Aerodynamics
Boyd, Gamba, Raman, Roe
Materials
Boyd, Sodano,
Sundararaghavan
Structures
Cesnik, Friedmann
Propulsion
Driscoll, Gamba, Raman
Guidance, Navigation
& Control
Kolmanovsky, Cesnik
Hypersonics Research Capabilities
At the University of Michigan
Integrated Vehicle Analysis
Cesnik, Driscoll, Friedmann
Hypersonic AerodynamicsBoyd, Gamba, Raman, Roe
Computational Aerothermochemistry
CFD Validation
Mach 12 flow tested at CUBRC, computed with
UM hypersonic flow code LeMANS
Trajectory calculations on potential energy surfaces
provide temperature dependent rates for CFD
Turbulence
CFD Analysis of Vehicles
Mach 20, 40 km altitude
11-species air
Quantum-to-continuum workflow and unsteady
highly parallel solvers
Hypersonic PropulsionDriscoll, Gamba, Raman
CFD capabilities
Dual-mode ramjet/scramjet studies
Combustion modeling and
complex geometry simulations
Direct numerical and large eddy
simulations enable reduced-
order modeling
Hypersonic facilities & diagnostics
Isolator studies
A combination of direct-connect ramjet/scramjet engine
and high-enthalpy hypersonic facilities are used to access
relevant conditions
Investigation of combustion properties and
dynamics using modern laser diagnostics
Cavity stabilized dual-mode studies
Isolator performance,
dynamics & control
Rapid end-to-end
simulations from
CAD to results
• From ab-initio to continuum mechanics
• State-of-the-art combustion modeling, including
complex detailed chemistry and non-equilibrium
Hypersonic StructuresCesnik, Friedmann
Computational Aerothermoelasticity
CFD-based transient simulation
High-fidelity fully-coupled solution to reveal the
mechanism of aerothermoelastic instability
Multi-fidelity
computational
framework for
fluid-
structural-
thermal
interaction
Aerothermoelastic Scaling Law
ROM-based quasi-steady simulation
“Two-pronged” approach:
Analytical derivation +
numerical simulation &
optimization
Novel ROM techniques and coupling schemes for
faster-than-real-time simulation
Deformation Temperature
Hypersonic MaterialsBoyd, Sodano, Sundararaghavan
Thermal Protection Systems
Fabrication and Experimental Testing of TPS
Ablation Resistant Tiles for Launch and Reentry
Effect of hypersonic flow on an ablating TPS
Ceramic Composites/Coatings
Multiscale modeling
Oxidation of Carbon Fiber in a Ceramic Matrix Composite
Intact carbon
fiber
Partially oxidized
fiber
Tows
Oxygen density distribution
Atomistic to continuum scale modeling for heat shield materials
Model predictive control guidance
Real-time trajectory optimization for time-optimal way
point following subject to exclusion zone, actuator,
structural and thermal constraints
Constrained flight control
Extended Command Governor (ECG) protects nominal
closed-loop system against critical constraint violation
• x-y trajectory, target sets
and exclusion zones
• flight path angle
and limits
• bank angle
and limits
• elastic deflections
and limits• ECG modifies set-points to
enforce constraints
Hypersonic Guidance, Navigation & ControlKolmanovsky, Cesnik
Control Design-oriented Modeling
State limits
LHS of x
ID state space Surrogate Training
SVD
0th order fit
1st order fit
2nd order fit
NRMSE
m-training samples
k-testing samples
min(x,u), max(x,u)
{x1,…,xs,u1,…,uq}
S
UΣRT
UΣVT
Completed
ROM
no
yes
dtraining
Error ≤ tol.
dtesting
SVD techniques to create nonlinear fully coupled models
for control design
Real-time Simulation
Hardware-software integration for RT simulation
Model predictive control guidance
Real-time trajectory optimization for time-optimal way point following subject to exclusion zone, actuator,
structural and thermal constraints
Constrained flight control
Extended Command Governor (ECG) protects nominal closed-loop system against critical constraint violation
• x-y trajectory, target sets and exclusion zones
• flight path angle and limits
• bank angle and limits
• elastic deflections and limits
• ECG modifies set-points to enforce constraints
Hypersonic Guidance, Navigation & Control Kolmanovsky, Cesnik
Control Design-oriented Modeling
State limits
LHS of x
ID state space Surrogate Training
SVD
0th order fit
1st order fit
2nd order fit
NRMSE
m-training
samples
k-testing samples
min(x,u), max(x,u)
{x1,…,xs,u1,…,uq}
S
UΣRT
UΣVT
Completed
ROM
no
yes
dtraining
Error ≤ tol.
dtesting
SVD techniques to create nonlinear fully coupled models for control design
Real-time Simulation
Hardware-software integration for RT simulation
Integrated Hypersonic Airframe Scramjet Model
for Aerothermoelastic DeformationFriedmann, Driscoll
Integrated Vehicle-Scramjet Model
Integrated Engine Performance
Engine performance
by MASIV: a 2D static
solver for the mean
flow path of the
propulsion system
Aerothermoelastic
deformations
interpolated to the
propulsion analysis
Thrust FX indicator of
aerothermoelastic
deformation of cowl on
engine performance
Integrated vehicle-engine flow
path consists of: elongated
forebody, isolator, combustor
and exit nozzle
Aerothermoelastic deformation
of cowl governs thrust
Conjugate Heat Transfer (CHT)
Uncertainty Quantification (UQ) of Performance
Cowl
For constant mass flow the
deflection of the cowl leading
edge is dominant and changes
performance by up to 20%
Cowl deformation is more
important than change in angle
of attack; therefore control
strategy plays a significant
role for performance
Simultaneous solution of Navier-Stokes equations and
structural heat transfer on undeformed vehicle
Fx
MASIV: Michigan AFRL Scramjet In Vehicle