Accession Number : ADP005867

Title :   Aeroelastic Tailoring Procedure for Controlling Fin Hinge Moments,

Corporate Author : NIELSEN ENGINEERING AND RESEARCH INC MOUNTAIN VIEW CA

Personal Author(s) : Dillenius, M. F. ; McIntosh, S. C., Jr

Report Date : MAR 1989

Pagination or Media Count : 14

Abstract : A combined static aeroelastic and optimization design method is presented which is aimed at controlling the center of pressure acting on a missile control fin made of composite material. Specifically, the material principal-axis directions of various segments of an orthotropic fin are varied in order to influence the chordwise location of the center of pressure through elastic fin deformation under nonlinear supersonic aerodynamic loading. The design problem is posed as an optimization problem, where the principal-axis directions are the design variables, and the objective is the difference between the current center of pressure location and its desired location. Constraints on flutter speeds, displacements, and natural frequencies are permitted, and the design variables have upper and lower bounds. Consistent fin deformations are obtained by iterating between the aerodynamic load and the fin displacement calculations. Results obtained by the present method are presented for a hypothetical supersonic missile control fin. (JES)

Descriptors :   *GUIDED MISSILES, AERODYNAMIC LOADING, COMPOSITE MATERIALS, COMPUTATIONS, CONSISTENCY, CONTROL SURFACES, DEFORMATION, DISPLACEMENT, ELASTIC PROPERTIES, FINS, FLUTTER, HINGES, MOMENTS, NONLINEAR SYSTEMS, OPTIMIZATION, POSITION(LOCATION), PRESSURE, RESONANT FREQUENCY, SUPERSONIC CHARACTERISTICS, VELOCITY.

Subject Categories : Guided Missiles
      Aerodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE