Ryerson University Initiatives in Design and Development of Miniature Satellites Including Femto-Satellites
- Paper number
IAC-07-B4.4.02
- Author
Dr. Krishna Kumar, Ryerson University, Canada
- Coauthor
Mike Alger, Ryerson University, Canada
- Coauthor
Geoffrey McVittie, Ryerson University, Canada
- Year
2007
- Abstract
Recently, Ryerson University has started work on design and development of miniature satellites under the author’s supervision. These miniature satellites include 350 gm Can-sized satellite (RyCanSat), 1 kg pico-sized satellite (RyPicosat), and 100 gm femto-sized satellite (RyFemsat). The design of RyCanSat has been completed and it has undergone flight testing using a balloon and a rocket to an altitude of 3000 feet. This satellite won the first prize in the CanSat competition 2006 organised by American Astronatucal Society (AAS), American Institute of Aeronautics and Astronautics (AIAA), National Space Grant Consortia (NSGC), and Universities Space Research Association (USRA). RyPicosat and RyFemsat are in developmental stage. The primary objectives of RyPicosat mission are: (a) test and demonstration of onboard sensors (GPS receiver, sun sensor, rate sensor, magnetometer, onboard camera, temperature sensor), (b) test and demonstration of the flight computer used for RyCanSat, (c) flight qualification and certifications of various vendors’ subsystems including MEMS based sensors (MEMS based rate sensor, sun sensor, temperature sensor, and others), (d) test design methodology for the development of cost-effective modular Picosatellites, and (e) test passive attitude stabilization using permanent magnet. RyFemsat is designed to be no bigger than a typical cell phone and it carries its own battery and charging circuit. This satellite is proposed for Ryerson femto formation flying experiment (RyF3ex) missions: RyF3ex-1 mission consists of two tethered femtosatellites while RyF3ex-2 mission involves a formation of multiple femto-satellites. The first mission will carry simple attitude sensors as payload and will serve to prove the viability of the data link to the ground. The main mission objectives are: (a) test command and control architecture and hardware, (b) formation keeping and reconfiguration control algorithms, (c) communications protocol and data relay, and (d) imaging of the Earth’s surface. The paper will present in detail about the design and development of miniature satellites including formation flying mission. Furthermore, limitations of these satellites in comparison to their large counterparts will be discussed. Finally, checklists and documentation that have been prepared for successful design of satellites will be explained.
- Abstract document
- Manuscript document
IAC-07-B4.4.02.pdf (🔒 authorized access only).
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