27-10-2012, 04:13 PM
WingOpt - An MDO Research Tool for Concurrent Aerodynamic Shape and Structural Sizing Optimization of Flexible Aircraft Wings.
WingOpt.ppt (Size: 3.24 MB / Downloads: 29)
Aims and Objectives
Develop a software for MDO of aircraft wing - Study issues of integrating MDA for formal design optimization
Aeroelastic optimization as an MDO problem - Concurrent aerodynamic shape and structural sizing optimization of a/c wing
Realistic MDO problem - Showcase a reasonably complex aircraft design optimization problem with high fidelity analysis
Study different MDO architectures – reformulations of the optimization problem
Influence of fidelity level of structural analysis
Study computational performance
Benchmark problem for MDO framework development
Design Drivers/Constraints for the WingOpt Architechture
Definition of a meaningful overall design problem based on available analysis and optimization capability
Limited disciplines considered: Geometry, Aerodynamics, Structures, Trim/Maneuver
Aeroelasticity as basis for coupling disciplines
Software integration within confines of high level programming languages (FORTRAN/C) through students
At least one discipline taken to its highest fidelity (structures)
Emulate some elements of a general purpose framework
Variables & Function Database
Identify array of all variables/functions associated with the system analysis
Identify all possible candidates for design variables/constraints
Partition variables database to fixed and design parameters.
Tag user codes to all variables/functions
Define subset optimization problem through tags
Create location look-up tables for selected subset variables/constraints
Features of WingOpt
Flexibility
Easy and quick setup of the design problem
Aeroelastic module can be switched ON/OFF
Selection of structural analysis (FEM / EPM)
Selection of Optimizer (FFSQP / NPSOL)
Selection of MDO Architecture (MDF / IDF) and their variants
Design variable linking
Load Case specification. Variables/design constraints attached to load cases
Summary
Software for MDO of wing was developed
Simultaneous structural and aerodynamic optimization
Focused around aeroelasticity
Handles internal loop instability
MDO Architectures formulated and implemented
Methods for accelerating convergence formulated and implement
Multiple load case implemented
User interface improved