Validation of VARTM patch repair for composite structures
Abstract
The United States Marine Corps (USMC) awarded Sikorsky Aircraft with a contract to develop a heavy-lift helicopter successor to the CH-53E in April 2006. The successor has been designated as the CH-53K Super Stallion and represents substantial design revision that incorporates extensive use of carbon fiber composites and titanium resulting in a vast increase in operational capability and a doubling of the lift capacity of the CH-53E. Upon introduction it will be the largest rotary wing aircraft in the United States Department of Defense (USDOD). In accordance with USMC operational doctrine, the CH-53K is designed for the transportation of materiel, personnel and supplies during the assault phase of an amphibious operation. As such, the potential threat to a slow moving, low flying helicopter is significant, particularly with respect to small arms fire. There is no field level composite repair capability with the USDOD. Purdue University has developed a field level rapid repair technique capable of returning strength and integrity to in service damage sustained to carbon composite structural components. The patch is carbon fiber repair patch that is applied using Vacuum Assisted Resin Transfer Molding (VARTM). This thesis seeks to validate the repair process by constructing panels representative of the CH-53K structural panels, inflicting typical damage to the panels and repairing them in accordance with the newly developed techniques.
Degree
M.S.A.A.
Advisors
Pipes, Purdue University.
Subject Area
Engineering|Aerospace engineering|Materials science
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