記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.2514/1.B38854

記述言語：英語   掲載種別：研究論文（その他学術会議資料等）  

DOI： 10.1007/978-981-19-2635-8_99

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.1016/j.actaastro.2022.03.016

記述言語：その他   掲載種別：研究論文（その他学術会議資料等）  

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.1016/j.paerosci.2021.100742

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.2514/1.a34584

記述言語：英語   掲載種別：研究論文（学術雑誌）  

DOI： 10.1002/ctpp.201900028

記述言語：英語  

DOI： 10.2514/6.2019-1245

記述言語：英語   掲載種別：研究論文（その他学術会議資料等）  

DOI： 10.1007/978-981-13-3305-7_159

記述言語：英語  

開催年月日： 2023年9月

記述言語：英語  

開催地：Gold Coast, Australia   国名：日本国  

開催年月日： 2023年9月

記述言語：英語  

国名：中華人民共和国  

開催年月日： 2023年9月

記述言語：英語  

開催地：Beppu   国名：日本国  

開催年月日： 2023年9月

記述言語：日本語  

国名：日本国  

開催年月日： 2023年9月

記述言語：英語  

国名：アメリカ合衆国  

開催年月日： 2023年9月

記述言語：日本語  

国名：日本国  

開催年月日： 2022年11月

記述言語：英語  

国名：大韓民国  

開催年月日： 2022年11月

記述言語：英語  

開催地：San Diego   国名：アメリカ合衆国  

Electric Propulsion (EP) is a suitable propulsion technology for satellite and space missions, offering advantages over chemical propulsion in various aspects including fuel consumption hence launch cost. The cusped field thruster(CFT) offers advantages over other types of EP such as the gridded ion thruster and Hall effect thruster, with enhanced electron confinement owing to the magnetic mirror and reduced particle loss effects at the dielectric wall. The increasing demand for performance improvement of the propulsion system while downscaling for micro-satellite class platforms has led to considerable efforts dedicated to physical modeling and performance characterization of downsized CFT. In the present study a multi-objective design optimization (MDO) study has been conducted to characterize the performance to maximize three performance objectives of downscaled CFT, namely, thrust, total efficiency, and specific impulse defined by common design parameters, namely, anode voltage, anode current, mass flow rate and geometric configuration. Particle-in-cell simulations have been performed for the selected design points identified in MD studies for verification by accurately accounting for phenomena and performance losses that originate from uncertainties and complexities associated with the thruster design and physics.

その他リンク： https://arc.aiaa.org/doi/abs/10.2514/6.2019-1245

記述言語：英語  

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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記述言語：英語  

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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