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

Bhattarai, Shankar; Go, Ji-Seong; Kim, Hongrae; Oh, Hyun-Ung

doi:10.3390/aerospace8030064

Cited by 11 publications

(2 citation statements)

References 18 publications

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“…Corresponds to parts from the energy infrastructure 3. Improved by[160] 4. Confirmed by[161].5 Partially confirmed by[151,152,156] 6.…”

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confidence: 90%

Renewability and Robustness Analysis and Review for Sustainable-Technology Propulsion Systems in Modern Transportation Infrastructure Administration

Covaci,

Gălătuș,

Petreuș

et al. 2023

Applied Sciences

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Recently, major climate events highlighted the increasing need to use sustainable technologies in the transportation domain. Energy production infrastructure, storage, and propulsion systems still rely on non-sustainable technology for economic growth. Therefore, this study reviews the modern transportation propulsion systems and transportation infrastructure components, describing the possible outcomes for several future directions based on prototypes and study advances. The in-production vehicles were reviewed for providing immediate, robust, and renewable solutions for the existing non-sustainable transportation infrastructure. The study continues with extended-capability vehicles and their limitations and vulnerability based on the current infrastructural circumstances. An alternative energy transfer infrastructure has been concluded to possibly provide the necessary capabilities to approach a neutral carbon footprint and mitigate ongoing climate adverse events. The hypothetical prototype uses distance energy transfer to bypass the described environmental constraints and provide a direction for achieving a possibly sustainable and economically evolving infrastructure.

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“…Corresponds to parts from the energy infrastructure 3. Improved by[160] 4. Confirmed by[161].5 Partially confirmed by[151,152,156] 6.…”

mentioning

confidence: 90%

Renewability and Robustness Analysis and Review for Sustainable-Technology Propulsion Systems in Modern Transportation Infrastructure Administration

Covaci,

Gălătuș,

Petreuș

et al. 2023

Applied Sciences

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“…Perforations were implemented in systems falling in the smaller mass classifications, up to masses of around 30-40 kg. The most well-known small satellite design is the ISO standardized CubeSat Design [31] developed by the California Polytechnic State University (Cal-Poly) [32], in its basic configuration (the so-called 1U design, with a volume of 10 cubic centimeters and a mass of around 1.5 kg) and also its larger configurations (2U, 3U, 6U, and larger) [33,34]. However, a review of past works failed to identify satellite structures falling into higher satellite mass ranges, such as 40 kg and above, that employed the metal perforation technique.…”

Section: Introductionmentioning

confidence: 99%

Modal Analysis of Conceptual Microsatellite Design Employing Perforated Structural Components for Mass Reduction

2022

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Mass reduction is a primary design goal pursued in satellite structural design, since the launch cost is proportional to their total mass. The most common mass reduction method currently employed is to introduce honeycomb structures, with space qualified composite materials as facing materials, into the structural design, especially for satellites with larger masses. However, efficient implementation of these materials requires significant expertise in their design, analysis, and fabrication processes; moreover, the material procurement costs are high, therefore increasing the overall program costs. Thus, the current work proposes a low-cost alternative approach through the design and implementation of geometrically-shaped, parametrically-defined metal perforation patterns, fabricated by standard processes. These patterns included four geometric shapes (diamonds, hexagons, squares, and triangles) implemented onto several components of a structural design for a conceptual satellite, with a parametric design space defined by two scale factors and also two aspect ratio variations. The change in the structure’s fundamental natural frequency, as a result of implementing each pattern shape and parameter variation, was the selection criterion, due to its importance during the launcher selection process. The best pattern from among the four alternatives was then selected, after having validated the computational methodology through implementing experimental modal analysis on a scaled down physical model of a primary load-bearing component of the structural design. From the findings, a significant mass reduction percentage of 23.15%, utilizing the proposed perforation concept, was achieved in the final parametric design iteration relative to the baseline unperforated case while maintaining the same fundamental frequency. Dynamic loading analysis was also conducted, utilizing both the baseline unperforated and the finalized perforated designs, to check its capability to withstand realistic launch loads through applying quasi-static loads. The findings show that the final perforated design outperformed the baseline unperforated design with respect to the maximum displacements, maximum Von Mises stresses, and also the computed margin of safety. With these encouraging outcomes, the perforated design concept proved that it could provide an opportunity to develop low-cost satellite structural designs with reduced mass.

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Solar Panel Deployment Mechanism for Nano-Satellite

Kamboj

Aditya

Srivastava

et al. 2023

Lecture Notes in Electrical Engineering

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

Cited by 11 publications

References 18 publications

Renewability and Robustness Analysis and Review for Sustainable-Technology Propulsion Systems in Modern Transportation Infrastructure Administration

Renewability and Robustness Analysis and Review for Sustainable-Technology Propulsion Systems in Modern Transportation Infrastructure Administration

Modal Analysis of Conceptual Microsatellite Design Employing Perforated Structural Components for Mass Reduction

Solar Panel Deployment Mechanism for Nano-Satellite

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