Title

Integral Damping Treatment for Primary Aircraft Structures

Report Number

WL-TR-91-3078 Volume I, p. BAA-1 thru BAA-15

Creator

Liguore, Sal

Ferman, Marty

Yurkovich, Rudy

Corporate Author

McDonnell Aircraft Company, McDonnell Douglas Corporation, St. Louis, Missouri

Laboratory

Wright Laboratory

Date

1991

Date Issued

1991-08

Extent

15

Contract

Laboratory Research - No Contract

DoD Project

2401

DoD Task

240104

Identifier

ADA241311

Format

1 online resource

Abstract

The dynamic response of primary aircraft structure to buffeting flows, high acoustic levels, and shock boundary layer interaction has led to premature structural fatigue failures on current aircraft and is anticipated to be a continuing problem in the future. Increasing structural strength/stiffness can be a solution but this approach adds weight to the aircraft. Since the problem is dynamic response, increasing the amount of damping in the structure can also be a solution. If integral damping is considered as a part of the original design, a lighter weight design can result. The application of integral damping to primary aircraft structure was investigated and its effectiveness in controlling the primary structural modes was assessed. The findings show the approach is feasible. A simulated aircraft structure was tested with damping treatments applied. The most promising damping concepts were then analytically evaluated on the F/A-18 vertical tail.

Description

The dynamic response of primary aircraft structure to buffeting flows, high acoustic levels, and shock boundary layer interaction has led to premature structural fatigue failures on current aircraft and is anticipated to be a continuing problem in the future. Increasing structural strength/stiffness can be a solution but this approach adds weight to the aircraft. Since the problem is dynamic response, increasing the amount of damping in the structure can also be a solution. If integral damping is considered as a part of the original design, a lighter weight design can result. The application of integral damping to primary aircraft structure was investigated and its effectiveness in controlling the primary structural modes was assessed. The findings show the approach is feasible. A simulated aircraft structure was tested with damping treatments applied. The most promising damping concepts were then analytically evaluated on the F/A-18 vertical tail.

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 Damping '91: 13-15 February 1991 San Diego, California (Pages AAC-1 through DCC-19)