Effects of Repair on Structural Integrity
Abstract
FAA regulations require commercial aircraft operators to repair damaged aircraft structures. These repairs must be performed in a timely manner to reduce aircraft downtime and loss of revenue. A guiding principal for such repairs is to restore the structure to the original (or better) static strength and stiffness. However, the repair can also be designed for adequate fatigue resistance, damage tolerance, and inspectability. Fatigue and damage tolerance (DT) analyses should be based on realistic stress histories which, in turn, should be derived from realist load spectra. Thus, an algorithm for the development of a stress history should be included in a comprehensive analysis of repairs. Since many damage repair stations and airlines do have at least basic computer facilities that can be used for fatigue and damage tolerance analysis, one goal has been the development of a relatively simple, yet accurate analytical tool to design aircraft repairs more effectively. Structural analysis and stress spectrum development procedures described in this report are approximate and, therefore, have certain limitations. These procedures might be used to qualitatively compare the quality of different repair options with the original structure. SKINFIX, Load spectra, static strength, damage tolerance
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1993
- Accession Number
- ADA275756
Entities
People
- Broek D. Smith
- M. Rosenfeld
- R. Francini
- R. Rice
- S. Rust
- Sharidya Rahman
Organizations
- Battelle Memorial Institute