Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.2514/1.B38854

Language：English   Publishing type：Research paper (other academic)  

DOI： 10.1007/978-981-19-2635-8_99

Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1016/j.actaastro.2022.03.016

Language：Others   Publishing type：Research paper (other academic)  

Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1016/j.paerosci.2021.100742

Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.2514/1.a34584

Language：English   Publishing type：Research paper (scientific journal)  

DOI： 10.1002/ctpp.201900028

Language：English  

DOI： 10.2514/6.2019-1245

Language：English   Publishing type：Research paper (other academic)  

DOI： 10.1007/978-981-13-3305-7_159

Language：English  

Event date： 2023.9

Language：English  

Venue：Gold Coast, Australia   Country：Japan  

Event date： 2023.9

Language：English  

Country：China  

Event date： 2023.9

Language：English  

Venue：Beppu   Country：Japan  

Event date： 2023.9

Language：Japanese  

Country：Japan  

Event date： 2023.9

Language：English  

Country：United States  

Event date： 2023.9

Language：Japanese  

Country：Japan  

Event date： 2022.11

Language：English  

Country：Korea, Republic of  

Event date： 2022.11

Language：English  

Venue：San Diego   Country：United States  

No

Other Link： https://arc.aiaa.org/doi/abs/10.2514/6.2019-1245

Language：English  

Mars exploration is driven by its proximity and scientific goals, such as search for life, studying surface features and planetary evolution as well as preparation for human missions. Designing a spacecraft for sizable payloads to Mars is challenging, especially with chemical propulsion systems that inherently require substantial mass of propellant for trajectory maneuvers. The interdependent subsystems managing mass and power budgets add complexity, which would inevitably need diverse expertise and substantial iterations in conventional design approaches. This intricate interplay significantly complicates spacecraft development. Multidisciplinary system design optimization offers a promising solution to these challenges by simultaneously considering multiple disciplines to achieve an optimal system design, accounting for the interdependencies among various subsystems. This study proposes a multidisciplinary system design optimization approach specifically tailored for interplanetary missions between Earth and Mars. This approach allows for design exploration simultaneously considering subsystems such as trajectory, propulsion, thermal control, attitude control, structure, mass, and power to optimize the overall system performance in terms of required velocity increments and time offlight while maximizing payload mass and fulfilling the requirements of each subsystem.

DOI： 10.2514/6.2025-0771

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Language：English  

Exploring Solar System objects such as planets, moons, and small bodies brings us vital information to unravel the origin of our universe. In such deep-space exploration missions using spacecraft, transporting abundant scientific instruments to the destination is of utmost importance. Generally, however, scientific resources tend to be highly restricted because of other essential components such as bus instruments, structure, and propellant. This paper proposes a design optimization method for interplanetary vehicles with solar electric propulsion, in an attempt to maximize the scientific capability in Solar System explorations. There are innumerable solutions for low-thrust interplanetary trajectories, on which the spacecraft system design problem strongly depends. An infinitely broad solution space must be evaluated extensively so as to determine the optimal system design, which is computationally extremely expensive. To achieve this, we develop a machine-learning model for low-thrust trajectories. A shape-based method is used in order to rapidly generate training trajectory data. The feasibility of the spacecraft components such as power management, communication, and thermal control is evaluated using the predicted trajectory. The developed method allows us to obtain an optimal system design solution that simultaneously maximizes the payload mass and the data downlink rate with the minimal time of flight.

DOI： 10.2514/6.2025-0359

Scopus

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