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CubeSat satellites are used extensively to perform inexpensive space missions and technology tests due to their compact sizes. Structural integrity during launch operation, which is characterized by extreme mechanical loading, is essential to ensure successful CubeSat missions. In this work, the structural integrity of a 1U CubeSat satellite frame (100 mm × 100 mm × 100 mm) was analyzed and validated numerically using finite element method. The findings were compared to previous CubeSat studies to prove the numerical reliability. The CubeSat satellite structure was modeled in three dimensions using the software package ANSYS Mechanical, material properties of aluminum alloy were applied, and load of acceleration was imposed under the condition of fixing its base surface, simulating the deployment process. Numerical results revealed maximal displacement value of 2.474 × 10⁻⁶ m and a value of maximum von-Mises stress of 0.556 MPa, which both fall well below the material strength values. Mesh independence analysis was carried out in order to confirm the numerical stability of results.
"Structural Analysis and Validation of a 1U CubeSat Frame Using Finite Element Analysis", International Journal for Research Trends and Innovation (www.ijrti.org), ISSN:2456-3315, Vol.11, Issue 4, page no.a129-a137, April-2026, Available :http://www.ijrti.org/papers/IJRTI2604017.pdf
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2456-3315 | IMPACT FACTOR: 8.14 Calculated By Google Scholar| ESTD YEAR: 2016
An International Scholarly Open Access Journal, Peer-Reviewed, Refereed Journal Impact Factor 8.14 Calculate by Google Scholar and Semantic Scholar | AI-Powered Research Tool, Multidisciplinary, Monthly, Multilanguage Journal Indexing in All Major Database & Metadata, Citation Generator