Abstract
The power-limited solar electric propulsion system is considered more practical in mission design. An accurate mathematical model of the propulsion system, based on experimental data of the power generation system, is used in this paper. An indirect method is used to deal with the time-optimal and fuel-optimal control problems, in which the solar electric propulsion system is described using a finite number of operation points, which are characterized by different pairs of thruster input power. In order to guarantee the integral accuracy for the discrete power-limited problem, a power operation detection technique is embedded in the fourth-order Runge-Kutta algorithm with fixed step. Moreover, the logarithmic homotopy method and normalization technique are employed to overcome the difficulties caused by using indirect methods. Three numerical simulations with actual propulsion systems are given to substantiate the feasibility and efficiency of the proposed method.
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Notes
Data available online at https://ssd.jpl.nasa.gov/dat/ELEMENTS.NUMBR [retrieved 22 February 2017].
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Acknowledgement
This work is supported by the National Natural Science Fund of China (Grants 11672146 and 11572166).
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Chi, Z., Li, H., Jiang, F. et al. Power-limited low-thrust trajectory optimization with operation point detection. Astrophys Space Sci 363, 122 (2018). https://doi.org/10.1007/s10509-018-3344-8
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DOI: https://doi.org/10.1007/s10509-018-3344-8