Date of Award

3-2024

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

Robert A. Bettinger, PhD

Abstract

The Air Force Institute of Technology (AFIT) has renewed its interest in the area of CubeSat research by performing the preliminary structural design and analysis of a 27U CubeSat. The aim of this research is to shed light on the design process for this CubeSat and highlight design challenges and assumptions. Next, to provide the testing standards as outlined by the NASA General Environmental Verification Standards (GEVS) and present a modal analysis in various configurations of 27U CubeSat using Finite Element Analysis (FEA). The 27U CubeSat was manufactured by machining plates made from aluminum alloy 7075-T6, and validated individual component Finite Element (FE) models using Free-Free Boundary Condition (FFBC) vibration testing. Finally, make recommendations for future 27U CubeSat testing and design improvements. This research provides both a physical and FE model to be used as a springboard for satellite random vibration, low-level sine sweep, and thermal vacuum (TVAC) testing. Ultimately, the impact of this research could eventually provide consumers a CubeSat that has 27 liters of volume, more than double that of the 12U CubeSat, that is better-equipped for missions beyond low Earth Orbit (LEO).

AFIT Designator

AFIT-ENY-MS-24-M-188

Comments

A 12-month embargo was observed for posting this work on AFIT Scholar.

Distribution Statement A, Approved for Public Release. PA case number 88ABW-2024-0312.

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