Technology demonstration on University of Tokyo's pico-satellite “XI-V” and its effective operation result using ground station network

Funase, Ryu; Takei, Ernesto; Nakamura, Yuya; Nagai, Masaki; Enokuchi, Akito; Yuliang, Cheng; Nakada, Kenji; Nojiri, Yuta; Sasaki, Fumiki; Funane, Tsukasa; Eishima, Takeshi; Nakasuka, Shinichi

doi:10.1016/j.actaastro.2006.12.032

Cited by 25 publications

(8 citation statements)

References 3 publications

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“…A precautionary measure can be taken to save that satellite from such type attacks.WSN can be used as parasitic communication, but according to the rules ITU-R S.524-8 and ITU-R SF.358-5 [3] interference should not take place among the other satellites. Nano and Pico satellite concept has already been introduced to interconnect the satellites and for the inspection of satellite [12]. WSN keeps monitoring the surroundings of satellite just like Pico-Satellite.…”

Section: Space Weaponmentioning

confidence: 99%

Energy Efficient WSN-SAT System for Surveillance of Satellites

Khalil¹,

Abas²,

Rauf³

2015

WSN

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Satellite communication plays a vital role in the arena of telecommunication. The main objective of this manuscript is to examine the threats and problems like space debris, space weather and space weapons that could damage or disable the satellite system. In consequence, we discuss the role of wireless sensor networks (WSN) and nodes in space based technologies. The scope of this paper is to minimize the threats and vulnerabilities to the satellite systems and based on that, design the next generation and state of the art satellite communication system. We proposed the solutions for the vulnerabilities and surveillance of satellite system by integrating the energy efficient and cost effective WSN to the satellite system.

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Section: Space Weaponmentioning

confidence: 99%

Energy Efficient WSN-SAT System for Surveillance of Satellites

Khalil¹,

Abas²,

Rauf³

2015

WSN

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“…Further, the simulated plasma drag force is compared with that of the analytic model in Eqs. (1) and (2), and the validity of the model is examined. Additionally, a parametric study is performed to investigate the effect of θ, n 0 , and M d on the plasma drag force.…”

Section: Introductionmentioning

confidence: 99%

Particle Simulation of Plasma Drag Force Generation in the Magnetic Plasma Deorbit

Kawashima¹,

Bak²,

Matsuzawa³

et al. 2018

Journal of Spacecraft and Rockets

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The magnetic plasma deorbit method has been proposed for micro and nanosatellites in the low earth orbit (LEO). The magnetic plasma deorbit utilizes the plasma drag force generated by the interaction between space plasma and the magnetic field surrounding magnetic torquers (MTQs). In this study, the plasma drag force generated by the magnetic plasma deorbit method is estimated by using a plasma flow simulation based on the fully kinetic model. The dependences of the plasma drag force on the MTQ angle, atmospheric plasma density, and MTQ magnetic moment are investigated. The simulation results show that the structures of the bow shock and magnetosphere are formed in the vicinity of the MTQs. The predicted plasma drag force is 105.2 nN for an MTQ of 10 A m 2 when the MTQ magnetic moment is parallel to the satellite velocity direction. The plasma drag force shows a strong dependence on the magnetic moment angle. In addition, the plasma drag force is proportional to the atmospheric plasma density and the MTQ magnetic moment. Steady drag force generation in the magnetic plasma deorbit is validated, and the sensitivities of the drag force to the relevant parameters are elucidated.

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“…These values of the size and the mass are set by reference to the previously realized satellites. [1][2][3][4] There is little data of the specific heat of satellites. The specific heat of three satellites in Table 1 is set to 688 J/(kg K) in such a way that the temperature of satellites changes more easily than the realized satellites.…”

Section: Introductionmentioning

confidence: 99%

One Nodal Thermal Analysis for Nano and Micro Satellites on Sun-Synchronous and Circular Orbits

Totani

Ogawa

Inoue

et al. 2013

AEROSPACE TECHNOLOGY JAPAN

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One nodal thermal analysis of nano and micro cubic satellites pointing to the Earth on sun-synchronous and circular orbits is carried out. The altitudes of the orbits are from 300 to 1,000 km. The local time of descending node is from 6 to 12. The combinations of the solar absorptivity and the infrared emissivity on the surface of the satellite in which the satellite satisfies the allowable temperature range, from 0 to 40 deg. C., are clarified for each of the above orbits. As the parameter of heat capacity of the satellite over one surface area of the satellite increases, the choice of combinations of the solar absorptivity and the infrared emissivity increases. The number of combinations in the case of the orbits without the shadow region is much larger than that with the shadow region. The number of combinations in the orbits without the shadow region increases with higher altitude and larger projected area with respect to the sun. The number of combinations in the orbits with the shadow region increases with higher altitude, larger projected area and smaller angle of the shadow region.

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Technology demonstration on University of Tokyo's pico-satellite “XI-V” and its effective operation result using ground station network

Cited by 25 publications

References 3 publications

Energy Efficient WSN-SAT System for Surveillance of Satellites

Energy Efficient WSN-SAT System for Surveillance of Satellites

Particle Simulation of Plasma Drag Force Generation in the Magnetic Plasma Deorbit

One Nodal Thermal Analysis for Nano and Micro Satellites on Sun-Synchronous and Circular Orbits

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