||Optimization of Windows on Composite Aircraft
||Department of Aeronautics & Astronautics
In order to save computational time during optimization process, we want to know if optimization of simplified model can give us a trend to follow to improve much more complicated model. By running optimization process from the most general case, an infinite plate containing a hole under a traction loading to more complicated case, finite plate containing a hole with traction and pressure loading, we obtained results for a simplified model. Then we used these results into a more complicated problem. By using this approach, we optimize an aircraft composite fuselage panel. For these optimizations, we focused on mechanical part of this system, objective is to reduce the stress concentration factor. Results obtained with optimization procedure and results from the real model have similar trends. Therefor this procedure can be used to save a lot of optimization computational time.
TABLE OF CONTENTS III
LIST OF TABLES V
LIST OF FIGURES VII
CHAPTER I INTRODUCTION 1
1.1 Problem faced during complex model optimization 1
1.2. Literature review 2
CHAPTER II METHODOLOGY 3
2.1. Methodology presentation 3
2.2. Optimization problem 6
CHAPTER III PROCEDURE 22
3.1. Tools testing 22
3.1.1. Verifying ANSYS and AEPH results 22
3.1.2. Optimization’s trend check 23
3.2. Optimization process 33
3.2.1. Optimization of a finite plate containing a hole without pressure force. 33
3.2.2. Optimization of a finite plate containing a hole with pressure force. 34
3.3. Real model 36
3.3.1. Real model description 36
3.3.2. ANSYS modelling 40
CHAPTER IV RESULTS 48
4.1. Preliminary test 48
4.1.1. Test results 48
4.1.2. Optimization trend 50
4.2. Finite plate optimization 60
4.2.1. Finite plate without pressure force 60
4.2.2. Finite plate with pressure force 68
4.3. Real model 75
CHAPTER V CONCLUSION AND SUGGESTIONS 82
5.1. Conclusion 82
5.2. Suggestion 83
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