Difference between revisions of "Projects:2021s1-13001 Improving the Resilience of Autonomous Satellite Networks against High-Energy Disruptions"

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=== Project Objectives ===
 
=== Project Objectives ===
1. To design and develop a novel system architecture to detect and correct single event upsets, and to restore system operation in a failure event.​
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* To design and develop a novel system architecture to detect and correct single event upsets, and to restore system operation in a failure event.​
  
2. To provide sufficient fault protection such that an industry-rated FPGA may be used in space applications for a minimum period of 2 years (in Low Earth Orbit) without loss of functionality. ​
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* To provide sufficient fault protection such that an industry-rated FPGA may be used in space applications for a minimum period of 2 years (in Low Earth Orbit) without loss of functionality. ​
  
3. To provide clearly defined research outcomes which can be incorporated into the development process for future CubeSat launches.​
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* To provide clearly defined research outcomes which can be incorporated into the development process for future CubeSat launches.​
  
 
== Background ==
 
== Background ==

Revision as of 14:59, 13 April 2021

Artist's impression of the Buccaneer Risk Mitigation Mission (BRMM) satellite.

While FPGAs offer a number of benefits for aerospace applications, they are highly susceptible to single event effects (SEE) when exposed to high-radiation environments. These upsets can cause undesirable behaviour within the system, and potentially lead to catastrophic system failure. Students will build upon existing work to develop a novel FPGA configuration scrubber to overcome these effects using an external microcontroller.

Introduction

Project description here

Project team

Project students

  • Jack Nelson
  • Albert Pistorius

Supervisors

  • Dr. Said Al-Sarawi
  • Dr. Dharmapriya Bandara (DST Group)

Advisors

  • Dr. Brayden Phillips

Project Objectives

  • To design and develop a novel system architecture to detect and correct single event upsets, and to restore system operation in a failure event.​
  • To provide sufficient fault protection such that an industry-rated FPGA may be used in space applications for a minimum period of 2 years (in Low Earth Orbit) without loss of functionality. ​
  • To provide clearly defined research outcomes which can be incorporated into the development process for future CubeSat launches.​

Background

Method

Results

Conclusion

References

[1] a, b, c, "Simple page", In Proceedings of the Conference of Simpleness, 2010.

[2] ...