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# ENGA3005: Structural Dynamics and Aeroelasticity Assessment

Order Code: CLT209501-4
• Subject Code :

ENGA3005

• University :

De Montfort University Leicerster

• Country :

United Kingdom

Introduction

Lightweight structures offer many feasible design features for future fuel efficient, environmentally friendly aircraft to help to deliver on the decarbonization strategy. However,  the use of lightweight structures is constrained by aeroelastic effects such as flutter, static divergence and control surface reversal, etc. This assignment is designed to provide you with the practical understanding of static/dynamic aeroelastic analysis using two-system coupling and analytical approaches.

Task 1: Explain what the static and dynamic aeroelasticity are using the Collar’s triangle.

Task 2: static aeroelastic analysis of an airfoil section: Elastic twist

1) Use a diagram to explain what the two-system coupling strategy is?

NOTE: You will need to explain what the two systems are, and how to couple the two systems for static  aeroelastic analysis using a diagram.

2) An airfoil section is elastically mounted on a torsional spring as shown in Figure 1. Flow  conditions and structural parameters are given in table 1.

a) Implement the two-coupling strategy in MATLAB to compute the elastic twist for the aeroelastic system and validate your code by comparing your results with the analytical solution for a range of freestream velocity by assuming constant torsional spring stiffness, and linear aerodynamics.

NOTE: You will need to compute and compare your results for three freestream velocities.

b) Explore how to reduce the elastic twist using the MATLAB program you developed.

Task 3: Dynamic aeroelastic analysis of an airfoil section: Flutter onset

1) What is flutter and explain why it is an important design consideration in future aircraft design?

2) A pitch/plunge aeroelastic system is shown in Figure 2, and the flow conditions and structural parameters are given in table 2.

a) Write a MATLAB function and convert the EOM of the structural system into a state space model.

b) Assuming the elastic centre is at a quarter chord, develop a MATLAB program to construct the aeroelastic system in a state space formulation using Theodorsen theory to predict flutter onset Mach number.

NOTE: You will need to plot the eigenspectrum as a function of Mach number, and the structural  response at the flutter onset.

c) Explore how the position of the elastic centre influences the flutter onset using the MATLAB program you developed.

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• Uploaded By : Katthy Wills
• Posted on : February 15th, 2023
• Views : 219

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