This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Composite Applications to Aircraft Structures Now and in the Future
Annotation ability available
Sector:
Language:
English
Abstract
The primary force behind composite materials development for aircraft applications was to achieve weight savings in weight-critical regions. In today's aircraft technology, graphite/epoxy composites are fulfilling this need and are being used as structural materials in the form of cross-plied fiber-reinforced laminates for conventional monolithic wing/empennage skins and substructure, or as face sheets on honeycomb-type structure. All metal components have been replaced by composite structure on aircraft such as the B-1, F-18, and AV-8B. Weight/cost savings were demonstrated for the B-1 aircraft in which not only weight savings, but also cost competitiveness were the goals. The next-generation aircraft will incorporate composites in a significantly larger proportion of the airframe structure to exploit more fully all advantageous characteristics of advanced composite structure (strength, stiffness, tailorability, weight, and fabrication cost savings).
This paper describes some of the various applications of composite materials on today's aircraft using state-of-the-art technology, and the various innovative integral advanced composite design and fabrication concepts as well as aeroelastic tailoring which can be used on future aircraft systems to achieve the overall objective of higher efficiency at lower cost.
Recommended Content
Authors
Topic
Citation
Lackman, L., Price, M., and Matoi, T., "Composite Applications to Aircraft Structures Now and in the Future," SAE Technical Paper 790146, 1979, https://doi.org/10.4271/790146.Also In
References
- Parker D. E. “Development of Low-Cost Composite Vertical Stabilizer - Volume I - Development and Structural Validation of the Composite Vertical Stabilizer,” Rockwell International Corporation/Los Angeles Division Prepared for Air Force Flight Dynamics Laboratory Report AFFDL-TR-78-5 June 1978
- “HiMAT Development Design Methodology,” Contract NAS4-2560 January 1979
- O'Brien W. L. et al “Wing/Fuselage Critical Component Development Program - Preliminary Structural Design Phase,” Contract F33615-77-C-5229 Rockwell International Corporation/Los Angeles Division, Prepared for Air Force Flight Dynamics Laboratory, Wright-Patterson Air Force Base
- Lackman L. M. et al “Advanced Composites Integral Structures Meet the Challenge of Future Aircraft Systems,” TFD-78-653 Rockwell International Corporation/Los Angeles Division October 1978
- Nadler M. A. “Integral Design and Manufacturing Approach to Composite Wing/Fuselage Structure,” Rockwell, International/Los Angeles Division Paper for Presentation at SPE PACTEC IV Conference January 31 February 2 1979 Costa Mesa, California