Chinese Space Science and Technology ›› 2019, Vol. 39 ›› Issue (6): 47-.doi: 10.16708/j.cnki.1000-758X.2019.0049
CHEN Jizheng, SUN Songtao, FENG Gang, XIAO Yuzhi
A method of fast launching and positioning for GEO satellites is proposed. After the satellite is launched into the GTO orbit, it is maneuvered into any designated position in the GEO orbit by the upper stage or by itself within 48 hours. Considering the constraints of time and TeleTracking & Controlling, the nominal trajectory of fast positioning is optimized for minimizing fuel consumption. Based on the nonsingular Equinoctial orbital elements, an explicit guidance is proposed for spacecraft maneuvering and positioning with finite thrust. The simulation shows that the fast launching and positioning control of GEO satellite can be achieved by using the proposed maneuvering strategy, trajectory optimization method and guidance law.
fast launching and positioning,
equinoctial orbital element,
flight dynamics and control
CHEN Jizheng, SUN Songtao, FENG Gang, XIAO Yuzhi. Control method of fast launching and positioning for geostationary satellites#br#[J]. Chinese Space Science and Technology, 2019, 39(6): 47-.
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