie Luan

^*Corresponding author for this work

Harbin Institute of Technology
China Natl. Space Admin.

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

1 Citation (Scopus)

Abstract

An impulse feedback control law to change the mean orbit elements of spacecraft around asteroid is presented. First, the mean orbit elements are transferred to the osculating orbit elements at the burning time. Then, the feedback control law based on Gauss's perturbation equations of motion is given. And the impulse control for targeting from the higher circulation orbit to the specified periapsis is developed. Finally, the numerical simulation is performed and the simulation results show that the presented impulse control law is effective.

Original language	English
Pages (from-to)	349-352
Number of pages	4
Journal	Journal of Harbin Institute of Technology (New Series)
Volume	10
Issue number	4
Publication status	Published - Dec 2003
Externally published	Yes

Keywords

Impulse feedback control
Mean orbit elements
Orbit transfer

Cite this

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title = "Impulsive orbit control for spacecraft around asteroid",

abstract = "An impulse feedback control law to change the mean orbit elements of spacecraft around asteroid is presented. First, the mean orbit elements are transferred to the osculating orbit elements at the burning time. Then, the feedback control law based on Gauss's perturbation equations of motion is given. And the impulse control for targeting from the higher circulation orbit to the specified periapsis is developed. Finally, the numerical simulation is performed and the simulation results show that the presented impulse control law is effective.",

keywords = "Impulse feedback control, Mean orbit elements, Orbit transfer",

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

year = "2003",

month = dec,

language = "English",

volume = "10",

pages = "349--352",

journal = "Journal of Harbin Institute of Technology (New Series)",

issn = "1005-9113",

publisher = "Harbin Institute of Technology",

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TY - JOUR

T1 - Impulsive orbit control for spacecraft around asteroid

AU - Cui, Hu Tao

AU - Cui, Ping Yuan

AU - Luan, En Jie

PY - 2003/12

Y1 - 2003/12

N2 - An impulse feedback control law to change the mean orbit elements of spacecraft around asteroid is presented. First, the mean orbit elements are transferred to the osculating orbit elements at the burning time. Then, the feedback control law based on Gauss's perturbation equations of motion is given. And the impulse control for targeting from the higher circulation orbit to the specified periapsis is developed. Finally, the numerical simulation is performed and the simulation results show that the presented impulse control law is effective.

AB - An impulse feedback control law to change the mean orbit elements of spacecraft around asteroid is presented. First, the mean orbit elements are transferred to the osculating orbit elements at the burning time. Then, the feedback control law based on Gauss's perturbation equations of motion is given. And the impulse control for targeting from the higher circulation orbit to the specified periapsis is developed. Finally, the numerical simulation is performed and the simulation results show that the presented impulse control law is effective.

KW - Impulse feedback control

KW - Mean orbit elements

KW - Orbit transfer

UR - https://www.scopus.com/pages/publications/1942508257

M3 - Article

AN - SCOPUS:1942508257

SN - 1005-9113

VL - 10

SP - 349

EP - 352

JO - Journal of Harbin Institute of Technology (New Series)

JF - Journal of Harbin Institute of Technology (New Series)

IS - 4

ER -

Impulsive orbit control for spacecraft around asteroid

Abstract

Keywords

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