Up until 2015 the rate at which cube satellite missions achieved full mission success
was only 44.1% for any organizations rst mission (academic or corporate), the success
rate increases to only 62% for cube satellites launched as a second mission. This
thesis suggests that there are two main sources for the high failure rate: improper
veri cation, and the common use of COTS components and their reliability in a
space environment. The thesis provides a means of increasing mission assurance
through the use of physics of failure reliability estimation models that incorporate
the intrinsic and extrinsic failures of thermal mechanical e ects as well as radiation
e ects on EEE components, a design methodology is also presented that incorporates
reliability modeling as well as thorough software and hardware in loop testing to
prevent failure due to improper veri cation. The environment and reliability models
are calculated for the on board command and data handling system of the ECOSat-
II cube satellite being developed by the University of Victoria ECOSat team using
NX Siemens for thermal FEA modelling, SPENVIS for radiation environment, and
MATLAB for reliability calculation. / Graduate / 0544 / 0538 / cass.hussmann@gmail.com
| Identifer | oai:union.ndltd.org:uvic.ca/oai:dspace.library.uvic.ca:1828/7385 |
| Date | 04 July 2016 |
| Creators | Hussmann, Cass Adam |
| Contributors | Suleman, Afzal |
| Source Sets | University of Victoria |
| Language | English, English |
| Detected Language | English |
| Type | Thesis |
| Rights | Available to the World Wide Web, http://creativecommons.org/licenses/by/2.5/ca/ |
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