Abstract

The paper describes a novel method for the detection of damage in carbon composites as used in drone frames. When damage is detected a further novel corrective response is initiated in the quadcopter flight controller to switch from a four-arm control system to a three-arm control system. This is made possible as a symmetrical frame is utilized, which allows for a balanced weight distribution between both the undamaged quadcopter and the fallback tri-copter layout. The resulting work allows for continued flight where this was not previously possible. Further developing work includes improved flight stability with the aid of an underslung load model. This is beneficial to the quadcopter as a damaged arm attached to the main body by the motor wires behaves as an underslung load. The underslung load works are also transferable in a dual master and slave drone system where the master drone transports a smaller slave drone by a tether, which acts as an underslung load.

Highlights

  • The interest in advances in materials and the development of health monitoring solutions has nowadays gained considerable attention from several researchers

  • Early failure detection methods with critical failure prevention are preferable as they offer a structured approach to resolve failure related issues giving essential early indication of damage and offers options for preventative measures

  • A low cost and minimal overhead approach by flexible design that allows for multiple implementations

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Summary

Introduction

The interest in advances in materials and the development of health monitoring solutions has nowadays gained considerable attention from several researchers (see, for e.g., [1,2]). Early failure detection methods with critical failure prevention are preferable as they offer a structured approach to resolve failure related issues giving essential early indication of damage and offers options for preventative measures. The single drone rotor arm in effect becomes an underslung load; both are covered in the paper as future work will progress to a dual drone system based on a master and slave. Both master and slave drones will incorporate the control system corrective response methods providing an extremely robust and yet minimal complete system

Failure Detection
Control Structure
Wafer Structure
Incorporated Electronic Design
Printed Circuit Board Design
Flight
Development
12. Telemetry flight data of damaged
Conclusions

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