Linearized FUN3D for Rapid Aeroelastic and Aeroservoelastic Design and Analysis

Period of Performance: 01/01/2014 - 12/31/2014

$125K

Phase 1 SBIR

Recipient Firm

Zona Technology, Inc.
9489 East Ironwood Square Drive
Scottsdale, AZ 85258
Principal Investigator
Firm POC

Abstract

The overall objective of this Phase I project is to develop a hybrid approach in FUN3D, referred herein to as the Linearized FUN3D, for rapid aeroelastic and aeroservoelastic (ASE) design and analysis. The Linearized FUN3D solves a linearized Euler equation with a transpiration boundary condition using the FUN3D steady N-S solution as the steady background flow to efficiently generate a Reduced Order Model (ROM) in the form of the frequency-domain Generalized Aerodynamic Forces (GAF) matrices due to the structural modes, control surface kinematic modes and gust excitation. The Linearized FUN3D can generate an accurate unsteady aerodynamic solution in the small perturbation sense about a nonlinear steady flow condition. It also can avoid the moving mesh problem associated with applying the exact N-S boundary condition which requires additional computational resources, and becomes very complex in dealing with the discontinuous displacement in mode shapes such as the control surface modes for which generating a computational mesh could be a very tedious effort.In order to enable the Linearized FUN3D to perform frequency-domain open-loop and closed-loop aeroelastic analysis and to generate a plant model in terms of state space equations, several modules in ZAERO, ZONA's flagship commercial software for aeroelastic, ASE, and gust analysis, will be incorporated into the Linearized FUN3D. One can directly import such a plant model into MATLAB to design a flutter suppression and Gust Loads Alleviation (GLA) control system using the modern control design schemes available in MATLAB.The accurate flow field prediction of the wing pressures when a spoiler is deployed is currently beyond the capabilities of the existing aeroservoelastic codes. The wind tunnel measured unsteady pressures on the Benchmark Active Controls Technology wing will be selected to validate the proposed Linearized FUN3D for unsteady aerodynamic prediction due to spoiler oscillations.