Development and testing of a modular cubeSat system enabling rapid access to space

Helmich, James A.

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https://hdl.handle.net/2142/129965 Copy

Description

Title

Development and testing of a modular cubeSat system enabling rapid access to space

Author(s)

Helmich, James A.

Issue Date

2025-07-21

Director of Research (if dissertation) or Advisor (if thesis)

Lembeck, Michael F

Department of Study

Aerospace Engineering

Discipline

Aerospace Engineering

Degree Granting Institution

University of Illinois Urbana-Champaign

Degree Name

M.S.

Degree Level

Thesis

Keyword(s)

• CubeSat
• Space Structures
• Small Satellite
• Aerospace
• Systems Engineering
• Structural Analysis
• Qualification Testing
• Responsive Space
• Satellite Bus

Abstract

This thesis presents the development of a modular CubeSat system, herein called CUBE, that provides configurable payload hosting capabilities and promotes rapid access to space. Small satellites are being increasingly utilized to operate civil, defense, commercial, and educational payloads in space. These satellites offer comparatively easy access to space for payload developers. However, current standard program practices are inefficient and create many opportunities for irrecoverable mission failures in the leadup to launch. Each new payload typically requires a bespoke satellite to support it. The assembly, integration, and testing process is highly serialized, leading to schedule delays and late discovery of integration issues. All of this results in large monetary and schedule burdens on any organization wishing to launch a payload. The novel modular system developed for this thesis streamlines the assembly, integration, and testing process by dividing the structure into independent modules that separate the payload from the supporting bus hardware. The bus hardware selected for the system can be used to support a variety of different payloads. Furthermore, the modules can be configured in different orientations to meet the specific needs of a wide range of payloads. This allows the modular system design to be used for multiple missions, removing the need for bespoke satellite design work for each payload. The bus modules can also be flight qualified and prepared in advance, allowing for rapid response missions that can accommodate late payload integration. The versatility of the system is validated with a set of conceptual design reference missions. The design of the structure is then verified by a suite of load analyses. Once verified, a prototype of the structure is manufactured. The structure undergoes a thorough testing campaign to qualify it for spaceflight.

Graduation Semester

2025-08

Type of Resource

Thesis

Handle URL

https://hdl.handle.net/2142/129965

Copyright and License Information

Copyright 2025 James A. Helmich

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