Damage Tolerance Analysis for Manned Hypervelocity Vehicles. Volume 2. Software User's Manual
Abstract
The objective of this program was to provide a fracture mechanics based life prediction procedure for hypersonic airframe structures subjected to combined mechanical loadings and thermal profiles. Existing routines were used along with element test data to develop this procedure. Accuracy of the procedure was determined by predicting the crack growth under thermomechanical load histories typical of advanced fighters and aerospace vehicles, and then comparing those predictions with test results. Limitations in the ability of this procedure to predict the test results were used to formulate recommendations for further modeling efforts and research. A fracture mechanics based life prediction procedure was developed for hypersonic airframes subjected to thermomechanical load profiles. The analysis that was developed models crack growth behavior in metals, accounts for the effects of temperature on yield strength and fracture toughness, and includes the effects of sustained loads at elevated temperature on crack growth rate. The analysis was incorporated into a computer routine named DAMAGE. Predictions made with the DAMAGE routine were within 20% of the test lives for 67% of the combined thermomechanical load history tests performed. Keywords: Fatigue life; Fracture mechanics; Service life expectancy; Mathematical prediction; Thermal/mechanical fatigue.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1989
- Accession Number
- ADA222136
Entities
People
- C. R. Saff
- D. M. Harmon
Organizations
- McDonnell Aircraft Corporation