2015 Fiscal Year Annual Research Report
低推力高効率推進系を用いた複数小惑星フライバイミッションの体系的設計手法
| Project/Area Number |
15J00521
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| Research Institution | Japan Aerospace EXploration Agency |
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Principal Investigator |
VICTORINO SARLI BRUNO 国立研究開発法人宇宙航空研究開発機構, 宇宙科学研究所, 特別研究員(PD)
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| Project Period (FY) |
2015-04-24 – 2017-03-31
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| Keywords | Mission design / Asteriod flyby |
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| Outline of Annual Research Achievements |
This work focuses on the study of multiple asteroid flyby missions developing methods and tools to design deepspace trajectories for these missions based on optimal control. The multiple asteroid flyby trajectory design is challenging in many aspects, but believed to be very relevant and in line with the 2013 Global Exploration Roadmap. In order to achieve the final goal, the research is developed in three large areas of space trajectory, which comprehend the fundamentals of the design used in space missions: trajectory design by ballistic arcs, trajectory design by impulsive maneuvers, and trajectory design by low-thrust maneuvers. In here, the ballistic area is used to identify the problem minimums and as basis for the impulsive area, with and both designing main trajectories that are latter used as reference in the low-thrust area to add a secondary a objective, midcourse flyby, to the mission.
The research is well under way with all the main objectives already completed. Three papers that together describe the research have already been published into peer review journals. With these publications, the full Multiple Asteroid Flyby Mission Design method is complete. The methods and tool developed for multiple flyby mission has already been successful implemented in two JAXA missions: DESTINY+ and the extension plan for Hayabusa 2.
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| Current Status of Research Progress |
Current Status of Research Progress
1: Research has progressed more than it was originally planned.
Reason
Three papers that together describe the research have already been published into peer review journals. With these publications, the full Multiple Asteroid Flyby Mission Design method is complete.
The proposed final step was to develop a high-fidelity model. However, when discussing with specialists in JAXA, it was explained that different research groups have their own high-fidelity simulator, including commercial simulators. Therefore, JAXA specialists advise to refocus the next year's efforts in a very important area: research on how to best deflect a potentially hazardous asteroid via kinetic impactor and NED methods. It is well known that interplanetary designs can often be improved by the use of deep space maneuvers, planetary flybys, and/or low-thrust electric propulsion. However, none of these techniques has yet been applied in this study. This research will be performed in conjunction with the Navigation and Mission Design Branch from NASA Goddard Space Flight Center, as they are the most advanced team in this area.
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| Strategy for Future Research Activity |
Many institutes are currently conducting research on how to best deflect a potentially hazardous asteroid via kinetic impactor and NED methods. All the asteroid deflection works are dependent on the interplanetary trajectory design to reach the asteroid and impart the optimal deflection impulse. To date the trajectory analysis work has been limited to pure ballistic trajectories, i.e. the spacecraft departs from the Earth via a single maneuver provided by the launch vehicle and then coasts to the target. It is well known that interplanetary designs can often be improved by the use of deep space maneuvers (DSMs), planetary flybys, and/or low-thrust electric propulsion. None of these techniques has yet been applied in this study. This research requires to perform an analysis using a advanced trajectory optimization software. In addition, the research will require to directly optimize the performance of a kinetic impactor, that is, making the distance by which the post-deflection asteroid misses the Earth into an objective function which the optimizer can act on directly. These techniques may then be applied to other asteroid case studies.
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Research Products
(6 results)
