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Related citation:Xiao-Ning Shi,Li-Tao Li,Nai-Gang Cui.Design of Near-optimal Earth Escape Orbits for Solar Sail Spacecraft[J].Journal of Harbin Institute Of Technology(New Series),2013,20(1):12-16.DOI:10.11916/j.issn.1005-9113.2013.01.003.
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Design of Near-optimal Earth Escape Orbits for Solar Sail Spacecraft
Author NameAffiliation
Xiao-Ning Shi Dept. Astronautical Engineering, Harbin Institute of Technology, Harbin 150001,China 
Li-Tao Li Dept. Astronautical Engineering, Harbin Institute of Technology, Harbin 150001,China 
Nai-Gang Cui Dept. Astronautical Engineering, Harbin Institute of Technology, Harbin 150001,China 
Abstract:
With the increase of the interest in solar sailing, it is required to provide a basis for future detailed planetary escape mission analysis by drawing together prior work, clarifying and explaining previously anomalies. In this paper, a technique for escaping the Earth by using a solar sail is developed and numerically simulated. The spacecraft is initially in a geosynchronous transfer orbit (GTO). Blended solar sail analytical control law, explicitly independent of time, are then presented, which provide near-optimal escape trajectories and maintain a safe minimum altitude and which are suitable as a potential autonomous onboard controller. This control law is investigated from a range of initial conditions and is shown to maintain the optimality previously demonstrated by the use of a single-energy gain control law but without the risk of planetary collision. Finally, it is shown that the blending solar sail analytical control law is suitable for solar sail on-board autonomously control system.
Key words:  near-optimal  solar sail  escape trajectory  analytical method  blending control law
DOI：10.11916/j.issn.1005-9113.2013.01.003
Clc Number:V412.4
Fund:

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