Accession Number : AD0683289
Title : AIRCRAFT AND MISSILE STRUCTURES OPERATING AT HIGH TEMPERATURES.
Descriptive Note : Final technical status rept.,
Corporate Author : STANFORD UNIV CALIF DEPT OF AERONAUTICS AND ASTRONAUTICS
Personal Author(s) : Hoff,Nicholas J.
Report Date : 30 SEP 1968
Pagination or Media Count : 10
Abstract : The report describes contributions made to the clarification of the buckling process of thin shells. One of the results was the discovery that a very slight modification of the classical boundary conditions results in a reduction in the value of the critical stress of the linear theory by a factor of about one-half. Another result of importance was that the procedure of Karman and Tsien in finding a minimal value of the post-buckling stress loads to a perfectly correct but trival result. The maximal value of the equilibrium stress of the imperfect shell reached in testing machine loading has been calculated by Prof. Hoff by two methods. The number of buckles around the circumference were shown experimentally and theoretically to decrease as the length-to-radius ratio of the shell is increased. A tie-in between buckling in testing machine loading and buckling under thermal stresses was obtained theoretically and experimentally. (Author)
Descriptors : (*AIRFRAMES, STRUCTURAL PROPERTIES), (*SHELLS(STRUCTURAL FORMS), THERMAL STRESSES), HIGH TEMPERATURE, GUIDED MISSILES, LAUNCH VEHICLES, SPACECRAFT, AIRCRAFT, LOADS(FORCES), BUCKLING, STRESSES, CYLINDRICAL BODIES, ELASTIC SHELLS, CONICAL BODIES, DEFORMATION
Subject Categories : Structural Engineering and Building Technology
Distribution Statement : APPROVED FOR PUBLIC RELEASE