Minimizing fuel consumption is one of the major concerns in the aviation industry. There have been many attempts to improve the fuel efficiency of aircraft. One of the methods proposed is to vary the lift-to-drag ratio of the aircraft in different flight conditions. To achieve this, the wing of the airplane must be able to change its configuration during flight…
Contents
1 INTRODUCTION
1.1 MOTIVATION
1.2 OBJECTIVE
1.3 OUTLINE
1.4 TECHNICAL CHALLENGES
1.5 THESIS CONTENTS
2 OVERVIEW OF VARIABLE CAMBER WING
2.1 VARIABLE CAMBER WING IN THE PAST
2.2 CONTEMPORY VARIABLE WING AND CONCEPTS
2.2.1 High-Lift Devices
2.2.2 Mission Adaptive Wing (MAV)
2.2.3 Active Aeroelastic Wing (AAW)
2.2.4 Variform Wing Concept and Buckle-Wing Biplane
2.3 SMART MATERIALS AND VARIABLE CAMBER WING
2.3.1 Compliant Mechanism
2.3.2 Piezoelectric Actuator and Variable Camber Wing
2.3.3 Reconfigurable Wing
2.3.4 DARPA/Wright Lab “Smart Wing”
3 VARIABLE CAMBER WING DESIGN
3.1 INITIAL CONCEPT
3.2 MULTI-SECTION VARIABLE CAMBER WING
3.2.1 Wing Ribs and Spars
3.2.2 Actuators
3.2.3 Wing Structures Assembly
3.2.4 Wing Skin
3.3 RIGID WING MODELS
4 AERODYNAMIC ANALYSIS
4.1 AIRCRAFT RANGE AND ENDURANCE
4.2 DEVELOPMENT OF THE ESTIMATED LIFT AND DRAG
4.2.1 Lift Calculation
4.2.2 Drag Calculation
5 EXPERIMENTAL TESTING OF MULTI-SECTIO VARIABLE CAMBER WING
5.1 EXPERIMENTAL TEST APPARATUS…..
6 CONCLUSION……..
Author: Poonsong, Prasobchok
Source: University of Maryland