Dual Redundant Flight Control System Design for Microminiature UAV

DOI

10.2991/icecee-15.2015.153How to use a DOI?

Keywords

unmanned aerial vehicle (UAV); flight control; system on a programmable chip (SOPC); fault tolerance.

Abstract

The rigorous requirement for safety, reliability, maintainability, and miniaturization in microminiature unmanned aerial vehicle (UAV) has motivated significant research in new technology. A dual redundant fault-tolerant flight control platform is designed based on the technology of system on a programmable chip (SOPC) and fault tolerance. The scheme of fault-tolerant system is carried out in detail from both hardware and software perspectives. The key technology of the synchronization, fault diagnosis and location, dynamic reconfiguration and isolation is studied in detail. After lots of simulations and experiments, it indicates that the design is reasonable. The platform not only realizes the basic function of the flight control, but also has a high level of integration and flexibility, and can keep safe after a failure.

Copyright

© 2015, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Xiaolin Zhang
AU  - Haisheng Li
AU  - Dandan Yuan
PY  - 2015/06
DA  - 2015/06
TI  - Dual Redundant Flight Control System Design for Microminiature UAV
BT  - Proceedings of the 2015 International Conference on Electrical, Computer Engineering and Electronics
PB  - Atlantis Press
SP  - 785
EP  - 791
SN  - 2352-538X
UR  - https://doi.org/10.2991/icecee-15.2015.153
DO  - 10.2991/icecee-15.2015.153
ID  - Zhang2015/06
ER  -