Development of the small satellite “Tsubame”

Toizumi, T.; Enomoto, Takahiro; Yatsu, Yoichi; Nakamori, Takeshi; Kawai, N.; Ishizaka, Kazuya; Muta, Azusa; Morishita, Hiroyuki; Akiyama, Kensuke; Kisa, Nobuhiko; Inagawa, Shinichi; Kawakubo, Manabu; Nishida, Jun‐ichi; Mizunuma, Shintaro; Matsunaga, Saburo; Kataoka, J.

doi:10.1016/j.physe.2010.07.029

Cited by 5 publications

(4 citation statements)

References 8 publications

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“…For this reason, miniature satellites (less than 100 kg) have recently been attracting much interest from the space engineering community for various missions. [17][18][19][20][21] Since miniature satellites could be less costly and developed in a shorter term, they can be manufactured and operated by small organizations, such as universities and small companies. However, because of the limitations of weight, volume, and power, almost all of the miniature satellites do not have any propulsion systems.…”

Section: Introductionmentioning

confidence: 99%

Microfabricated emitter array for an ionic liquid electrospray thruster

Nakagawa

Tsuchiya

Takao

2017

Jpn. J. Appl. Phys.

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We have fabricated needle-shaped emitters on a Si wafer by a MEMS process, and measured the voltage-current characteristics and the frequency dependence of a bipolar pulse voltage for ionic liquid electrospray thrusters, which can be mounted on nanosatellites (≤ ~10 kg). Although the extracted current did not increase with increasing number of emitters, probably owing to the lack of uniformity of the emitters fabricated, we have demonstrated that the emitted current depends on the gap distance between the emitter and the extractor grid electrode, and low frequencies of the bipolar pulse voltage are desirable for thruster operation. Moreover, the Bosch process is required for fabricating a reservoir of ionic liquid, which prevents undesirable

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Section: Introductionmentioning

confidence: 99%

Microfabricated emitter array for an ionic liquid electrospray thruster

Nakagawa

Tsuchiya

Takao

2017

Jpn. J. Appl. Phys.

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“…Control Moment Gyroscope CMG [1][2][3] Single Gimbal Magnetically Suspended CMG SGMSCMG [4] 1~10°/s SGMSCMG PID [5] [6] [4] [7] CMG [8][9][10][11][12] [10] SGMSCMG …”

Section: Imentioning

confidence: 99%

Research on single axis maneuver attitude control of agile small satellite with two parallel mounted SGMSCMGs

Yan

Cui

Zhang

2011

2011 International Conference on Electrical and Control Engineering

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High accuracy and large torque actuators are needed for the agile satellite. Magnetically Suspended Control Moment Gyroscope (MSCMG) has these characters. In addition, it has the advantages of long-life, micro-vibration and non-lubricate, and then is an ideal actuator for agile satellite. However, the stability of the rotor in magnetic bearing and the precision of output torque are affected by the fast slew of satellite and the rotational gimbals. This paper is aimed to meet the demand of the agile small satellite maneuver and attitude control by using two parallel mounted small SGMSCMGs. The effect of whether using limited torque, limited gimbals rate, and the attitude control period on the displacement of rotor and the precision of output torque are analyzed. Simulation results are given to show that, the pitch axis of the satellite has the ability to rotate fifty degrees in ten seconds without destroying the rotor stability.

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“…1) Because nano/microsatellites can be developed quickly and at a low cost, 2) small companies and universities, as well as large companies and government agencies, can make and operate nano/microsatellites. [3][4][5][6][7][8][9][10] These satellites (<100 kg) are now deployed for diverse applications, and advanced missions, such as formation flights and constellations of nano/microsatellites, are now being planned and carried out. [11][12][13] Such nano/microsatellite-based missions require propulsion systems that can be mounted on nano/microsatellites and achieve precise thrust control to maintain the relative positions of a satellite formation.…”

Section: Introductionmentioning

confidence: 99%

Uniform needle-emitter arrays for ionic liquid electrospray thrusters with precise thrust control

Tachibana

Tsuchiya

Takao

2021

Jpn. J. Appl. Phys.

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The development of ionic liquid electrospray thrusters with highly precise needle-emitter arrays is reported. Micro-electro-mechanical systems process technology is applied in the fabrication process of needle-emitter arrays to achieve a uniform shape of emitter tips. The resulting emitter-array chips were then tested to gather the current–voltage characteristics of emitter arrays with different numbers of emitters. The maximum ion current extracted from the emitters increased almost in proportion with the number of emitters. When the current–voltage curves of 81-, 169-, and 361-emitter chips were compared with a constant gap distance between the emitter and extractor electrodes, the onset voltage of ion emission was nearly constant because the emitter tips on all the chips were uniform in shape. Moreover, the current–voltage curves had similar slopes for the different number of emitters after the onset voltage, which demonstrates the uniform ion current output of all the emitter arrays.

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Development of the small satellite “Tsubame”

Cited by 5 publications

References 8 publications

Microfabricated emitter array for an ionic liquid electrospray thruster

Microfabricated emitter array for an ionic liquid electrospray thruster

Research on single axis maneuver attitude control of agile small satellite with two parallel mounted SGMSCMGs

Uniform needle-emitter arrays for ionic liquid electrospray thrusters with precise thrust control

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