Abstract
Recently-developed electron-beam-curable epoxy resin paste adhesives and laminating resins were explored to determine their suitability for use in aircraft components. The application chosen for demonstration was the composite windshield frame/arch of the T-38 Talon, the U.S. Air Force's primary supersonic jet training aircraft. The current configuration of the T-38 windshield frame/arch, designed by the USAF Advanced Composites Program Office, incorporates thermally-cured epoxy prepreg and film adhesive. Two windshield assemblies were fabricated, substituting electron-beam materials for thermally cured materials. Fabrication of the innerskin, bulkhead doubler, and fairing fiberglass/epoxy components took place using the AECL Whiteshell Laboratory's I-10/1 Electron Accelerator (10 MeV, 1 kW). The arch is 25.4 cm thick, containing 15 mm of stainless steel. Curing through this cross-section required the use of X-rays. The arch was cured at E-Beam Services using a 50 kW accelerator. Assembly of the components was done at McClellan AFB, CA using the conventional thermally-cured adhesives. The T-38 windshield frame/arch must be able to withstand the impact of a 4 pound bird at 400 knots. The new e-beam frame/arch was tested at the PPG bird-strike facility in Huntsville, AL. Results of the test, and comparisons to the thermally-cured frame and arch are discussed.
Original language | English |
---|---|
Pages (from-to) | 1647-1659 |
Number of pages | 13 |
Journal | International SAMPE Symposium and Exhibition (Proceedings) |
Volume | 43 |
Issue number | 2 |
State | Published - 1998 |
Externally published | Yes |
Event | Proceedings of the 1998 43rd International SAMPE Symposium and Exhibition. Part 2 (of 2) - Anaheim, CA, USA Duration: May 31 1998 → Jun 4 1998 |