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Trajectory optimization for Sun-Earth L5 point missions
Li, Mingtao; Zheng, Jianhua
Department空间技术部
Source PublicationProceedings of the International Astronautical Congress, IAC
2013
Pages5293-5298
Language英语
ISSN0074-1795
ISBN9781629939094
AbstractSun-Earth L5 point is an ideal location to observe the Sun. Spacecraft in the vicinity of Sun-Earth L5 point can provide different perspectives of the Sun than that of near Earth observatories. One satellite of NASA's STEREO mission passed the vicinity of the Sun-Earth L5 point. However, none satellite has been launched into periodic orbit about the Sun-Earth L4/L5 point. This paper studies trajectory optimization for Sun-Earth L5 point missions. Two approaches, the multi-revolution phasing and the invariant manifolds, are used to optimize the transfer trajectory to L5 point. In the multi-revolution phasing approach, satellite is first launched into heliocentric transfer trajectory with semi-major axis a little larger than that of the Earth. Due to the inequality of angular velocity, the phase angle between the Earth and the satellite increases with time. When the phase angle achieves 60 degree after several revolutions, the satellite is injected into the L5 periodic orbit with a tangent maneuver. The tradeoff between transfer time and maneuver velocity is studied. In the invariant manifolds approach, satellite is first transferred to the Sun-Earth L2 point using stable manifolds of Lissajous trajectory. Then the satellite flies to the L5 point to using the unstable manifolds. An injection maneuver is implemented when the satellite arrives at the L5 regions. Three-body transit orbits are used to optimize to the flight time of transfer trajectory. Finally, mission scenarios using both approaches are simulated in high precision dynamical model considering perturbations of planets and the DE 405 ephemeris.
Conference Name64th International Astronautical Congress 2013, IAC 2013
Conference DateSeptember 23, 2013 - September 27, 2013
Conference PlaceBeijing, China
Indexed ByEI
Document Type会议论文
Identifierhttp://ir.nssc.ac.cn/handle/122/4753
Collection空间技术部
Recommended Citation
GB/T 7714
Li, Mingtao,Zheng, Jianhua. Trajectory optimization for Sun-Earth L5 point missions[C]:International Astronautical Federation, IAF,2013:5293-5298.
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