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Low-thrust trajectory optimization of asteroid sample return mission with multiple revolutions and moon gravity assists

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Abstract

Near-Earth asteroids have gained a lot of interest and the development in low-thrust propulsion technology makes complex deep space exploration missions possible. A mission from low-Earth orbit using low-thrust electric propulsion system to rendezvous with near-Earth asteroid and bring sample back is investigated. By dividing the mission into five segments, the complex mission is solved separately. Then different methods are used to find optimal trajectories for every segment. Multiple revolutions around the Earth and multiple Moon gravity assists are used to decrease the fuel consumption to escape from the Earth. To avoid possible numerical difficulty of indirect methods, a direct method to parameterize the switching moment and direction of thrust vector is proposed. To maximize the mass of sample, optimal control theory and homotopic approach are applied to find the optimal trajectory. Direct methods of finding proper time to brake the spacecraft using Moon gravity assist are also proposed. Practical techniques including both direct and indirect methods are investigated to optimize trajectories for different segments and they can be easily extended to other missions and more precise dynamic model.

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Authors and Affiliations

  1. School of Aerospace Engineering, Tsinghua University, Beijing, 100084, China

    Gao Tang, FanHuag Jiang & JunFeng Li

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  1. Gao Tang
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  2. FanHuag Jiang
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  3. JunFeng Li
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Correspondence to FanHuag Jiang.

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Tang, G., Jiang, F. & Li, J. Low-thrust trajectory optimization of asteroid sample return mission with multiple revolutions and moon gravity assists. Sci. China Phys. Mech. Astron. 58, 114501 (2015). https://doi.org/10.1007/s11433-015-5699-y

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  • DOI: https://doi.org/10.1007/s11433-015-5699-y

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