Implementation of a configurable small satellite design and mission planning tool

Harrigan, Michael

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https://hdl.handle.net/2142/125623 Copy

Description

Title

Implementation of a configurable small satellite design and mission planning tool

Author(s)

Harrigan, Michael

Issue Date

2024-07-17

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 at Urbana-Champaign

Degree Name

M.S.

Degree Level

Thesis

Keyword(s)

• FreeFlyer
• Aerospace Systems Engineering
• Design Optimization
• Satellite
• Small Satellite
• CubeSat
• Mission Planning
• Power System Sizing
• Link Budget
• Power Budget
• Force Modeling
• Data Budget
• LASSI
• Mission Design
• Orbital Simulation

Abstract

This thesis introduces an implementation of a configurable small satellite mission design tool based on a. i. Solutions’ FreeFlyer™ platform. Designing and operating small satellite missions poses significant challenges due to their size and mass constraints. Small satellites have limited resources and constrained capabilities, such as attitude control, power, and communication. Optimizing the performance of these subsystems is crucial for ensuring mission success and maximizing scientific return. To address these challenges, a comprehensive, integrated tool for small satellite mission design and analysis is needed. FreeFlyer™ provides a highly customizable, robust, and reliable framework for orbital performance simulations. A vital feature of the tool is its ability to script adaptive mission plans. The tool supports a wide range of orbit types, propagators, maneuvers, models, and output options for modeling and simulating complex space scenarios. The tool allows users to define and adjust satellite system parameters (e.g., satellite pointing configurations, attitude control devices, solar array and battery sizing, and communications link budgets) in a unified analysis and simulation environment to evaluate the possible trade-offs in performance against resource costs for various design choices. A survey of existing programs and their shortcomings is explored. A description of an improved tool is provided, and examples of its applications demonstrate its effectiveness in optimizing and validating a previously designed small satellite mission. These case studies illustrate the tool’s usefulness in sizing critical mission components and showcase its potential to expedite the small satellite mission design process.

Graduation Semester

2024-08

Type of Resource

Thesis

Handle URL

https://hdl.handle.net/2142/125623

Copyright and License Information

© 2024 Michael Harrigan

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