Some potentially low-cost manufacturing techniques to produce composite drive shafts for helicopter dynamic systems are investigated. These include a tow-placement process for graphite/PEEK composite, filament-winding of graphite/PEEK and resin-transfer-molding of a two-dimensionally braided graphite fiber preform with two different resin systems, a standard epoxy and a toughened epoxy. Shaft specimens were based upon an existing helicopter shaft and sized for the same design requirements. Damage resistance to 'low-velocity' impact events typical of tool drops and part handling was determined using an instrumented impact machine. Damage in the form of delaminations was found in all specimens for energies as low as 2 ft-lb. A dynamic model of the impact even confirmed that contact forces can develop during the impact because the high local stiffness of a cylindrical shell. Damage resistance results show that the tow-placed specimen and braided specimen with a toughened epoxy had the least amount of damage for a given impact. Specimens without and with impact damage were tested to ultimate torque. Results show that the tow-placed thermoplastic shaft had the highest residual strength after impact.
Damage tolerance evaluation of new manufacturing techniques for composite helicopter drive shafts
Die Ermittlung der Schadentoleranz von neuer Fertigungstechnik für Hubschrauberantriebswellen aus Verbundwerkstoff
1993
10 Seiten, 19 Bilder, 4 Tabellen, 6 Quellen
Conference paper
English
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