An innovative deployable solar panel system for Cubesats

Santoni, Fábio; Piergentili, Fabrizio; Donati, Serena; Perelli, Massimo; Negri, A.; Marino, Michele

doi:10.1016/j.actaastro.2013.11.011

Cited by 64 publications

(32 citation statements)

References 16 publications

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“…[8][9][10][11][12] Because of the volume constraints for launch-vehicle payloads, the size of the rectangular segments are limited. With a more complex folding pattern, we can maximize the available volume in the launch vehicle.…”

Section: Introductionmentioning

confidence: 99%

HanaFlex: a large solar array for space applications

et al. 2015

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HanaFlex is a new method for deployment from a compact folded form to a large array derived from the origami flasher folding pattern. One of the unique features of this model is that the height constraints of the stowed array do not limit the deployed diameter. Additional rings can be added to increase the deployed diameter while only minimally increasing the stowed diameter. Larger solar arrays may enable longer missions in space, manned missions to distant destinations, or clean energy sources for Earth. The novel folding design of the HanaFlex array introduces many new possibilities for space exploration. This paper demonstrates the performance of the HanaFlex array in four areas: deployed stiffness, deployed strength, stowed volume specific power, and mass specific power.

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Section: Introductionmentioning

confidence: 99%

HanaFlex: a large solar array for space applications

et al. 2015

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“…To enhance the capability of a CubeSat, deployable solar panels are required, which would increase the surface area of a CubeSat for the installation of solar cells and would help orient the panels to face perpendicular to the sun for effective power generation. When the sun is orthogonal to the solar panels, the power generation performance would increase 160% to 400% with respect to the bodymounted solar panels [2]. This significantly increases the output power of the solar cells.…”

Section: Introductionmentioning

confidence: 99%

Development of Pogo Pin-Based Holding and Release Mechanism for Deployable Solar Panel of CubeSat

Bhattarai

Kim²,

Jung

et al. 2019

International Journal of Aerospace Engineering

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CubeSats are revolutionary to the space industry and are transforming space exploration which enables the next generation of scientists and engineers to complete all phases of space missions. Deployable solar panels have been widely used for the generation of enough power in CubeSats due to their limited volume area for solar cell integration. In general, the cable cutting release mechanism have been used in 1U-3U small satellites because of its simplicity and low cost. However, this mechanism has a low constraint force and is unable to apply constraints along the in-plane and out-of-plane directions. In this study, for the improvement of the conventional cable cutting mechanism, a spring-loaded pogo pin-based nichrome burn wire holding and release mechanism (HRM) was proposed and fabricated. The pogo pin constitutes an immensely attractive function for the holding and release mechanism of solar panels because it works as an electrical interface to provide power, a separation spring to initiate the reaction force to deploy the panels, and a status switch to determine deployments. In addition, the proposed mechanism guarantees the loading capability along the in-plane and out-of-plane directions of solar panels, the synchronous release of multiple panels, and a handling simplicity that differentiates it from the conventional mechanism. The design feasibility, structural safety, and reliability of the mechanism were verified through functionality tests and launch and on-orbit environmental tests. The proposed pogo pin-based holding and release mechanism would be equally applicable for other CubeSat deployable appendages.

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“…Deployable solar panels on CubeSat can be used to optimize solar power generation and to accomplish specific missions. Many papers about the former application have been published, wherein novel solar panel configurations were designed and solar energy harnessing was studied [2][3][4][5]. For the latter application, in one mission example, the strong atmospheric drag at orbits below 500 km was manipulated to achieve attitude stability [6,7].…”

Section: Introductionmentioning

confidence: 99%

Comparison of Solar Radiation Torque and Power Generation of Deployable Solar Panel Configurations on Nanosatellites

Ibrahim

Yamaguchi

2019

Aerospace

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Nanosatellites, like CubeSat, have begun completing advanced missions that require high power that can be obtained using deployable solar panels. However, a larger solar array area facing the Sun increases the solar radiation torque on the satellite. In this study, we investigated solar radiation torque characteristics resulting from the increased area of solar panels on board the CubeSats. Three common deployable solar panel configurations that are commercially available were introduced and their reference missions were established for the purpose of comparison. The software algorithms used to simulate a variety of orbit scenarios are described in detail and some concerns are highlighted based on the results obtained. The solar power generation of the respective configurations is provided. The findings are useful for nanosatellite developers in predicting the characteristics of solar radiation torques and solar power generation that will be encountered when using various deployable solar panels, thus helping with the selection of a suitable configuration for their design.

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An innovative deployable solar panel system for Cubesats

Cited by 64 publications

References 16 publications

HanaFlex: a large solar array for space applications

HanaFlex: a large solar array for space applications

Development of Pogo Pin-Based Holding and Release Mechanism for Deployable Solar Panel of CubeSat

Comparison of Solar Radiation Torque and Power Generation of Deployable Solar Panel Configurations on Nanosatellites

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