Title

The Use of Models for Control of Sonically Induced Vibration

Report Number

RTD-TDR-63-4197 Part I, p. 609

Creator

Berstein, M.

Gross, R.

Corporate Author

Grumman Aircraft Engineering Corporation, Dynamic Analysis Section

Laboratory

Air Force Flight Dynamics Laboratory

Date

1964

Date Issued

1964-03

Extent

39

Abstract

A half-scale dynamically-similar model of a non-uniformly-stiffened fuselage structure of slightly varying cross section was designed, constructed, and tested to obtain data on the response of the full-scale structure to propeller-noise excitation. This approach was chosen as the logical compromise between the cost of a full-scale accuracy of practicabte analytical methods. The model was used to determine how the natural frequencies of the structure might be varied, if necessary, and to investigate means for reducing internal noise and vibration levels. As an indication of the accuracy of practicable analytical methods when applied to relatively complex, realistic structures, a comparison was made between the experimental vibration characteristics and the mode shapes and frequencies computed for an" equivalent" uniform cylinder and for a ring cross-section with stiffners included.

Distribution Classification

1

Distribution Conflict

No

DTIC Record Exists

No

Illinois Tech Related

No

Photo Quality

Complete

Report Availability

Full text available

Type

article

Is Part Of

Proceedings of Symposium on Aeroelastic & Dynamic Modeling Technology

Provenance

Bombardier/Aero