The effort during Phase I of the contract included detailed design of a composite wheel assembly to function structurally and mechanically in a manner identical to the existing metal braked main landing gear wheel for the T-39 aircraft. The design and analysis of the graphite composite landing gear wheel was based on demonstrated material properties. A thermal analysis of the composite structure showed the maximum wheel temperature to be 406 F adjacent to the steel brake keys (inner wheel half) and 223 F on the outer wheel half. Hercules 4397/AS resin system was selected for the inner wheel half and 3501/AS for the outer half. During Phase II, one inner and two outer wheel halves were fabricated. (Author)
Graphite Composite Aircraft Landing Gear Wheel
1976
94 pages
Report
No indication
English