Transactions of Nanjing University of Aeronautics & Astronautics
Special Issue for UAV
Experimental Investigation of High Velocity Impact on Ti/CFRP/Ti Sandwich Structure
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Abstract:
Aircraft laminated composite components often suffer a variety of high velocity impacts with large quantity of energy, which usually affects aircraft behavior and would incur component damages, even disastrous consequences. Therefore, one investigates the impact resistance of a new type of composite material, Ti/CFRP/Ti sandwich structure, and launches impact tests by using an air gun test system. Then one acquires the critical breakthrough rate of the structure and analyzes the damages. The results show that the main failure mode of the front titanium sheet is shear plugging and brittle fracture of adhesive layer with fiber breakage, while the back titanium sheet is severely ripped. The rear damage is worse than the front one. Compared with traditional CFRP laminates, the critical breakthrough rate of Ti/CFRP/Ti sandwich structure is improved by 69.9% when suffered the impact of a bearing ball with 2 mm radius.
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This work was funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions.
Clc Number:
CHINA AERO-SCIENCES
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