Monitoring of compressive behaviour of stiffened composite panels using embedded fibre optic and strain gauge sensors. Issue 1 (6th February 2017)

• Record Type: Journal Article
• Authors: Ruzek, Roman; Kadlec, Martin; Tserpes, Konstantinos; Karachalios, Evaggelos
• Is Part Of: International journal of structural integrity. Volume 8:Issue 1(2017)
• Page Start: 134
• Page End: 150
• Publication Date: 2017-02-06
• Subjects: Sensor -- Composite -- Optical fibre -- Stiffened panel -- Strain gauge -- Structure health monitoring; Structural engineering -- Research -- Periodicals; 620.11205
• DOI: 10.1108/IJSI-11-2015-0052
• Languages: English
• ISSNs: 1757-9864

Abstract

Abstract : Purpose: Compression is critical loading condition for composite airframes. Compression behaviour of structures with or without damages is a weak point for composite fuselage panels. This is one of the reasons for need of continuous in-service health monitoring of composite structures. The purpose of this paper is to characterize the compression panel behaviour on the base of a developed and implemented structural health monitoring (SHM) system. Design/methodology/approach: The SHM system based on fibre optic Bragg grating (FOBG) sensors and standard resistance strain gauges (SGs) was placed onto/into (embedded or bonded) three stiffened carbon fibre reinforced polymer (CFRP) fuselage panels. The FOBG sensor system was used to monitor the structural integrity of the reference, impacted, and fatigued panels under compression loading. Both barely visible impact damage and visible impact damage were created to evaluate their influence on the panel behaviour. The functionality of the SHM system was verified through mechanical testing. Findings: Experimental data showed the presence of impact damages significantly changes the buckling modes development and deformation behaviour of the panels. Some differences between the optical and SG sensors during buckling were observed. The buckling waves and failure development were very well indicated during loading by all sensors located on the panel surface but not by the embedded sensors. Good agreement between the data from the SGs and FOBG sensors was achieved for all sensors placed on the stringers, which did not buckle. The good reliability of FOBG sensors during the fatigue and static testing up to panel failure was verified. Originality/value: The paper gives information about different buckling behaviour of CFRP fuselage stiffened panels in compression. The paper gives detailed information about measured signals from different sensors based on their location on/in the panel structure for realistic loading scenario of composite aerostructures. The paper gives an integrated overview of sensors placement considering possibilities to predicate structure behaviour.