An orbital design method for satellite formation flying

Autor:	Hai-Ying Cui, Yunfeng Gao, Junfeng Li
Rok vydání:	2006
Předmět:	Physics Orbital elements Orbital speed Mechanical Engineering Orbital eccentricity Frozen orbit Orbital mechanics Specific orbital energy Orbit Mechanics of Materials Control theory Physics::Space Physics Astrophysics::Earth and Planetary Astrophysics Parabolic trajectory
Zdroj:	Journal of Mechanical Science and Technology. 20:177-184
ISSN:	1738-494X
DOI:	10.1007/bf02915818
Popis:	An orbital design method of the formation initialization based on the relative orbital element method is presented. It firstly constructed the relative motion equation of the satellite formation flying in terms of the leader and followers’ orbital elements. Then the equation was simplified when the orbit eccentricity of the leader satellite was small. And according to the satellites’ mission, a general design method for the relative trajectory was proposed. The advantage of this method is that one can get a very simple analytical formula of each follower satellite’s orbital elements when the orbital eccentricity of the leader satellite is zero. The simulation results show that the method is effective.
Databáze:	OpenAIRE
Externí odkaz:	https://explore.openaire.eu/search/publication?articleId=doi_________::99615aa00efadce15bb94a0c3bb4f506 https://doi.org/10.1007/bf02915818 Zobrazit plný text záznamu Full text from SpringerLink