Abstract
Global 4-D trajectory (x, y, z, t) is optimized for a spacecraft, which is launched from the Earth to fly around the Sun, just as star-drift of 1437 asteroids in the solar system. The spacecraft trajectory is controlled by low thrust. The performance index of optimal trajectory is to maximize the rendezvous times with the intermediate asteroids, and also maximize the final mass. This paper provides a combined algorithm of global 4-D trajectory optimization. The algorithm is composed of dynamic programming and two-point-boundary algorithm based on optimal control theory. The best 4-D trajectory is obtained: the spacecraft flies passing 55 asteroids, and rendezvous with (following or passing again) asteroids for 454 days, and finally rendezvous with the asteroid 2005SN25 on the day 60521 (MJD), the final mass of the spacecraft is 836.53 kg.
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Nan, Y., Huang, G., Lu, Y. et al. Global 4-D trajectory optimization for spacecraft. Sci. China Technol. Sci. 53, 2097–2101 (2010). https://doi.org/10.1007/s11431-010-3031-7
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DOI: https://doi.org/10.1007/s11431-010-3031-7