The Experts below are selected from a list of 303 Experts worldwide ranked by ideXlab platform

Yoshitsugu Sone - One of the best experts on this subject based on the ideXlab platform.

  • charge discharge performance of lithium ion Secondary cells under microgravity conditions lessons learned from operation of interplanetary spacecraft hayabusa
    Electrochimica Acta, 2013
    Co-Authors: Yoshitsugu Sone
    Abstract:

    Abstract The Japan Aerospace Exploration Agency (JAXA) is developing a lithium-ion Secondary Battery for deep space missions. Lithium-ion Secondary Battery was first used for the interplanetary spacecraft, Hayabusa. With a view to future long-term operations on the moon and interplanetary travel, the in-orbit performance of the lithium-ion Battery of Hayabusa was examined. The Battery cells maintained a constant performance over 2.7 years of operation as Hayabusa travelled to the asteroid Itokawa. To maintain cell conditions. The state of charge was fixed by using a balance circuit. The cell voltages differed by less than 60 mV during the operation, which is within the error expected based on the circuit design and the telemetry conditions.

  • Charge/discharge performance of lithium-ion Secondary cells under microgravity conditions: Lessons learned from operation of interplanetary spacecraft Hayabusa
    Electrochimica Acta, 2013
    Co-Authors: Yoshitsugu Sone
    Abstract:

    Abstract The Japan Aerospace Exploration Agency (JAXA) is developing a lithium-ion Secondary Battery for deep space missions. Lithium-ion Secondary Battery was first used for the interplanetary spacecraft, Hayabusa. With a view to future long-term operations on the moon and interplanetary travel, the in-orbit performance of the lithium-ion Battery of Hayabusa was examined. The Battery cells maintained a constant performance over 2.7 years of operation as Hayabusa travelled to the asteroid Itokawa. To maintain cell conditions. The state of charge was fixed by using a balance circuit. The cell voltages differed by less than 60 mV during the operation, which is within the error expected based on the circuit design and the telemetry conditions.

  • Storage of a lithium-ion Secondary Battery under micro-gravity conditions
    Journal of Power Sources, 2008
    Co-Authors: Yoshitsugu Sone, Hiroki Ooto, Takashi Eguro, Teiji Yoshida, Masatoshi Uno, Kazuyuki Hirose, Shigeru Sakai, Keiji Takahashi, Masahiro Yamamoto, Michio Tajima
    Abstract:

    'HAYABUSA' is a Japanese inter-planetary spacecraft built for the exploration of an asteroid named 'ITOKAWA.' The spacecraft is powered by a 13.2 Ah lithium-ion Secondary Battery. To realize maximum performance of the Battery for long flight operation, the state-of-charge (SOC) of the Battery was maintained at ca. 65% during storage, in case it is required for a loss of attitude control. The capacity of the Battery was measured during flight operations. Along with the operation in orbit, a ground-test Battery was discharged, and both results showed a good agreement. This result confirmed that the performance of the lithium-ion Secondary Battery stored under micro-gravity conditions is predictable using a ground-test Battery. © 2008.

  • the performance of the lithium ion Secondary cells under micro gravity conditions in orbit operation of the interplanetary spacecraft hayabusa
    Electrochemistry, 2007
    Co-Authors: Yoshitsugu Sone, Hiroki Ooto, Takashi Eguro, Teiji Yoshida, Masatoshi Uno, Shigeru Sakai, Masahiro Yamamoto, Masaaki Kubota, Hiroyuki Yoshida, Kazuyuki Hirose
    Abstract:

    ‘HAYABUSA’ is a Japanese interplanetary spacecraft for the exploration of an asteroid named ‘ITOKAWA.’ The spacecraft is powered by a 13.2 Ah lithium-ion Secondary Battery. To realize maximum performance of the Battery for long flight operation, the state-of-charge (SOC) of the Battery was maintained at ca. 65% during storage in case it is required for contingency operations. To maintain this SOC condition, the Battery is charged once a week. We further charge the Battery up to 4.1 V/cell using bypass circuits to balance the cells every four months. The capacity of the Battery was measured during the flight operation, which revealed the appropriate capacity for the expected mission.

  • The Performance of the Lithium-Ion Secondary Cells under Micro-Gravity Conditions—In-Orbit Operation of the Interplanetary Spacecraft ‘HAYABUSA’
    Electrochemistry, 2007
    Co-Authors: Yoshitsugu Sone, Hiroki Ooto, Takashi Eguro, Teiji Yoshida, Masatoshi Uno, Shigeru Sakai, Masahiro Yamamoto, Masaaki Kubota, Hiroyuki Yoshida, Kazuyuki Hirose
    Abstract:

    ‘HAYABUSA’ is a Japanese interplanetary spacecraft for the exploration of an asteroid named ‘ITOKAWA.’ The spacecraft is powered by a 13.2 Ah lithium-ion Secondary Battery. To realize maximum performance of the Battery for long flight operation, the state-of-charge (SOC) of the Battery was maintained at ca. 65% during storage in case it is required for contingency operations. To maintain this SOC condition, the Battery is charged once a week. We further charge the Battery up to 4.1 V/cell using bypass circuits to balance the cells every four months. The capacity of the Battery was measured during the flight operation, which revealed the appropriate capacity for the expected mission.

Serge Gonzalez - One of the best experts on this subject based on the ideXlab platform.

  • Non-aqueous aluminiumeair Battery based on ionic liquid electrolyte
    Journal of Power Sources, 2014
    Co-Authors: Renaud Revel, Thomas Audichon, Serge Gonzalez
    Abstract:

    A promising metaleair Secondary Battery based on aluminiumeoxygen couple is described. In this paper, we observed that an aluminiumeair Battery employing EMImCl, AlCl3 room temperature ionic liquid (RTIL) as electrolyte and aluminium as negative electrode, has an exceptional reduced self-discharged rate. Due to its new and innovative type of electrolyte, this aluminiumeair Battery can support relatively high current densities (up to 0.6 mA cm-2) and an average voltage of 0.6e0.8 V. Such batteries may find immediate applications, as they can provide an internal, built-in autonomous and self-sustained energy source.

Atsushi Fukunaga - One of the best experts on this subject based on the ideXlab platform.

  • Charge-discharge Performance of an Ionic Liquid-based Sodium Secondary Battery in a Wide Temperature Range
    Electrochemistry, 2015
    Co-Authors: Changsheng Ding, Toshiyuki Nohira, Atsushi Fukunaga, Rika Hagiwara
    Abstract:

    A sodium Secondary Battery has been constructed by using a nonvolatile and nonflammable Na[FSA]-[C(3)C(1)pyrr][FSA] (FSA = bis(fluorosulfonyl)amide, C(3)C(1)pyrr = N-methyl-N-propylpyrrolidinium) ionic liquid, a NaCrO(2) positive electrode and a Na metal negative electrode. The charge-discharge performance is evaluated over a wide temperature range of −20–90℃. It has been demonstrated that the sodium Secondary Battery has long cycle lives both at a high temperature of 90℃ and at a low temperature of 0℃. Thus, the ionic liquid-based sodium Secondary Battery is expected to be a viable alternative to lithium ion Battery for many applications

  • charge discharge behavior of tin negative electrode for a sodium Secondary Battery using intermediate temperature ionic liquid sodium bis fluorosulfonyl amide potassium bis fluorosulfonyl amide
    Journal of Power Sources, 2012
    Co-Authors: Takayuki Yamamoto, Toshiyuki Nohira, Atsushi Fukunaga, Rika Hagiwara, Shoichiro Sakai, Koji Nitta, Shinji Inazawa
    Abstract:

    Abstract The charge–discharge behavior of a Sn negative electrode for use in a sodium Secondary Battery was investigated in an intermediate temperature ionic liquid, NaFSA–KFSA ( x NaFSA  = 0.56, x KFSA  = 0.44, FSA = bis(fluorosulfonyl)amides), at 363 K. A Na/Sn half-cell was prepared using a Sn-film (10–12 μm t ) electrode. The charge–discharge curves at 0.619 mA cm −2 with cut-off voltages of 0.005 and 1.200 V exhibited three potential plateaus in both the charging (alloying) and discharging (de-alloying) processes, indicating the formation of various alloy phases. Charge and discharge capacities as high as 790 and 729 mA h (g-Sn) −1 , respectively, were obtained for the 1st cycle; however, the capacities decreased rapidly due to volume change during the alloying and de-alloying processes. The best cycleability was achieved when the lower and higher cut-off voltages were set to 0.005 and 0.200 V, respectively. In this case, a reversible capacity of about 300 mA h (g-Sn) −1 was obtained for the initial 15 cycles.

Rika Hagiwara - One of the best experts on this subject based on the ideXlab platform.

  • Charge-discharge Performance of an Ionic Liquid-based Sodium Secondary Battery in a Wide Temperature Range
    Electrochemistry, 2015
    Co-Authors: Changsheng Ding, Toshiyuki Nohira, Atsushi Fukunaga, Rika Hagiwara
    Abstract:

    A sodium Secondary Battery has been constructed by using a nonvolatile and nonflammable Na[FSA]-[C(3)C(1)pyrr][FSA] (FSA = bis(fluorosulfonyl)amide, C(3)C(1)pyrr = N-methyl-N-propylpyrrolidinium) ionic liquid, a NaCrO(2) positive electrode and a Na metal negative electrode. The charge-discharge performance is evaluated over a wide temperature range of −20–90℃. It has been demonstrated that the sodium Secondary Battery has long cycle lives both at a high temperature of 90℃ and at a low temperature of 0℃. Thus, the ionic liquid-based sodium Secondary Battery is expected to be a viable alternative to lithium ion Battery for many applications

  • charge discharge behavior of tin negative electrode for a sodium Secondary Battery using intermediate temperature ionic liquid sodium bis fluorosulfonyl amide potassium bis fluorosulfonyl amide
    Journal of Power Sources, 2012
    Co-Authors: Takayuki Yamamoto, Toshiyuki Nohira, Atsushi Fukunaga, Rika Hagiwara, Shoichiro Sakai, Koji Nitta, Shinji Inazawa
    Abstract:

    Abstract The charge–discharge behavior of a Sn negative electrode for use in a sodium Secondary Battery was investigated in an intermediate temperature ionic liquid, NaFSA–KFSA ( x NaFSA  = 0.56, x KFSA  = 0.44, FSA = bis(fluorosulfonyl)amides), at 363 K. A Na/Sn half-cell was prepared using a Sn-film (10–12 μm t ) electrode. The charge–discharge curves at 0.619 mA cm −2 with cut-off voltages of 0.005 and 1.200 V exhibited three potential plateaus in both the charging (alloying) and discharging (de-alloying) processes, indicating the formation of various alloy phases. Charge and discharge capacities as high as 790 and 729 mA h (g-Sn) −1 , respectively, were obtained for the 1st cycle; however, the capacities decreased rapidly due to volume change during the alloying and de-alloying processes. The best cycleability was achieved when the lower and higher cut-off voltages were set to 0.005 and 0.200 V, respectively. In this case, a reversible capacity of about 300 mA h (g-Sn) −1 was obtained for the initial 15 cycles.

Michio Tajima - One of the best experts on this subject based on the ideXlab platform.

  • Storage of a lithium-ion Secondary Battery under micro-gravity conditions
    Journal of Power Sources, 2008
    Co-Authors: Yoshitsugu Sone, Hiroki Ooto, Takashi Eguro, Teiji Yoshida, Masatoshi Uno, Kazuyuki Hirose, Shigeru Sakai, Keiji Takahashi, Masahiro Yamamoto, Michio Tajima
    Abstract:

    'HAYABUSA' is a Japanese inter-planetary spacecraft built for the exploration of an asteroid named 'ITOKAWA.' The spacecraft is powered by a 13.2 Ah lithium-ion Secondary Battery. To realize maximum performance of the Battery for long flight operation, the state-of-charge (SOC) of the Battery was maintained at ca. 65% during storage, in case it is required for a loss of attitude control. The capacity of the Battery was measured during flight operations. Along with the operation in orbit, a ground-test Battery was discharged, and both results showed a good agreement. This result confirmed that the performance of the lithium-ion Secondary Battery stored under micro-gravity conditions is predictable using a ground-test Battery. © 2008.