A System Approach using CartEuler-based Nonlinear Aeroelasticity for FP/LCO Analysis and Design of Control Surfaces

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-08-M-3837
Agency Tracking Number: F081-086-0474
Amount: $99,987.00
Phase: Phase I
Program: SBIR
Awards Year: 2008
Solitcitation Year: 2008
Solitcitation Topic Code: AF081-086
Solitcitation Number: 2008.1
Small Business Information
ZONA TECHNOLOGY, INC.
9489 E. Ironwood Square Drive, Scottsdale, AZ, 85258
Duns: 182103291
Hubzone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: Y
Principal Investigator
 Ping Chih Chen
 Principal Investigator
 (480) 945-9988
 pc@zonatech.com
Business Contact
 Jennifer Scherr
Title: Project Manager
Phone: (480) 945-9988
Email: jennifer@zonatech.com
Research Institution
N/A
Abstract
The ZONA Team proposes to develop a nonlinear aeroelastic/aeroservoelastic methodology for free-play (FP)/LCO analysis and prediction for aircraft control surfaces at various trim conditions and subjected to gust/pilot commend excitations. In phase I, a CartEuler-based FP/LCO methodology (CEFM) will be established with a ZONA-developed Cartesian Euler solver fully integrated with a ZONA nonlinear flutter/LCO module (NLFLTR). The Cartesian grid/ boundary condition features of CartEuler allows it to perform rapid but accurate nonlinear aeroelastic simulation for complex aircraft configurations. The CEFM solutions will be validated with wind tunnel test data to be obtained by Duke University with an existing model of typical airfoil section at various FP angle and AoA under gust excitations. Next, using CEFM we will fully investigate various F-16/HT cases, including strained/unstrained structures and under gust/pilot-commend excitations for the impacts of nonlinear aerodynamic and nonlinear structural effects on each free-play and LCO responses from a 3D system perspective. Computed solutions of CEFM for the F-16/HT cases will be compared with those of ZAERO. Based on the computed CEFM results, a useful free-play scaling law will be developed that can be readily applied to establish improved control surface free-play criteria for modern aircraft.

* information listed above is at the time of submission.

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