• Document: The Design of an Efficient, Elegant, and Cubic Pico-Satellite Electronics System
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The Design of an Efficient, Elegant, and Cubic Pico-Satellite Electronics System A Thesis Presented to the Faculty of California Polytechnic State University In Partial Fulfillment of the Requirements for Master of Science in Electrical Engineering By Christopher Alan Day December 2004 AUTHORIZATION FOR REPRODUCTION OF MASTER’S THESIS I grant permission for the reproduction of this thesis in its entirety without further authorization from me. Signature__________________________ Typed Name: Christopher Alan Day Date______________________________ ii APPROVAL PAGE TITLE: The Design of an Efficient, Elegant, and Cubic Pico-Satellite Electronics System AUTHOR: Christopher Alan Day DATE SUBMITTED: 12-10-04 William Ahlgren _________________________ Advisor Signature Taufik_____________________ _________________________ Committee Member Signature Jordi Puig-Suari _________________________ Committee Member Signature Albert A. Liddicoat _________________________ Committee Member Signature iii ABSTRACT The Design and Testing of an Efficient, Elegant, and Cubic Pico-Satellite Electronics System By Christopher Alan Day 1kg satellites, called CubeSats, are small and cheap enough that most universities are able to design and build them as fully functional satellites. Designing satellite systems in this new, small, and light-weight design presents a new challenge to satellite developers. This thesis describes the design of a flexible electronic power system (EPS) and Command and Data Handling (C&DH) system capable of interfacing to many different payloads. The power system is designed to be robust with a fault tolerant architecture. The solar panels are individually peak power tracked for optimal performance and are each fused for short circuit protection. Redundant batteries are used with individual safety circuits so that if either battery has an internal short or open, that battery can be disconnected from the power bus and the other battery can continue to operate normally. The electrical loads are isolated from each other through the use of multiple DC-DC converters and “smart fuses.” The C&DH system is designed with a two wire serial bus that transports critical data between more than 20 devices on the spacecraft. The C&DH processor controls data flow on the bus and is able to isolate bus branches in case a failure prevents bus iv operation. Nine data acquisition circuits throughout the satellite monitor over 70 different sensors giving satellite health and status. By designing circuits that mirror the operation and capability of larger and more complex satellite systems, CubeSats such as this are able to distribute power, communicate with ground stations, and perform scientific missions in much the same way as their larger brethren. The power system and C&DH system described in this thesis has been built into the CubeSat CP2. CP2 has been built and is currently under final testing at Cal Poly. The design modifications listed in chapter 4 of this thesis represent most of the important design modifications on CP2’s electronics at the time this thesis is written. v ACKNOWLEDGMENTS I would like to thank all of the teachers and professors who have instilled in me analytical and creative knowledge. I would like to thank my parents and extended family for raising me into the individual that I am today. Most importantly, I would like to thank the Creator of the electron who has made this work possible and whose name I praise. vi Table of Contents Page List of Figures xi Chapter 1 Introduction

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