tutorial on nonlinear modal analysis of mechanical systems · tutorial on nonlinear modal analysis...
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![Page 1: Tutorial on Nonlinear Modal Analysis of Mechanical Systems · Tutorial on Nonlinear Modal Analysis of Mechanical Systems Gaëtan Kerschen Aerospace and Mechanical Eng. Dept. University](https://reader034.vdocuments.mx/reader034/viewer/2022042103/5e810e27de062620d32bb8c3/html5/thumbnails/1.jpg)
Tutorial on Nonlinear Modal Analysis of
Mechanical Systems
Gaëtan Kerschen
Aerospace and Mechanical Eng. Dept.
University of Liège, Belgium
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Belgium ?
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University of Liège ?
Founded in 1817 (Belgium was not existing yet !)
All disciplines covered
17000 undergraduate students
2000 graduate students
500 faculty members.
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Aerospace and Mechanical Engineering Dept.
Aerospace
Materials
Energetics
Biomechanics
Computer-Aided Eng.
Facts and figures:
25 Professors
85 researchers
15 staff members
5 Masters, among which the Master
of Aerospace Engineering
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Space Structures & Systems Laboratory (S3L)
Nonlinear dynamics
Spacecraft structures
Orbital mechanics
Nanosatellites
Facts and figures:
1 Professor
5 Postdoc, 6 PhD students, 1 TA
Collaborations: UIUC, Torino, VUB, LMS
Financial support: ERC, ESA, FNRS
BELSPO
System ID & modal analysis
Constructive utilization of NL
Bifurcation analysis & management
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Linear ?
A linear system has an output that is directly proportional
to input.
Superposition principle: cornerstone of linear theory
A X
B Y
A+B X+Y LIN
LIN
LIN
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Nonlinear ?
A nonlinear system is a system that is not linear.
Most physical systems are inherently nonlinear in nature !
(Navier-Stokes, planetary motion, rigid body rotation, etc.)
A X
B Y
A+B ??? NL
NL
NL
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Why Care About Nonlinearity in Structural Dynamics?
1. Nonlinear dynamics is fun !
2. Nonlinear dynamics is complex.
3. There are industrial needs.
1. Meet escalating performance.
2. Nonlinearities are pervasive.
3. Nonlinearity may reveal damage.
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Two Examples in Aerospace Engineering
SmallSat spacecraft
Collaborators:
J.B. Vergniaud @ EADS-Astrium,
B. Peeters @ LMS,
A. Newerla @ ESA.
Morane-Saulnier MS760
Collaborators:
C. Stephan @ ONERA,
P. Lubrina @ ONERA.
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Outline of the Presentation
Sources of nonlinearity
(with real-life examples)
Fundamental differences between
linear & nonlinear dynamics
What about nonlinear modes ?
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5 main assumptions for
Small vibrations around
an equilibrium
Small displ. and rotations
Mechanical vibrations
→ nonlinear boundary conditions
→ geometric nonlinearity
→ inherently nonlinear forces in
multiphysics applications
Mx (t) + Cx (t) + Kx(t) = f(t)
Linear elasticity → nonlinear materials
(hyperelastic, plasticity)
Linear Systems in Structural Dynamics
Viscous damping → nonlinear damping mechanisms
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Nonlinear Materials: Elastomers, Foams, Rubber
Impact of elastomeric engine mounts
on A-400 M engine roll mode
J.R. Ahlquist et al., IMAC 2010
Airbus Military
Decrease in
stiffness
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Geometric NL: Large Displacements/Rotations
Thin beam activated in large
displacements
Force
Rel. displ.
Increase in
stiffness
Cantilever beam with a thin beam
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Combined Nonlinearity: Nonlinear BCs + Friction
Bolted connections between wing
tip and external fuel tank. Paris aircraft @ ONERA (France)
Force
Rel. displ.
Decrease in
stiffness
5 60-4
0
FRF (dB)
Frequency (Hz)
Low excitation level
High excitation level
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Outline of the Presentation
Sources of nonlinearity
(with real-life examples)
Fundamental differences between
linear & nonlinear dynamics
What about nonlinear modes ?
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Superposition principle
Linear Nonlinear
Uniqueness of the solutions
x2 x2
Invariance of FRFs and of
modal parameters
NO ! By definition …
NO ! Freq.-energy dependence
NO ! Steady state response
depends on transient
response
Bifurcations, quasi-periodicity
and chaos.
+
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Superposition Principle (Linear Case)
0 0.03 0.05 0.10
0.3
0.7
Force F (N) with ω=1.1 rad/s
𝑥 + 0.05𝑥 + 𝑥 = 𝐹𝑠𝑖𝑛𝜔𝑡
Displ. x
(m)
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No Superposition Principle (Nonlinear Case)
0 0.03 0.05 0.10
0.3
0.7
Force F (N) with ω=1.1 rad/s
𝑥 + 0.05𝑥 + 𝑥 + 𝑥3 = 𝐹𝑠𝑖𝑛𝜔𝑡
𝑥 + 0.05𝑥 + 𝑥 = 𝐹𝑠𝑖𝑛𝜔𝑡
Discontinuous
behavior, potentially
dangerous in practice Displ. x
(m)
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0 100
0.1
1.5
Time (s)
𝑥 + 0.05𝑥 + 𝑥 + 𝑥3 = 0.15 𝑠𝑖𝑛 1.6𝑡
𝑥 0 = 0, 𝑥 0 = 0 𝑥 0 = 0, 𝑥 0 = 2
x15
Displ. x
(m)
Non-Uniqueness (Sensitivity to Initial Conditions)
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350 400
-0.8
-0.1
0.1
0.8
Marked Sensitivity to Forcing (→ Jump)
Time (s)
𝑥 + 0.05𝑥 + 𝑥 + 𝑥3 = 0.05 𝑠𝑖𝑛 1.22𝑡
x8
𝑥 + 0.05𝑥 + 𝑥 + 𝑥3 = 0.05 𝑠𝑖𝑛 1.24𝑡
Displ. x
(m)
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How to Compute the “FRFs” of a Linear System ?
𝑥 + 𝑥 = 𝐴𝑠𝑖𝑛 𝜔𝑡
𝑥(𝑡) = 𝐵𝑠𝑖𝑛 𝜔𝑡
−𝜔2𝐵 + 𝐵 = 𝐴
𝐵 =𝐴
1 − 𝜔2
Confirmation of the
superposition principle
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How to Compute the “FRFs” of a Nonlinear System ?
𝑥 + 𝑥 + 𝑥3 = 𝐴𝑠𝑖𝑛 𝜔𝑡
𝑥(𝑡) = 𝐵𝑠𝑖𝑛 𝜔𝑡
−𝜔2𝐵𝑠𝑖𝑛 𝜔𝑡 + 𝐵𝑠𝑖𝑛 𝜔𝑡 +𝐵3𝑠𝑖𝑛3𝜔𝑡 = 𝐴𝑠𝑖𝑛 𝜔𝑡
𝑠𝑖𝑛3𝜔𝑡 = (3𝑠𝑖𝑛 𝜔𝑡 − 𝑠𝑖𝑛 3𝜔𝑡)/4
Nonlinear relation
between B and A
𝑥 𝑡 = 𝐵𝑠𝑖𝑛 𝜔𝑡 + 𝐶𝑠𝑖𝑛 3𝜔𝑡
Solution: infinite series of
harmonics
OPTION 1: EXACT OPTION 2: APPROXIMATION
−𝜔2𝐵𝑠𝑖𝑛 𝜔𝑡 + 𝐵𝑠𝑖𝑛 𝜔𝑡 + 3
4𝐵3𝑠𝑖𝑛 𝜔𝑡 = 𝐴𝑠𝑖𝑛 𝜔𝑡
Solve a third order
polynomial
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Key Feature of Nonlinear Systems: Bifurcations
Pulsation ω (rad/s)
𝑥 + 0.05𝑥 + 𝑥 + 𝑥3 = 𝐹𝑠𝑖𝑛𝜔𝑡
0.6 1 1.1 1.5 2.20
1
1.8
3 solutions 1 solution 1 solution
Displ. x
(m)
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FRF Peak Skewness Perturbs Linear Modal Analysis
Introduction of two stable poles around 1 nonlinear mode.
B. Peeters et al., IMAC 2011
Polymax applied to F-16
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0.6 1 1.1 1.5 2.20
1
1.8
F=0.01 N
F=0.02 N
F=0.05 N
F=0.1 N
F=0.15 N
Displ. x
(m)
Pulsation ω (rad/s)
𝑥 + 0.05𝑥 + 𝑥 + 𝑥3 = 𝐹𝑠𝑖𝑛𝜔𝑡
3. Sensitivity to forcing
(F=0.05N,
ω=1.22/1.24)
2. Sensitivity to
initial conditions
(F=0.15N, ω=1.6)
1. No superp.
(various F, ω=1.1)
Explanation of Previous Results
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Outline of the Presentation
Sources of nonlinearity
(with real-life examples)
Fundamental differences between
linear & nonlinear dynamics
What about nonlinear modes ?
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Objectives of This Third Part
Can we extend modal analysis to nonlinear systems ?
3. How do we extract NNMs from experimental data ?
1. What do we mean by a nonlinear normal mode (NNM) ?
2. How do we compute NNMs from computational models ?
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Normal Modes of Conservative Systems
Linear normal mode (LNM):
synchronous periodic motion.
Nonlinear normal mode (NNM):
synchronous periodic motion.
Rosenberg
(1960s)
0)()( tt qKqM
NDOF system: existence of at
least N families of periodic
solutions around the equilibrium.
Lyapunov
(1907)
0)()()( ttt NL qfqKqM
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Fundamental Difference Between LNMs and NNMs
LNMs
𝑞 1 + 2𝑞1 − 𝑞2 = 0
𝑞 2 + 2𝑞2 − 𝑞1 = 0
𝐴 = 𝐵, 𝜔1= 1 rad/s
𝐴 = −𝐵, 𝜔2= 3 rad/s
𝑞1,2 = 𝐴, 𝐵𝑐𝑜𝑠𝜔𝑡
NNMs are frequency-
amplitude dependent !
𝑞 1 + 2𝑞1 − 𝑞2 + 0.5𝑞13 = 0
𝑞 2 + 2𝑞2 − 𝑞1 = 0
𝜔1 ∈ 1, 2 rad/s
𝜔2 ∈ 3,+ ∞ rad/s
𝐴 = ±8 𝜔2 − 2 𝜔2 − 1
3 𝜔2 − 2
𝐵 =𝐴
2 − 𝜔2
𝑞1,2 ≅ 𝐴, 𝐵𝑐𝑜𝑠𝜔𝑡
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0.5 1 2 3-1.5
-0.5
0.5
1
4Initial conditions on displacements
Blue mass
Ora
ng
e m
ass
1 1
1 1
0.5
(cubic)
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It Is Necessary to Extend the Definition of an NNM
LNM: synchronous
periodic motion.
NNM: synchronous
periodic motion.
Rosenberg
(1960s)
Modal
interactions
NNM: periodic motion
(nonnecessarily synchronous).
0)()()( ttt NL qfqKqM 0)()( tt qKqM
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A Frequency-Energy Plot Is a Convenient Depiction
10-5
103
0
0.7
2DOF linear
Energy (J)
Frequency
(Hz)
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A Frequency-Energy Plot Is a Convenient Depiction
10-5
103
0
0.7
Energy (J)
Out-of-phase
NNM
In-phase NNM
0.28
0.16
Frequency
(Hz)
2DOF nonlinear
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LNMs and NNMs Have a Clear Conceptual Relation
10-5
103
0
0.7
2DOF linear
Energy
Freq.
10-5
103
0
0.7
2DOF nonlinear
Freq.
Energy
Frequency-energy dependence
Harmonics: modal interactions
Bifurcations: #NNMs > #DOFs
Bifurcations: stable/unstable modes
But …
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Practical Significance for Damped-Forced Responses
10
8
Ampl.
(m)
Freq. (rad/s)
1 1.30
2.5
Ampl.
(m)
Freq. (rad/s)
Locus of LNMs
for various
energies
Locus of NNMs
for various
energies
Linear: resonances occur
in neighborhoods of LNMs.
Nonlinear: resonances occur
in neighborhoods of NNMs.
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In Summary
Clear physical meaning
Important mathematical properties
Orthogonality
Modal superposition
Invariance
Structural deformation at resonance
Synchronous vibration of the structure
YES
YES
YES
YES
YES
LNMs
YES, BUT…
NO
NO
YES
YES
NNMs
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Practical Computation of NNMs
10-5
103
0
0.7
Frequency-energy plot Complex finite
element model
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Shooting and Pseudo-Arclength Continuation
Numerical integration
(Newmark)
t=0 t=T
z0, T zT, T
Newton-Raphson
10-5
103
0
0.7
Freq.
Energy
STEP 1: compute an
isolated periodic solution
Prediction tangent
to the branch
Correction to the
prediction
zp0
T
Energy
Freq.
10-5
103
0
0.7
STEP 2: compute the
complete branch ┴
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Shooting
Periodicity condition
(2-point BVP)
Numerical solution through iterations:
2n x 1 2n x 2n Monodromy matrix
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Numerical Demonstration in Matlab
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In-Phase and Out-of-Phase NNMs Connected
102
104
0.208
0.23
Energy (J)
Frequency
(Hz)
3:1 modal interaction
Out-of-phase
NNM
In-phase
NNM
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Neither Abstract Art Nor a New Alphabet
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MS760 Aircraft (ONERA)
Front connection
Rear connection
Bolted connections
between external fuel
tank and wing tip
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Finite Element and Reduced-Order Modeling
Finite element model (2D shells
and beams, 85000 DOFs)
Reduced model accurate in
[0-100] Hz, 548 DOFs
Condensation of the linear
components of the model
Craig-Bampton technique
8 remaining nodes
+
500 internal modes
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A Close Look at Two Modes
Wing bending
Wing torsion (symmetric)
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Wing Bending Mode not Affected by Nonlinearity
MAC = 1.00 MAC = 0.99
Frequency
(Hz)
Energy (J)
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Wing Torsion Mode Is Affected by Nonlinearity
9:1
MAC = 1.00
MAC = 0.98
31.1
30.4
10-4 104
Frequency
(Hz)
Energy (J)
3:1
5:1
Decrease of the natural
frequency
Internal resonances
Mode shape slightly
affected
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6th NNM of the Spacecraft
100
105
28.5
30
31.3
Energy (J)
Frequency
(Hz)
9:1
3:1
26:1
2:1 interaction
with NNM12
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6th NNM: From a Local Mode to a Global Mode
NNM6: local deformation at
low energy level
NNM6: global deformation at
a higher energy level
(on the modal interaction branch)
The top floor vibrates
two times faster !
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5 30 60 90-5.9
0
5.9
Excitation frequency (Hz)
Acc.
(m/s2)
90 60 5
3.3
5.4
Sine sweep
Accelerometer
at top floor
20N
80N
? 80N: large top floor motion
20N: no top floor motion
x4 x4
x4 x4
x4
30
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Experimental Confirmation
Accel.
Base excitation
(sine sweep)
5 10 20 30 40 50 60 70-100
-50
0
50
100
Excitation frequency (Hz)
Acc.
(m/s2)
0.1 g
1 g
No mode of the top floor in
this frequency range
?
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Experimental Identification of NNMs ?
Nonlinear phase separation: NO !
► If several modes are excited (arbitrary forcing and/or ICs),
extraction of individual NNMs is not possible generally, because
modal superposition is no longer valid in the nonlinear case.
► Because the NNMs attract the dynamical flow, in some cases,
the motion may end up along one dominant NNM.
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Experimental Identification of NNMs ?
If the motion is initiated on one specific NNM, the
remaining NNMs remain quiescent for all time.
Nonlinear phase resonance: YES !
► Excite a single NNM
► Exploit invariance principle:
► Identify the resulting modal parameters
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Two-Step Methodology
NNM free decay
Inducing single-NNM
free decay
Turn off the
excitation ON OFF
NNM force appropriation
Isolating an NNM motion using
harmonic excitation
Extract the
NNM
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Necessary Ingredients
1. Appropriate excitation to isolate one NNM
2. Modal indicator (are we on the NNM of interest ?)
3. Invariance principle
4. Wavelet transform and NNM extraction
Extraction of NNMs and their oscillation
frequencies directly from experimental data
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Nonlinear Phase Lag Quadrature Criterion
A nonlinear structure vibrates according to an NNM if the
degrees of freedom have a phase lag of 90° with respect to
the excitation (for all harmonics !).
Nonlinear mode
indicator function (MIF)
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Invariance Principle
If the motion is initiated on one specific NNM,
the remaining NNMs remain quiescent for all time.
Turn off the
shaker
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Wavelet Transform & NNM Extraction
Modal curves of NNMs:
► Extracted directly from the time series
Oscillation frequencies of NNMs:
► Extracted using the wavelet transform
Reconstructed FEP from experimental data:
► Compute energy and eliminate time
Frequency vs. time
Frequency vs. energy
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Experimental Demonstration
Experimental set-up:
► 7 accelerometers along the main beam.
► One displacement sensor (laser vibrometer) at the beam end.
► One electrodynamic exciter.
► One force transducer.
Beam with a geometrical nonlinearity;
benchmark of the European COST Action F3.
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Moving Toward the First Mode
Stepped sine
excitation
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Moving Toward the First Mode
Stepped sine
excitation
OK !
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Modal Indicator
OK ! Nonlinear mode
indicator function (MIF)
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The First Mode Vibrates in Isolation
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Frequency-Energy Dependence
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Modal shapes at
different energy levels
Frequencies
(wavelet transform)
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Validation of the Methodology
Modal curves Modal shapes
Acc
#7
Acc #3
Theoretical Experimental
Acc
Position along the beam
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Validation of the Methodology
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Concluding Remarks
Virtually all engineering structures are nonlinear …
but they may vibrate in linear regimes of motion.
Nonlinearity is not “plug and play”:
Code for NNM computation available online.
► Highly individualistic nature of nonlinear systems.
► Even weakly nonlinear systems can exhibit complex dynamics.
► No universal method; toolbox philosophy.
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Thank you for your attention.
Gaetan Kerschen
Aerospace and Mechanical Eng. Dept.
University of Liège, Belgium