EXPLORATORY APPLICATION OF FILAMENT WOUND REINFORCED PLASTICS FOR AIRCRAFT LANDING GEAR.
Abstract
The investigation produced theoretical expressions for calculating the mechanical properties of various laminates and for predicting the strength and stiffness of structural elements under various types of loading. For tubular elements, the calculated strength and stiffness for bending and torsional loading agrees very well with test results. The application of fittings and attachments to the basic filament composite structural element is accompanied by a weight increase. This expenditure tends to offset the weight advantage inherent with the composite construction. The greatest promise for weight saving lies with components designed to support torsion or axial compression and tension. These loadings predominate with such items as torsion shafts, shock absorber restictor support tubes, spacer tubes, and landing gear side and drag braces. An important conclusion derived from the design study is that more work is necessary in the development of high efficiency structural joints which would provide a greater retention of the weight advantage afforded by the basic composite element. The results of the study indicate that in general, filament wound construction would be very competitive with conventional metal construction from the standpoint of cost. For some selected components, the cost for filament construction varies from 75 to 100 percent of the cost of conventional metal construction. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1966
- Accession Number
- AD0806336