This document discusses vibration in aircraft structures like wings through an experiment using a beam apparatus. The objectives are to determine the stiffness and damping properties of the beam system and study how vibration behavior changes with conditions. It motivates this by explaining how aircraft flutter from vibration can cause structural failure if frequencies match excitation frequencies. It introduces vibration concepts and modeling a wing as a simplified beam system with lumped mass, stiffness, and damping to analyze. The apparatus allows simulating beams in free and damped vibration.

1. 2145-392 Aerospace Engineering
Laboratory II
Vibration of Beam
by NAV
2145-392 NAV 2013 1

2. Vibration of Beam
 1. Motivation
 2. Introduction/Theory
 3. Objectives
 4. Apparatus
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3. 1. Motivation
Aircraft Vibration
 Engine
 Pump
 Landing gear extension and retraction
 Extension of speed brakes
 Wing
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 Normal? Low Vibration, background noise, turbulence
 Abnormal? Engine rotor imbalance, malfunction of
mechanical equipment, and airflow disturbances acting
over doors

4. Aircraft Wing Vibration
 Wing Fluttering
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• Flutter is an unstable condition in which unsteady
aerodynamics excite near or at the natural frequencies of
the structure over which the air flows.
• The resulting vibrations can grow to a magnitude that
causes the structure to fail.

5. Aircraft Wing Vibration
 If the aircraft’s structure is low damped, it means that the various
natural frequencies of different parts of the aircraft’s structure do
not dampen out and thus can ‘flutter’.
 In worst case scenarios flutter is a potentially dangerous
condition in which the vibrations of various parts of the structure
become divergent – leading to structural failure
 Flutter testing is important as it evaluates the aircraft’s stability
and dampening modes at limit speeds and high altitude
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6. 2. Introduction/Theory
Vibration is the branch of engineering that deals
with repetitive motion of mechanical systems.
Examples:
 engineering structure to earthquakes
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7. 2. Introduction
Vibration Related Examples:
 unbalanced rotating machine -> shut-down, failure
 plucked string of a musical instrument -> sound
 ride quality of an automobile or motorcycle -> stiff,
smooth
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8. 8
Only the most important features are considered in the
analysis to predict the behavior of the system under
specified input conditions.
The analysis of a vibrating system usually involves
 Step 1: Physical modeling
 Step 2: Mathematical modeling = derivation of the
governing equations
 Step 3: Solving the equations
 Step 4: Interpreting of the results (numerical, graphical,
etc).
Can we go backwards? Graphical results  equation?
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2. Theory

9. 9
Three basic elements in a simplified vibrating system
 the element restoring or releasing KE
 mass or a mass moment of inertia
 the element restoring or releasing PE
 an elastic component or a spring
 the element dissipating energy
 Damper
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2. Theory

10. 10

 These elements are related to the behaviors of the
system subjected to various kinds of excitation
 To analyze the vibration problem, the quantities of these
elements must be determined via some measurements.
 The natural/resonance frequencies are then calculated.
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2. Theory

11. 11
How important are these quantities?
When the excitation frequency meets the
resonance frequency / when the excitation is
large
 BIG vibration
 Structural Failure
See movies
 The Chinook resonances
 The MD-80 landing
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2. Introduction

12. 12
3. Objectives
 To determine values of the basic quantities of a
simplified beam system i.e. the stiffness of the
spring and the damping coefficient of a damper
through experiments by observing the time
response [displacement vs time graphs].
 To study the vibration behavior of the system
when the conditions/parameters vary.
 Ultimate goal: To understand the vibration
characteristics of a simplified aircraft wing and
apply the understanding to (partially) design of
wing structure 2145-392 NAV 2012

13. 13
Modeling
Wing flutters due to excitation e.g. from wind
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Simplify the model of the wing as a beam
Continuous system with structural stiffness and
damping
Physical model turns into a math model with a
governing partial differential equation
Simplify more and make the mass “lumped”
together
Simplify even more to get one rigid beam
pivoted at the end with a spring and a damper

14. 14
4. Apparatus
The vibration testing apparatus
“Universal Vibration”
It represents physical plants
including rigid and flexible beams
subjected to an unbalance force
available free and damped
vibration.
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