1. Aircraft Conceptual Design Optimization
Kristian Amadori, Dr. Christopher Jouannet

2. Outline Introduction Design Framework Test Case 1 Conclusions
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3. Introduction System design is today characterized by:
Distribution
Collaboration
Competition
Subsystem/ design team
System / system integration group
Subsystem interface
Aircraft are complex products
Increasing competition
Environmental challenges
Increasing foreseeable operational life of today’s aircraft
We need tools for distributed system design that handles these characteristics in early design stages
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4. Why?
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5. Introduction
Disciplinens
Table from: Nickol, C., “Conceptual Design Shop”, Presentation to Conceptual Aircraft Design Working Group (CADWG21), Sept. 2004
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6. Design Framework Based on Web Service Technology
Implements so-called Service Oriented Architecture (SOA)
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7. Design Framework Connect together tools from different disciplines
Maintain system perspective
Allow for distribution
Design optimization
Spread sheet with design analysis and optimization tools
System Model
Wing
Wing
Performance
Performance
Propulsion
Propulsion
Optimization
Fuselage
Fuselage
Structure
Propulsion
Aircraft Sizing Model
Electric Power System
Electric Power Sstem
Fuel System
Fuel System
Stability & Control
Stability & Control
Actuation System
Actuation System
Aerodynamic
Aerodynamics
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8. Parametric CAD Modeling
Flexible geometries
Robustness
Hierarchical
Associative
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9. Parametrization Various stages of Morphological instantiation
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10. Parametrization Various stages of Topological instantiation
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11. Parametric CAD Modeling
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13. Parametric CAD Modeling
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14. Parametric CAD Modeling
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15. Parametric CAD Modeling
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16. Parametric CAD Modeling
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17. Aerodynamics Tornado can be used (integrated to the framework)
PANAIR 3D
Capable of analyzing any geometry
Fast
(Relatively) accurate
Tornado can be used (integrated to the framework)
Other CFD tools can be used if jugsed necessary
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18. Test Case: Wing-Box Design Optimization
Wing-box structure optimization, given the air loads and a predefined shape:
Position, orientation and thickness of ribs
Spars thickness
Skin thickness
Number of ribs
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19. Test Case: The Optimization Problem
Problem formulated as:
Soft contraint formulation:
The loads considered were the airloads obtained from PANAIR during a hypothetical 3g pull up maneuver. Stress relieves from both an engine mounted on a wing pylon and from the structure weight itself were also taken into account.
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20. Test Case: Results (a)
Optimization stopped after 1000 trials with number of ribs are fixed to 10 (left) or let vary between 5 to 15 (right)
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21. Test Case: Results (b)
Optimization stopped after trials with number of ribs are fixed to 10 (left) or let vary between 5 to 15 (right)
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22. Test Case : Results Summary
1000 Iterations
20000 Iterations
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23. Conclusions
Framework architecture that focuses on its flexibility of application
How to proficiently include high-end CAD system into initial geometry generation
Higher model flexibility increases chance to find better solution
KBE-techniques
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