COMPUTATIONAL AEROELASTICITY IN HIGH PERFORMANCE AIRCRAFT FLIGHT LOADS

摘要

A computational aeroelasticity methodrnhas been developed that combines a computationalrnfluid dynamics (CFD) code based onrna finite volume, Cartesian / prismatic gridrnscheme with automated unstructured gridrncreation and adaption with establishedrnstructural finite element methods. Thisrnanalysis is motivated by the need to developrnan analysis capability for fighter-aircraftrncritical flight loads. Flight conditions forrnsuch often reside in transonic flow regimesrnand comprise nonlinear aerodynamics due tornshocks, flow-separation onset, and complexrngeometry. The Multidisciplinary ComputationalrnEnvironment, MDICE [1], is providingrnfor timely integration of LockheedrnMartin’s CFD software, SPLITFLOW [2] inrna maintenance friendly, loosely coupledrnnonlinear analysis method. Analysis correlationrnwith static aeroelastic wind tunnelrndata demonstrates potential. Analysis set-uprnand results for a fighter aircraft with multiplerncontrol surfaces are demonstrated.