physics-infused differential-algebraic reduced-order
TRANSCRIPT
APUS LabAerospace multi-Physical andUnconventional Systems
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Physics-InfusedDifferential-Algebraic Reduced-Order Modelsfor Multi-Disciplinary SystemsCarlos Vargas Venagas and Daning Huang
LLNL Machine Learning for Industry Forum, August 10-12, 2021
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BackgroundHypersonic Aerothermoelasticity
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Barrier to fly at Hypersonic speed
Aerothermoelasticity
SR-72Image source: Lockheed Martin
Aerothermoelastic response of a 2D skin panel
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As a Multi-disciplinary system
Hypersonic Aerothermodynamics
Heat Conduction
StructuralDynamics
Heat flux
Temperature Deformation
Pressure
Temperature
Deformation
โข Real gas effectโข Viscous interactionโข Compressible turbulence
โข Thermal managementโข Material degradationโข Charring and ablation
โข Flutter and bucklingโข Fatigue and creepโข Reliability assessment
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Challenge to analyze, optimize, control such systemsโฆ
Example:Aerothermal Subproblem
States >109
e.g. flow states
๏ฟฝฬ๏ฟฝ = ๐ ๐, ๐; ๐๐ = ๐(๐, ๐; ๐)
Input ~103
e.g. thermoelastic response,control commands
Output ~103
e.g. aerothermal loads
Parameters ~103
e.g. geometrical configuration
High computational cost Vast design space
High-dimensionaloptimal control laws &uncertainty quantification
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What are the options?Functional form ofpredictive model
Generalizability tosystem parameters Computational cost
Physics (+ Data) High High
Physics Mid Mid
Physics + Data High? Low?
Data Mid Low
Data Low Low
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FormulationPhysics-Infused Reduced-Order Modeling
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General Idea
ร Full-Order Model (FOM)
ร Low-Order Model โ First principle, much less states
ร Physics-Infused Reduced-Order Model
๏ฟฝฬ๏ฟฝ = ๐ญ ๐, ๐; ๐๐ = ๐ฏ(๐, ๐; ๐)
0 = ๐ ๐, ๏ฟฝฬ๏ฟฝ, ๐, ๐; ๐๐ = ๐(๐, ๐; ๐)๐ = ๐(๐, ๐, ๐; ๐)
0 = ๐ ๐, ๏ฟฝฬ๏ฟฝ, ๐, ๐; ๐๐จ๏ฟฝฬ๏ฟฝ = 4๐(๐, ๐, ๐; ๐)๐ = ๐(๐, ๐, ๐; ๐)
Examples Boundary layer Slender structure
Full-order Navier-Stokes Eqn. Elasticity Eqns.
States Density, velocity, energy 3D displacement field
Low-order Momentum integral Eqn. Euler-Bernoulli Eqn.
State variables BL thicknesses 1D disp. field
Aux. variables Shape factor, Skin friction Bending stiffness
ร Differential-algebraic Eqn.ร Auxiliary variables
0 = ๐ ๐, ๏ฟฝฬ๏ฟฝ, ๐, ๐; ๐๐จ๏ฟฝฬ๏ฟฝ = 4๐(๐, ๐, ๐; ๐; ๐ฏ)๐ = ๐(๐, ๐, ๐; ๐)ร Augmented form
๐จโ, ๐ฏโ = argmin๐จ,๐ฏ ๐"#$ โ ๐
s.t.
ร DAE-constrained optimization
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Back to Hypersonic aerothermodynamicsFirst-principle modeling: Turbulence Viscous-Inviscid Interaction (TVI)
โข Classical integral equations that respect physics
โข A system of differential-algebraic equations (DAEs)
โข But misses some physics, e.g. High-temperature effects
๐๐๐ฅ
๐ฟโ
๐ป+ ๐ป"
๐#๐$โ 4
๐ฟโ
๐ป๐%
๐๐%
๐๐ฅ=๐ถ&2
๐% ๐ฅ = ๐' 1 +๐พ โ 12
๐'๐๐ฆ%๐๐ฅ
())*+
๐ฆ% = ๐ฆ# + ๐ฟโ
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Casting to state-space formFirst-principle modeling: Turbulence Viscous-Inviscid Interaction (TVI)
โข Classical integral equations that respect physics
โข A system of differential-algebraic equations (DAEs)
โข But misses some physics, e.g. High-temperature effects
Aux. variables:
โข Shape factor
โข Skin friction coefficient
โข Pressure ratio
Output variables:
โข Surface pressure
โข Surface heat flux
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Creating the PIRO modelFirst-principle modeling: Turbulence Viscous-Inviscid Interaction (TVI)
โข Classical integral equations that respect physics
โข A system of differential-algebraic equations (DAEs)
โข But misses some physics, e.g. High-temperature effects
Model augmentation by functional correction
โข To account for missing physics -
โข Taking an algebraic multiplicative form
โข A new DAE with unknown functions
Learn unknown functionals from data
โข Learn corrections by a DAE-constrained optimization
โข Works for computational (RANS/LES/DNS) or experimental data
โข Captures more physics and is interpretable!
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Methodology Overview
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Stage 0: RANS Solutions
Computational Grid
ThermoelasticResponseFlow conditions
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Stage 1: Solving Inverse Problems
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Stage 1, 1/2: Sampling inputs & parameters
Deformation:
Wall temperature:
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Stage 1, 2/2: DAE-Constrained Optimization
Example: M76D5-100%
๐ฒ ๐ฑ ๐ฎ ๐ฝ ๐ท๐๐,๐ ๐ฑ๐ ๐๐,๐ ๐ฝ๐,๐ ๐ท๐,๐
๐๐,๐ ๐ฑ๐ ๐๐,๐ ๐ฝ๐,๐ ๐ท๐,๐๐๐,๐ ๐ฑ๐ ๐๐,๐ ๐ฝ๐,๐ ๐ท๐,๐
๐๐,๐ ๐ฑ๐ ๐๐,๐ ๐ฝ๐,๐ ๐ท๐,๐
๐๐,๐ ๐ฑ๐ ๐๐,๐ ๐ฝ๐,๐ ๐ท๐,๐
๐๐,๐ ๐ฑ๐ ๐๐,๐ ๐ฝ๐,๐ ๐ท๐,๐
Training Dataset
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Stage 2: Functional Representation of Correctors
20Going fancier, we could use tools like symbolic regressionto get analytical expressions for the correction terms!
Stage 2: Machine Learning
๐ฒ ๐ฑ ๐ฎ ๐ฝ ๐ท๐๐,๐ ๐ฑ๐ ๐๐,๐ ๐ฝ๐,๐ ๐ท๐,๐
๐๐,๐ ๐ฑ๐ ๐๐,๐ ๐ฝ๐,๐ ๐ท๐,๐๐๐,๐ ๐ฑ๐ ๐๐,๐ ๐ฝ๐,๐ ๐ท๐,๐
๐๐,๐ ๐ฑ๐ ๐๐,๐ ๐ฝ๐,๐ ๐ท๐,๐
๐๐,๐ ๐ฑ๐ ๐๐,๐ ๐ฝ๐,๐ ๐ท๐,๐
๐๐,๐ ๐ฑ๐ ๐๐,๐ ๐ฝ๐,๐ ๐ท๐,๐
Training Dataset
Gaussian Process Regression (GPR)
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Stage 3: Reconciling Trade-off
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Demo: New response, New flow conditionsDisplacement: ๐ฆ1 ๐ฅ = 0.6 ๐ฆ12 ๐ฅ + ๐ฆ13 ๐ฅ /2Wall temperature: ๐1 ๐ฅ = ๐456 + 0.7 ๐12 ๐ฅ + ๐13 ๐ฅ /2Mach number: ๐ = 7.5
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ApplicationBack to Hypersonic Aerothermoelasticity
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Benchmark case for aerothermoelasticity
Aerothermoelastic response of a 2D skin panel
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HYPATE-X: HYPersonic AeroThermoElastic eXtended
Reduced Order Modelsโข Tradeoff between Accuracy & Model Complexityโข Convex Optimization + Dynamic System Theoryโข Parametric Sensitivity Analysis
Aero-Thermal-Acoustics Servo-Thermoelasticity
Linear Time-Varying Model for Tangent SubspaceSparse Learning for Model Refinement
Multi-Fid. Gaussian Proc. Regr.
Physics-Infused ROM
Aerothermodynamics Thermoelasticity Rigid Body Dynamics
Analytical Models
Unsteady RANS
Large Eddy Simulation
Galerkin-based/Finite-difference
Fully Nonlinear Solid FEM
Geometrically Nonlinear Shell FEM Euler-LagrangianDynamics
High Fidelity Modelsโข Time-Accurate Transient Analysisโข Long-Term Quasi Steady Analysisโข Linearized Stability Analysis
Existing modules
Developing modules
Collaborators:
โข Drs. P.P. Friedmann
and T. Rokita (UMich)
โข Drs. P. Singla and
X.I.A. Yang (PSU)
โข Dr. K.M. Hanquist
(UofAz)
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Accuracy of RANS at cost of milli-secs
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A closer look at the responses
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Enabling parametric study as well
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Key takeawaysSummary:o Presented the formulation of Physics-Infused Reduced-Order Modeling.o Demonstrated the methodology for a hypersonic aerothermodynamic application.o Comparing to conventional aerothermal surrogate:q Generalize well to operating conditions and thermoelastic responses not in the training data set.q Requires <102 samples for any response, v.s. 103-104 samples ร Much less samplesq Computational cost 90 ms, v.s. 50 ms ร Similar computational efficiency
Future Work:o Extend the methodology for general DAE problems โ Open to collaborations!o Develop a general framework for systematic creation of physics-infused ROM.o Couple to frameworks of multi-disciplinary optimization.