The MUSES-C mission for the sample and return—its technology development status and readiness

Kawaguchi, Jun’ichiro; Uesugi, Kenjiro; Fujiwara, Akira

doi:10.1016/s0094-5765(02)00146-7

Cited by 45 publications

(20 citation statements)

References 2 publications

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“…Department of Aeronautics and Astronautics, The University of Tokyo, Tokyo, Japan 2) Japan Aerospace Exploration Agency, Sagamihara, Japan (Received June 10th, 2013) Japan Aerospace Exploration Agency (JAXA) are planning an outer solar system exploration and sample return mission from a Jovian Trojan asteroid using a 3000 m 2 solar power sail. The difficulty of this mission is a severe restriction on the weight; only 300 kg is allocated for sampling and returning to Earth.…”

Section: )mentioning

confidence: 99%

“…The sail area is determined to be 3000 m 2 in order to satisfy the electric power supply requirement 1) . Since this spacecraft has the sail and the ion engines, it is considered to be a succession of the world's first asteroid sample return mission HAYABUSA 2) and the world's first solar power sail IKAROS 3) . Main features of this mission are -The world's first sample return mission from a Jovian Trojan asteroid.…”

Section: Introductionmentioning

confidence: 99%

“…, Ryu FUNASE 1) , Osamu MORI 2) , Yoji SHIRASAWA 2) , Go ONO 1) , Taku HAMASAKI 1) , Naohiro HAYASHI 1) , Toshihiro CHUJO 1) , Norizumi MOTOOKA 1) and Keita TANAKA 1)…”

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Mission Analysis of Sample Return from Jovian Trojan Asteroid by Solar Power Sail

Matsumoto

Funase

Mori

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

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Japan Aerospace Exploration Agency (JAXA) are planning an outer solar system exploration and sample return mission from a Jovian Trojan asteroid using a 3000 m 2 solar power sail. The difficulty of this mission is a severe restriction on the weight; only 300 kg is allocated for sampling and returning to Earth. In this weight, fuel for trajectory and attitude control, sampling mechanism, re-entry capsule, and other systems required to return to the Earth are included. In this paper, a preliminary analysis of this sample return mission is conducted. Three scenarios for sampling are proposed; sampling with a 3000 m 2 solar power sail, with a detachable small solar power sail using electric propulsion systems and with a small probe using chemical propulsion systems. The mission analysis shows that the most feasible configuration is to conduct the sampling with the 3000 m 2 solar power sail using an extension mast.

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Section: )mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Mission Analysis of Sample Return from Jovian Trojan Asteroid by Solar Power Sail

Matsumoto

Funase

Mori

et al. 2014

AEROSPACE TECHNOLOGY JAPAN

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“…Other designs are in development or have been proposed as viable concepts. A 1.3 kg wheeled rover, at one time considered a payload for the Hayabusa mission on which MINERVA flew (Kawaguchi et al, 2003;Wilcox, 2000), was proposed with a novel mobility mechanism that also enables ballistic hopping. It further offered a capability to self-right in response to inevitable tumbling during landing from a hop or while traversing the surface at 1.5 mm/sec in low gravity (Tunstel, 1999).…”

Section: Rolling and Hopping Locomotionmentioning

confidence: 99%

Gravity-Independent Locomotion: Dynamics and Position-Based Control of Robots on Asteroid Surfaces

Chacin¹,

Tunstel²

2012

Robotic Systems - Applications, Control and Programming

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“…And it succeeded in rendezvousing with the asteroid "Itokawa" in September 2005 and touching down on it in November 2005 after a 2-year flight. Now, HAYABUSA has already started on its return journey and is running to aim to reach the Earth in June 2010 [4][5][6] . For ion thrusters, the low ionization potential of the propellant is the better propellant, therefore, mercury, xenon, etc., have been used as the propellant.…”

Section: Introductionmentioning

confidence: 99%

Development of a Microwave Discharge Ion Thruster Using Argon

Yamamoto

Miyoshi

Takao

et al. 2009

Trans. JSASS Space Tech. Japan

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Thrust performances in a microwave discharge ion thruster using argon as the propellant were investigated for possibility of alternative propellant of xenon. First, the ion beam currents using a 10 cm class were measured. The ion beam currents with argon propellant are larger than those with xenon propellant at Pi >24 W in the same configuration. The propellant utilization and ion beam production cost are 0.50 and 440 W/A, respectively at 2.45 GHz microwave input power of 37 W and argon gas flow rate of 2.28 sccm. Next the ion beam currents of 2 cm class ion thruster were measured. The optimum mass flow rate is 0.4 sccm, which is larger than that using xenon. This would be due to the smaller ionization cross section and lighter mass than those of xenon. The propellant utilization efficiency and ion beam production cost are 0.73, 750 W/A, respectively at argon mass flow rate of 0.4 sccm and input power of 16 W. This performance of ion thrusters using argon competes against that using xenon.

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The MUSES-C mission for the sample and return—its technology development status and readiness

Cited by 45 publications

References 2 publications

Mission Analysis of Sample Return from Jovian Trojan Asteroid by Solar Power Sail

Mission Analysis of Sample Return from Jovian Trojan Asteroid by Solar Power Sail

Gravity-Independent Locomotion: Dynamics and Position-Based Control of Robots on Asteroid Surfaces

Development of a Microwave Discharge Ion Thruster Using Argon

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