Impact Behavior of Fibrous Composites and Metal Substructures,
Abstract
This program was conducted to determine the differences in nonlinear load-defection characteristics between a typical helicopter ventral substructure fabricated with aluminum and one designed to the same loads criteria fabricated with fiber composite materials. The feasibility of applying the analytical and testing techniques developed under contract for a metal structure to a composite structure was investigated. The composite structure was designed as a one-for-one replacement of the metal structure to meet the same design loads that were used for the metal structure. Because full-scale specimen testing could not be performed using existing in-house equipment, a scale model test was conducted. A dimensional analysis procedure based on the scaling laws of the Buckingham theorem was used to define the scaling approach. The feasibility of testing scaled helicopters for proofing crash survivability requirements were also examined. Test results obtained were in agreement with those reported under the contractual effort and demonstrated that fuselage structures can be scaled for impact testing. The composite structure showed slightly lower energy absorption than the metal structure.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1982
- Accession Number
- ADA121618
Entities
People
- A. J. Gustafson
- G. Shek Ng
- G. T. Singley Iii