| Citation: | LU P F，WANG Y，QI Z，et al. Gravity-assist Earth-to-Jupiter transfer trajectories optimization and midcourse correction design in ephemeris model[J]. Journal of Beijing University of Aeronautics and Astronautics，2024，50（11）：3445-3455 （in Chinese） doi: 10.13700/j.bh.1001-5965.2022.0819
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The Jupiter system exploration has important scientific significance and strategic value, and the Earth-to-Jupiter transfer is the key basis for Jupiter system exploration. The optimal design of Earth-to-Jupiter transfer trajectories is carried out using gravity-assist flight technology, and the midcourse correction strategy is designed to reduce orbit errors during actual flight in the high-precision ephemeris model. First, gravity-assist flight sequences were analyzed through the Tisserand graph. Second, in order to maximize the mass of the probe entering the orbit around Jupiter, a nonlinear programming model is established to optimize the planet-assisted transfer trajectories by considering the planetary ephemeris. Then, the midcourse correction strategy is designed to eliminate actual flight errors of the multiple gravity-assist flight trajectories. Finally, with China’s Jupiter system exploration mission as an example, the optimal and suboptimal transfer solutions of various gravity-assist sequences are obtained by considering the capability of the Long March 5 launch vehicle in the launch window between the year 2034 and 2036. The results show that the optimal solution of the Venus-Earth-Earth-assisted transfer can make the mass of the probe entering the target orbit around Jupiter reach
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