Intro
List of Figures
List of Tables
List of symbols
1 Introduction
1.1 The need for a new simulation framework
1.2 State of the art
1.3 Objectives and thesis overview
2 Multidisciplinary analysis andoptimization framework
2.1 Developed process and mixture of competences
2.2 General process overview
3 Loads calculation process
3.1 Scope of computed load conditions
3.2 Loads calculation model
3.3 Electronic Flight Control System
4 Structural property optimization andmass penalty estimation
4.1 Modeling aspects of global FEM representation
4.2 Global FEM external loading
4.3 Linear static analysis and results management
4.4 Wing structural property optimization
4.5 Fuselage mass penalty estimation
5 Feedback loop
5.1 Starting approach
5.2 Main process steps of the feedback loop
5.3 Update of stiffness values - equivalent beamapproach
5.4 Update of mass values - grid point weight generator
5.5 Global convergence criteria
5.6 Impact of wing stiffness changes on the jig and flightshape
6 Design studies
6.1 Influence of the load alleviation function on thecalculated flight loads
6.2 First design study with reduced load case set
6.3 Design study with complete load case set
7 Summary, discussion of methods andresults, outlook
7.1 Summary
7.2 Discussion of methods
7.3 Discussion of results
7.4 Outlook
Bibliography
A Loads calculation and structuralassessment
B Feedback loop - main process steps
C Equivalent beam approach -validation
D Equivalent beam approach -influence of skin and stringer
E Grid Point Weight Generator - basics
F Influence of the load alleviationfunction on the calculated flightloads
G Structural baseline generation
H Influence of load alleviation functionon structural components.