Accession Number : AD0429770


Title :   ON CORRUGATION-STIFFENED PANELS,


Corporate Author : CALIFORNIA INST OF TECH PASADENA GRADUATE AERONAUTICAL LABS


Personal Author(s) : Fung,Y C


Report Date : 08 Jun 1962


Pagination or Media Count : 28


Abstract : A corrugation-stiffened panel consists of a flat plate and a cylindrically corrugated plate welded together along lines of contact. Such a panel appears on air-and space-craft mainly for its thermal-stress relieving characteristics. In some current publications such a plate is treated as an orthotropic plate. It is pointed out that the ordinary plate theory cannot be applied to the corrugation-stiffened panel, because the basic twisting moment relation, Mxy=Myx becomes untenable. A difference-differential equation is established here for the corrugation-stiffened panel. In an approximation, the difference-differential equation is written as a partial differential equation which has the same form as the orthotropic plate equation. The present theory tells how to interpret the coefficients as related to the plate geometry. Some consequences with regard to the static deflection and vibration modes and frequencies of corrugation-stiffened panels are discussed. If the formula to correct the experimental envelope of supersonic flutter boundaries given by Kordes, Tuovila, and Guy, is used a somewhat different boundary is obtained but the modification is not large. (Author)


Descriptors :   *PANELS , SHEETS , WELDING , LOADS(FORCES) , VIBRATION , DIFFERENCE EQUATIONS , SPACECRAFT


Distribution Statement : APPROVED FOR PUBLIC RELEASE