NASA sponsored composites research and development programs were set in place to develop the critical engineering technologies in large transport aircraft structures. This NASA-Boeing program focused on the critical issues of damage tolerance and pressure containment generic to the fuselage structure of large pressurized aircraft. Skin-stringer and honeycomb sandwich composite fuselage shell designs were evaluated to resolve these issues. Analyses were developed to model the structural response of the fuselage shell designs, and a development test program evaluated the selected design configurations to appropriate load conditions.
Development of pressure containment and damage tolerance technology for composite fuselage structures in large transport aircraft
1986-08-01
Report
No indication
English
Aspects of Damage Tolerance of Aircraft Fuselage Structures
British Library Conference Proceedings | 2008
|Aspects of damage tolerance of aircraft fuselage structures
Tema Archive | 2008
|Damage tolerance analysis of composite transport fuselage structure
Tema Archive | 1994
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