Title

Forced Vibrations Of Sandwich Structures

Description

In Part I of this report, a method is presented for the determination of the frequency response functions of the components of deformation and of stress in orthotropic sandwich plates. It applies to the case of simply supported rectangular plates loaded by dynamic pressure normal to their planes.

In Part II, a similar method is presented for orthotropic sandwich cylindrical shells. The boundaries of the shell are assumed as simply supported, and the dynamic pressure is normal to the middle surface. In both problems, the analysis takes into account the transverse shear deformation of the core and the material damping of core and facings. The results are presented in the form of expressions suitable for numerical evaluation.

Date

1961

Index Abstract

Contrails and DTIC

Photo Quality

Not Needed

Report Number

WADD TR 60-307

Creator

Freudenthal , Alfred M.

Bieniek, Maciej P.

Corporate Author

Columbia University

Laboratory

Materials Central

Extent

34

Identifier

AD0258536

AD0258536

Access Rights

OTS

Distribution Classification

1

Contract

AF 33(616)-7042

DoD Project

7351 - Metallic Materials

DoD Task

73521

DTIC Record Exists

No

Distribution Change Authority Correspondence

None

Report Availability

Full text available

Date Issued

1961-01

Abstract

In Part I of this report, a method is presented for the determination of the frequency response functions of the components of deformation and of stress in orthotropic sandwich plates. It applies to the case of simply supported rectangular plates loaded by dynamic pressure normal to their planes.

In Part II, a similar method is presented for orthotropic sandwich cylindrical shells. The boundaries of the shell are assumed as simply supported, and the dynamic pressure is normal to the middle surface. In both problems, the analysis takes into account the transverse shear deformation of the core and the material damping of core and facings. The results are presented in the form of expressions suitable for numerical evaluation.

Provenance

IIT

Type

report

Format

1 online resource (iv, 30 pages) : ill.

Subject

Sandwich Panels

Cylindrical Bodies

Deformation

Equations

Honeycomb Cores

Load Distribution

Mathematical Analysis

Mathematical Prediction

Mechanical Properties

Shear Stresses

Stresses

Structures

Theory

Vibration

Publisher

Wright-Patterson Air Force Base, OH : Wright Air Development Division, Air Research and Development Command, United States Air Force

NTRL Accession Number

AD258536

Distribution Conflict

No