TY - GEN
T1 - Low-Thrust trajectory design and operations of procyon, the first deep-space micro-spacecraft
AU - Campagnola, Stefano
AU - Ozaki, Naoya
AU - Funase, Ryu
AU - Nakasuka, Shinichi
AU - Sugimoto, Yoshihide
AU - Yam, Chit Hong
AU - Kawakatsu, Yasuhiro
AU - Chen, Hongru
AU - Kawabata, Yosuke
AU - Ogura, Satoshi
AU - Sarli, Bruno
N1 - Publisher Copyright:
Copyright © 2015 by the American Institute Federation of Aeronautics and Astronautics. Inc. All rights reserved.
PY - 2015
Y1 - 2015
N2 - PROCYON is the first deep-space micro-spacecraft; it was developed at low cost and short time (about one year) by the University of Tokyo and JAXA, and was launched on December 3rd, 2014 as a secondary payload of the H II A launch of Hayabusa2. The mission primary objective is the technology demonstration of a microspacecraft bus for deepspace exploration; the second objectives are several engineering and science experiments, including an asteroid flyby. This paper presents PROCYON high-fidelity, very-low-Thrust trajectory design and implementation, subject to mission and operation constraints. Contingency plans during the first months of operations are also discussed. All trajectories are optimized in high-fidelity model with jTOP, a mission design tool first presented in this paper. Following the ion engine failure of March 2015, it was found the nominal asteroid could not be targeted if the failure was not resolved by mid-April. A new approach to compute attainable sets for low-Thrust trajectories is also presented.
AB - PROCYON is the first deep-space micro-spacecraft; it was developed at low cost and short time (about one year) by the University of Tokyo and JAXA, and was launched on December 3rd, 2014 as a secondary payload of the H II A launch of Hayabusa2. The mission primary objective is the technology demonstration of a microspacecraft bus for deepspace exploration; the second objectives are several engineering and science experiments, including an asteroid flyby. This paper presents PROCYON high-fidelity, very-low-Thrust trajectory design and implementation, subject to mission and operation constraints. Contingency plans during the first months of operations are also discussed. All trajectories are optimized in high-fidelity model with jTOP, a mission design tool first presented in this paper. Following the ion engine failure of March 2015, it was found the nominal asteroid could not be targeted if the failure was not resolved by mid-April. A new approach to compute attainable sets for low-Thrust trajectories is also presented.
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M3 - Conference contribution
AN - SCOPUS:84991687632
T3 - Proceedings of the International Astronautical Congress, IAC
SP - 5231
EP - 5239
BT - 66th International Astronautical Congress 2015, IAC 2015
PB - International Astronautical Federation, IAF
T2 - 66th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015
Y2 - 12 October 2015 through 16 October 2015
ER -