A Spectrum Truncation and Damage Tolerance Study Associated with the C- 5A Outboard Pylon Aft Truss Lugs
Abstract
A simplified lug specimen configuration is subjected to two load spectra derived from the same exceedance data: (1) a 17 level block loading program, and (2) a 14-mission flight-by-flight loading program. Crack growth data from the two spectra for this PH 13-8Mo material are compared on a life basis; each spectrum contained an equal number of Ground Air Ground (GAG) cycles per lifetime. An analysis of the effect associated with the degree of truncation to which the flight spectrum could be subjected was performed using the conservative no retardation - no load interaction crack growth model and the Willenborg crack growth retardation model. The stress intensity factor calibration developed using finite element techniques is supplemented with stress intensity factor values obtained using the Anderson - James inverse approach. Additional tests on 7075-T6 aluminum are described which investigate the importance of load redundancy.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1974
- Accession Number
- AD0785196
Entities
People
- H. D. Stalnaker
- J. L. Rudd
- J. P. Gallagher
Organizations
- Flight Dynamics Laboratory