Accession Number:

ADA029641

Title:

Modal Method for Free Vibration of Oval Cylindrical Shells with Simply Supported or Clamped Ends.

Descriptive Note:

Interim rept.,

Corporate Author:

POLYTECHNIC INST OF NEW YORK BROOKLYN DEPT OF AEROSPACE ENGINEERING AND APPLIED MECHANICS

Personal Author(s):

Report Date:

1975-08-01

Pagination or Media Count:

48.0

Abstract:

The free vibration of an oval cylindrical shell of finite length was investigated. The analysis was based upon the kinematic relations of the first-order shell theory of Sanders, which is readily reducible to the Donnell-type of shell theory via a tracing constant k sub s. In-plane inertia was retained throughout the present analysis. A method incorporating a type of eigenfunction expansion into Hamiltons principle, suitable for the present class of problems, was developed. Such a method was judged to be far more convenient than a parallel Fourier analysis. In addition to the determination of the natural frequencies and deformation characteristics, attention was focused on the influence of various types of simple support and clamped conditions enforced at the edges of the shell. Two modes of deformation, corresponding to a higher and a lower frequency were observed to exist for every pair of axial and circumferential wave numbers, depending upon the degree of circumferential symmetry in the deformed pattern. Author

Subject Categories:

  • Aircraft
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE