Gravity-assist Earth-to-Jupiter transfer trajectories optimization and midcourse correction design in ephemeris model

LU Pengfei; WANG Yue; QI Zheng; LIU Jianhui

doi:10.13700/j.bh.1001-5965.2022.0819

Volume 50 Issue 11

Nov. 2024

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Journal of Beijing University of Aeronautics and Astronautics > 2024 > 50(11): 3445-3455.

Wu Hong, Li Qiushi, Guo Ming, et al. Aerodynamic optimization method of transonic fan rotor based on BVF[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(01): 14-17. (in Chinese)

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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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Gravity-assist Earth-to-Jupiter transfer trajectories optimization and midcourse correction design in ephemeris model

doi: 10.13700/j.bh.1001-5965.2022.0819

LU Pengfei¹,
WANG Yue^{1
,
,},
QI Zheng^{1, 2},
LIU Jianhui²

1.
School of Astronautics，Beihang University，Beijing 100191，China
2.
Science and Technology on Space Physics Laboratory，Beijing 100076，China

Funds: National Natural Science Foundation of China (11872007)；The Fundamental Research Funds for the Central Universities

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Corresponding author: E-mail：ywang@buaa.edu.cn
Received Date: 29 Sep 2022
Accepted Date: 09 Nov 2022

Available Online: 25 Nov 2022

Publish Date: 23 Nov 2022

Abstract

Abstract

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 4340.8 kg, which is about 1300 kg higher than that of the Hohmann transfer. Monte-Carlo simulations validate the midcourse correction strategy in the ephemeris model. The results show that under various errors, the final B-plane miss distances are less than 50 km, and the correction pulse consumption is small, which proves that the designed gravity-assist transfer trajectories and midcourse correction strategy can realize the Earth-to-Jupiter transfer mission in the high-precision mechanical environment and can provide a reference for the design of China’s Jupiter system exploration mission.
- Earth-to-Jupiter transfer,
- ephemeris model,
- gravity-assist flight,
- trajectories optimization,
- midcourse correction,
- Monte-Carlo simulation

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References

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Gravity-assist Earth-to-Jupiter transfer trajectories optimization and midcourse correction design in ephemeris model

doi: 10.13700/j.bh.1001-5965.2022.0819

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Gravity-assist Earth-to-Jupiter transfer trajectories optimization and midcourse correction design in ephemeris model

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