Accession Number : ADA325358

Title :   Development of Preliminary Design Models for Active Aeroelastic Wing Application.

Descriptive Note : Final rept. Oct 94-Dec 96,

Corporate Author : CSA ENGINEERING INC PALO ALTO CA

Personal Author(s) : Eastep, Frank

PDF Url : ADA325358

Report Date : JAN 1997

Pagination or Media Count : 134

Abstract : An investigation of active aeroelastic wing (AAW) technology was initially conducted on a 'beam rod' model of an FIA-18 aircraft for demonstration of an acceptable roll performance. The beam rod model was verified by comparing the natural frequencies to the results obtained by McDonnell-Douglas during a ground vibration test. Further verification of the beam-rod model and selected aerodynamic representation of the FIA-18 were obtained in flutter studies. The beam-rod model was further developed for active aeroelastic wing technology through a study of control surface blending for the roll performance enhancement of the FIA-18 with a reduction of wing stiffening. It is demonstrated that the roll performance of the FIA-18 could be enhanced by incorporating AAW concepts in the design stage of aircraft development It was determined that a finite- element representation of the built-up wing was necessary for the accurate prediction of aeroelastic deformation. A generic built-up fighter wing was considered to demonstrate preliminary design methods incorporating aeroelastic wing technology. Optimization studies of this aircraft wing were conducted utilizing multiple blended control surfaces to effect roll trim.

Descriptors :   *AEROELASTICITY, *WINGS, *AERODYNAMICS, TEST AND EVALUATION, GROUND LEVEL, METHODOLOGY, VIBRATION, ROLL, OPTIMIZATION, VERIFICATION, PREDICTIONS, BLENDING, STRUCTURAL PROPERTIES, DEFORMATION, STIFFENING, ACCURACY, REDUCTION, RESONANT FREQUENCY, VIABILITY, ATTACK AIRCRAFT, JET FIGHTERS, RODS, WEIGHT REDUCTION, FLUTTER, CONTROL SURFACES.

Subject Categories : Aerodynamics
      Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE