Investigation of Advanced Filament Wound Aircraft Landing Gear Structures.
Final rept. Jun 67-Jun 69,
MCDONNELL DOUGLAS CORP LONG BEACH CA DOUGLAS AIRCRAFT DIV
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This test program was devised to evaluate experimentally the feasibility of theuse of advanced filament wound structures in aircraft landing gear applications.Three cylindrical strut components were designed, analyzed, and fabricated from filament wound boronepoxy matrix composites. Each specimen, containing minimum weight end fittings and illustrating a variety of design conditions, was tested to destruction by a combination of service simulating loads including compression, bending, and torsion. The end fittings included an adhesive bonded type, a mechanical type, and a combination mechanical and adhesive bonded type. The orientation of the boron filaments in the cylindrical struts included longitudinal, helical, and circumferential plies, and the program included an investigation of the feasibility of employing the filament winding process for producing the struts. The experimental data was compared with predicted and actual responses of equivalent metal constructions. Author, modified-PL
- Laminates and Composite Materials