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