Optimization of Low-Thrust Trajectories Using an Indirect Shooting Method without Guesses of Initial Costates |
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| Authors: | Lin Hou-yuan Zhao Chang-yin |
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| Institution: | 1. Purple Mountain Observatory, Chinese Academy of Sciences, Nanjing 210008;2. Key Laboratory of Space Object & Debris Observation, Chinese Academy of Sciences, Nanjing 210008;3. Graduate University of Chinese Academy of Sciences, Beijing 100049 |
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| Abstract: | According to the optimal control theory, the optimal control problem of the low-thrust tra jectory can be converted into a solution of nonlinear two- point boundary-value problem (TPBVP). To solve the TPBVP, the repeated random guesses for the initial costate variables and iterative computations are needed. In order to enhance the convergence of the iterations, we select an appropriate performance index, and then linearize the equations of the TPBVP around a Keplerian orbit. For multi-revolution transfers, instead of the multi- revolution Lambert tra jectory, multiple segmented Keplerian arcs are used to ensure the effectiveness of the linearization. The method is totally automatic with multiple iterations. With this method, we can get the results within 3 ∼ 5 iterations, and the random guess of the initial costates is unnecessary. Finally by the iterative optimization of the performance index, a better control strategy approaching to the bang-bang control is obtained. |
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| Keywords: | Celestial mechanics Space vehicles Methods: numerical |
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