Design of Tokyo Tech nano-satellite Cute-1.7+APD II and its operation

Ashida, Hiroki; Fujihashi, Kota; Inagawa, Shinichi; Miura, Yoshio; Omagari, Kuniyuki; Miyashita, Naoki; Matunaga, Saburo; Toizumi, T.; Kataoka, J.; Kawai, N.

doi:10.1016/j.actaastro.2009.10.035

Cited by 42 publications

(21 citation statements)

References 5 publications

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“…They are considerably smaller than typical commercial satellites, with a volume of 10 cm 3 for a standard size of 1 unit (1U) and a mass of less than 1.33 kg, and they typically use commercial off-the-shelf components [1]. Recently, CubeSats have been advocated for not only by academia [2][3][4] but also by space agencies [5] and industries [6,7] around the world as a means of achieving increasingly complex missions, including scientific, surveillance, and technology demonstration missions. Their advantages include their lower cost, shorter development time, and the opportunity to provide educational experience through hands-on experience.…”

Section: Introductionmentioning

confidence: 99%

Experimental feasibility study of concentrating photovoltaic power system for cubesat applications

Park

2015

IEEE Trans. Aerosp. Electron. Syst.

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The ability to produce sufficient power is an important factor in assuring the success of the challenging and complex cube satellite (CubeSat) missions within an extremely small size. A CubeSat has only a limited surface area on which solar panels can be installed to generate power. The incidence angle of sunlight on the solar panels also varies according to the revolution and rotation of the satellite. These are important parameters for determining the amount of power that a CubeSat can generate. In this study, we propose a concentrating photovoltaic system for CubeSats that enhances the efficiency of power generation by effectively concentrating the solar energy on the solar panels by using a multi-array lens system under the worst condition for sun incidence angle. The feasibility of using the concentrating photovoltaic system for CubeSat applications is demonstrated by power measurement tests using a solar simulator and a commercial multi-array lens under various light source angles.

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Section: Introductionmentioning

confidence: 99%

Experimental feasibility study of concentrating photovoltaic power system for cubesat applications

Park

2015

IEEE Trans. Aerosp. Electron. Syst.

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“…Furthermore, dipoles are straightforward to design and deploy, and designs specific to CubeSats are available commercially. Examples of CubeSats that have flown with dipole antennas include Tokyo Institute of Technology's Cute 1.7+ APD II and California Polytechnic's CP1 (destroyed in launch failure) [2,3].…”

Section: Introductionmentioning

confidence: 99%

Structural Architectures for a Deployable Wideband UHF Antenna

Olson¹,

Pellegrino²,

Costantine³

et al. 2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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9
0

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This paper explores concepts for a wideband deployable antenna suitable for small satellites. The general approach taken was to closely couple antenna theory and structural mechanics, to produce a deployable antenna that is considered efficient in both fields. Approaches that can be deployed using stored elastic strain energy have been favored over those that require powered actuators or environmental effects to enforce deployment. Two types of concepts were developed: thin shell structure and pantograph. These concepts cover four antenna topologies: crossed log periodic, conical log spiral, helical and quadrifilar helix. Of these, the conical log spiral antenna and the accompanying deployment concepts are determined to be the most promising approaches that warrant further study.

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“…For the helical curve defined in Equation 2 with θ 0 = 0, the tangent vector t is given by (6) while the binormal vector b is given by (7) and both are shown in Figure 3. The torsion of the helix is (8) The bending and twisting moments in the initially straight rod are then (9) while the internal force, assuming no stretch in the helix, is (10) and both are uniform along the entire rod.…”

Section: B Analytical Solutions For Helices Made From Straight Rodsmentioning
confidence: 99%

Section: Introductionmentioning
confidence: 99%

Deployable helical antennas for cubesats
Olson
¹
,
Pellegrino
²
,
Banik
³

et al. 2013
54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
16
0
14
0
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This paper explores the behavior of a self-deploying helical pantograph antenna for CubeSats. The helical pantograph concept is described along with concepts for attachment to the satellite bus. Finite element folding simulations of a pantograph consisting of eight helices are presented and compared to compaction force experiments done on a prototype antenna. Reflection coefficient tests are also presented, demonstrating the operating frequency range of the prototype antenna. The helical pantograph is shown to be a promising alternative to current small satellite antenna solutions.

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Design of Tokyo Tech nano-satellite Cute-1.7+APD II and its operation

Cited by 42 publications

References 5 publications

Experimental feasibility study of concentrating photovoltaic power system for cubesat applications

Experimental feasibility study of concentrating photovoltaic power system for cubesat applications

Structural Architectures for a Deployable Wideband UHF Antenna

Deployable helical antennas for cubesats

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