Experimental Validation of the Structural Integrity of a CFRP Aircraft Fuselage
Fuselage is the main structure of any aerial vehicle—manned or unmanned. Design of aircraft fuselage is a well-established area in the field of aerospace. A composite fuselage has been successfully designed and realized for an aircraft, mainly made of carbon fibre-reinforced plastic (CFRP). The design and manufacturing process of the fuselage demands evaluation by experimental testing. Structural testing of the composite fuselage was carried out simulating the bending moment profile encountered at various conditions of the manoeuvring envelope (V-n diagram). Unlike testing of metallic fuselage, certain specific precautions were considered and implemented during the testing of the composite fuselage. Strains and deflections were measured during all the critical load cases, and the variations of these parameters with the applied loads dictate the evaluation of structural integrity of the composite fuselage.
KeywordsCFRP fuselage Strain gage Experimental validation
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