VELOX-II: Challenges of developing a 6U nanosatellite

International Journal of Aerospace Engineering

Kim²,

2020

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.

Section: Introductionmentioning

confidence: 99%

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

International Journal of Aerospace Engineering

Kim²,

2020

“…Instead, the carbon-fiber-reinforced plastic (CFRP) panel and honeycomb panel are comparatively lightweight and exhibit high rigidity. Lim et al [10] developed deployable solar panels for VELOX-II 6U CubeSat based on an aluminum honeycomb panel instead of the PCB to ensure the stiffness requirement specified by the launch provider. The two deployable solar panels of the VELOX-II could produce a peak power of 40.8 W. The VELOX-II CubeSat deployable solar panel module per unit mass is only 500 g. However, solar panels based on CFRP and honeycomb are relatively thick and expensive.…”

Section: Introductionmentioning

confidence: 99%

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

Kim³

et al. 2021

Aerospace

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.

“…In order to overcome this issue, several mechanical design strategies, such as increasing the eigenfrequency of the solar panel by implementing stiffeners made of aluminum or fiberglass-laminate [15,16], using carbon fiber-reinforced plastic (CFRP) and honeycomb panels, or employing multiple holding and release mechanisms (HRMs) to provide additional mechanical fixation points have been practiced by considering the design specification and mission requirements. However, the implementation of the additional stiffener approach involves a tradeoff between the panel's stiffness and weight, which might be a disadvantage for the CubeSat as it has a restraint mass budget.…”

Section: Introductionmentioning

confidence: 99%

Experimental Validation of a Highly Damped Deployable Solar Panel Module with a Pogo Pin-Based Burn Wire Triggering Release Mechanism

International Journal of Aerospace Engineering

Kim³

et al. 2020

In this present work, a highly damped deployable solar panel module was developed for application in the 3 U CubeSat. The solar panel proposed herein is effective in guaranteeing the structural safety of solar cells under a launch environment owing to the superior damping characteristics achieved using multilayered stiffeners with viscoelastic acrylic tapes. A holding and release action of the solar panel was achieved by a new version of spring-loaded pogo pin-based burn wire triggering mechanism. A demonstration model of high-damping solar panel assembly was fabricated and tested to validate the effectiveness of the design. The holding and release mechanism achieved using a pogo pin was functionally tested through solar panel deployment tests under ambient room temperature and a thermal vacuum environment. The design effectiveness and structural safety of the solar panel module were validated through qualification-level launch and in-orbit environment tests.