Advanced Metallic Air Vehicle Structure Program
Abstract
Refinement of the three designs for a wing carry through structure was continued to the end of Phase Ib. On the basis of trade studies, materials and component testing and the results of NDI and manufacturing development work, two of the configurations were chosen for the detail design phase. Materials testing was substantially completed for the beta annealed 6Al-4V titanium and testing is underway for the Beta C titanium and 10 Ni steel. Group I component tests (those performed to verify design concepts) are virtually complete. Tests to evaluate the welding, brazing and bonding processes are also well underway. Design of the test fixture is proceeding with some manufacturing effort already started. Detail design and analysis of the simulated fuselage structure for the test article is also in work. Additional trade studies were conducted early in Phase II and several design changes were incorporated into the two wing carry through structure configurations as a result of these studies. A ZFO panel was added to the 'No Box' box design. The fail safe removable lug configuration was redesignated the fail safe integral lug configuration after an integral lower plate-lug arrangement was selected for detail design.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1973
- Accession Number
- AD0914705
Entities
People
- C. E. Hart
- D. L. Duncan
- E. K. Hensley
- J. W. Jennings
- R. C. Bissell
Organizations
- General Dynamics