EXPERIMENTAL STUDY OF THE THERMAL BUCKLING OF CYLINDRICAL SHELLS,
Abstract
Air-and spacecraft fuselage normally consist of cylindrical and conical thin-walled shells. High-speed flight causes heating (either through an external aerodynamic effect, or from an internal energy source such as the rocket engine), which is mostly non-uniform and may induce buckling. Earlier works on this subject have shown that the most critical case is that of circumferential variation of the temperature. The report describes a device permitting study of buckling due to combined thermal and mechanical load. A test series and its results are presented. The tests were carried out on fixed-ended cylindrical shells, linearly heated along the upper generator. The concept of thermal buckling is discussed in the light of test results. The present tests are compared with those of earlier studies and their conclusion that the ratio between the nominal thermal stress to the classical linear theoretical one is higher than the ratio between the experimental stress to the classical one in uniform axial compression is reconfirmed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1969
- Accession Number
- AD0702126
Entities
People
- Joseph Frum
- Menahem Baruch
Organizations
- Technion – Israel Institute of Technology