Accession Number : ADP005879

Title :   Aeroelastic Analysis of Missile Control Surfaces with Structural Non-Linearity,

Corporate Author : BRITISH AEROSPACE PLC HATFIELD (UNITED KINGDOM)

Personal Author(s) : Sephay, D.

Report Date : MAR 1989

Pagination or Media Count : 12

Abstract : This paper presents an aeroelastic procedure to deal with structural nonlinearity of a missile control surface using the concept of linearised equivalent structural stiffness. This approach enables the use of standard software packages such as Nastran for linear aeroelastic analysis is divergence, flutter and dynamic response analysis. An example, backed up with experimental validation, is given for a flexible control surface with structural non-linearity due to free play at the root connection. A time simulation technique is also discussed for solution of the problem. (JES)

Descriptors :   *COMPUTER PROGRAMS, AEROELASTICITY, CONTROL SURFACES, DYNAMIC RESPONSE, EXPERIMENTAL DATA, FLUTTER, GUIDED MISSILES, LINEAR SYSTEMS, MATHEMATICAL ANALYSIS, METHODOLOGY, NONLINEAR SYSTEMS, PROBLEM SOLVING, SIMULATION, STANDARDS, STIFFNESS, STRUCTURAL PROPERTIES, TIME, VALIDATION.

Subject Categories : Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE