Development of 6 U CubeSat’s Deployable Solar Panel with Burn Wire Triggering Holding and Release Mechanism

Park, Tae‐Yong; Chae, Bong-Geon; Oh, Hyun-Ung

doi:10.1155/2019/7346436

Cited by 7 publications

(9 citation statements)

References 9 publications

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“…Considering that changes in the f 0 caused by the HRM are inevitable, the change in the f 0 of 6% measured on the Xand Z-axes is allowable change. However, in the Y-axis test, the f 0 of the DSP along the X-axis was found to decrease by 19.2% from the first LLSS test to the final LLSS test, which is a relatively large decrease compared to those found in other studies [28]. During the test for the Y-axis, the nylon wire of the HRM on the DSP was loosened, and the test was re-executed after repair, inducing a sudden change in f 0 , as shown in Figure 18.…”

Section: Vibration Testingcontrasting

confidence: 65%

“…The f 0 measured in the X-and Y-axis tests was lower than the results of the structural analysis, but that in the Z-axis test was higher than the results of the structural analysis. The constraints of the backlash in the torsional hinge and tightening levels of the nylon wire were not implemented sufficiently in the numerical analysis [28]. To enhance the reliability of the analysis results, the constraint for tightening the nylon wire was considered during pre-processing and verified through the FEA.…”

Section: Vibration Testingmentioning

confidence: 99%

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Novel Structure and Thermal Design and Analysis for CubeSats in Formation Flying

2021

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The CANYVAL-C (CubeSat Astronomy by NASA and Yonsei using a virtual telescope alignment for coronagraph) is a space science demonstration mission that involves taking several images of the solar corona with two CubeSats—1U CubeSat (Timon) and 2U CubeSat (Pumbaa)—in formation flying. In this study, we developed and evaluated structural and thermal designs of the CubeSats Timon and Pumbaa through finite element analyses, considering the nonlinearity effects of the nylon wire of the deployable solar panels installed in Pumbaa. On-orbit thermal analyses were performed with an accurate analytical model for a visible camera on Timon and a micro propulsion system on Pumbaa, which has a narrow operating temperature range. Finally, the analytical models were correlated for enhancing the reliability of the numerical analysis. The test results indicated that the CubeSats are structurally safe with respect to the launch environment and can activate each component under the space thermal environment. The natural frequency of the nylon wire for the deployable solar panels was found to increase significantly as the wire was tightened strongly. The conditions of the thermal vacuum and cycling testing were implemented in the thermal analytical model, which reduced the differences between the analysis and testing.

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Section: Vibration Testingcontrasting

confidence: 65%

Section: Vibration Testingmentioning

confidence: 99%

Novel Structure and Thermal Design and Analysis for CubeSats in Formation Flying

2021

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“…The dynamic deflection of a solar panel under vibration causes stress on the solar cells mounted on the panel by the bounded junction, which could ultimately lead to a crack or fracture in those cells. In the case of previously developed deployable solar panels for CubeSat applications, the mechanical design strategy for the deflection minimization was to increase the panel stiffness by applying additional stiffeners made up of various materials like aluminium, carbon-fiber-reinforced plastic, or fiberglass laminate [11,12]. However, this strategy typically led to an increase in the mass and development cost of the solar panel, which might be disadvantageous for Cube-Sats with an extremely restricted budget.…”

Section: Introductionmentioning

confidence: 99%

CubeSat’s Deployable Solar Panel with Viscoelastic Multilayered Stiffener for Launch Vibration Attenuation

Bhattarai

Kim²,

2020

International Journal of Aerospace Engineering

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Ensuring the structural safety of a deployable solar panel under a severe launch vibration environment is one of the important factors for a successful CubeSat mission. A CubeSat’s deployable solar panel proposed in this study is effective to guarantee the structural safety of solar cells by attenuating launch loads owing to the superior damping characteristic achieved by a multilayered stiffener with viscoelastic acrylic tapes. The demonstration model of 3 U CubeSat’s deployable solar panel was fabricated and tested to validate the effectiveness of the proposed design. The basic dynamic characteristics of the solar panel were measured through free-vibration tests according to the various layers of the stiffener. Moreover, the characteristics of the deployed solar panel were measured and investigated under various temperatures to predict its capability under in-orbit operation. The effectiveness of the proposed design for launch vibration attenuation was demonstrated through qualification level sine and random vibration tests.

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“…Printed circuit board (PCB) substrate-based flight-proven deployable solar panels of various configurations have been produced owing to the advantages of speedy fabrication and easy electrical interconnection with the mounted solar cells. To date, the mechanical design strategies commonly used to minimize panel dynamic deflection under launch vibration loads have increased the solar panel eigenfrequency by including additional stiffeners made up of aluminum or fiberglass-laminate [7,8]. For instance, ISISpace [7] has produced deployable solar panels for 6U CubeSat application, where a thin PCB made up of FR4 material of 0.18 mm thickness is stiffened by an aluminum panel.…”

Section: Introductionmentioning

confidence: 99%

Development of a Novel Deployable Solar Panel and Mechanism for 6U CubeSat of STEP Cube Lab-II

Bhattarai

Kim³

et al. 2021

Aerospace

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The structural safety of solar cells mounted on deployable solar panels in the launch vibration environment is a significant aspect of a successful CubeSat mission. This paper presents a novel highly damped deployable solar panel module that is effective in ensuring structural protection of solar cells under the launch environment by rapidly suppressing the vibrations transmitting through the solar panel by constrained layer damping achieved using printed circuit board (PCB)-based multilayered thin stiffeners with double-sided viscoelastic tapes. A high-damping solar panel demonstration model with a three-pogo pin-based burn wire release mechanism was fabricated and tested for application in the 6U CubeSat “STEP Cube Lab-II” developed by Chosun University, South Korea. The reliable release function and radiation hardness assurance of the mechanism in an in-orbit environment were confirmed by performing solar panel deployment tests and radiation tests, respectively. The design effectiveness and structural safety of the proposed solar panel module were validated by launch vibration and in-orbit environment tests at the qualification level.

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Development of 6 U CubeSat’s Deployable Solar Panel with Burn Wire Triggering Holding and Release Mechanism

Cited by 7 publications

References 9 publications

Novel Structure and Thermal Design and Analysis for CubeSats in Formation Flying

Novel Structure and Thermal Design and Analysis for CubeSats in Formation Flying

CubeSat’s Deployable Solar Panel with Viscoelastic Multilayered Stiffener for Launch Vibration Attenuation

Development of a Novel Deployable Solar Panel and Mechanism for 6U CubeSat of STEP Cube Lab-II

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