889. Design and Weight Aspects of Advanced Composites in Complex Fuselage Structures
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Paper
Abstract
This paper describes the design, analysis and testing of a full-scale section of F-111 aft fuselage constructed from a variety of advanced composite materials. This work represents the first application of advanced composites to complex fuselage structure. Maximum utilization of composites was maintained in both the shell structure and substructure. A wide variety of advanced composites and their applications were evaluated in a design and fabrication effort.
A 160 inch full scale static test component was designed, fabricated and tested to destruction. Fourteen subassemblies of frames and panels were fabricated and assembled into a 920 pound component utilizing 460 pounds of advanced composite materials.
Static test of the part included loading in bending with simultaneous application of internal pressure. Analytical predictions were obtained with a finite element simulation of the primary structure. Deflection gauge and strain gauge data showed excellent agreement with analytically predicted results.
Weight savings of up to 29 percent were obtained on various elements of the structure. An overall weight savings of 18 percent with respect to equivalent metallic structure was realized.
