Tfaws05 Rbond Afd
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Transcript of Tfaws05 Rbond Afd
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Aerothermal Capabilities atSandia National Laboratories
Ryan Bond
Don Potter
Dave Kuntz
Adam Amar
Justin Smith
Aerosciences and Compressible
Fluid Mechanics Department
Thermal and Fluids Analysis Workshop
August 9, 2005
Orlando, Florida
Approved for unlimited release as SAND 2005-4513P
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Aerothermal
Flight Vehicle Support
More than 100 Instrumented RV/RBsflown (1968-present)
7 Carbon-Carbon vehicles
6 RVs soft recovered
10 RVs on 9 AOs [USAF;MM III & PK] 9 RBs on 4 DASOs [USN]
Most vehicles, One-of-a-kind, unique
R & D tests
High risk, excellent track record
[>96% of flight test objectives
satisfied]
SAMAST/MINT
All Carbon-Carbon
Vehicle
NASA SHARP-B01
Vehicle
MaST Recovery
Vehicle
MaSTPayload
Minuteman Launch
from VAFB
GRANITE
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Presentation Topics
A x ia l P o s i tio n ( in )0 1 2 3 4 5 6
3 4 0 0
3 2 0 0
3 0 0 0
2 8 0 0
2 6 0 0
2 4 0 0
2 2 0 0
2 0 0 0
1 8 0 0
1 6 0 0
1600
1500
1400
1300
1200
1100
1000
900
800
700600
Temperature
Time
Measurement, 0.025 in.
Measurement, 0.100 in.
Calculation, 0.025 in.
Calculation, 0.100 in.
AerothermalAnalysis Tools
Aerothermal FlightVehicleInstrumentation
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Aerothermal
Analysis Tools
Flowfield/Aerodynamic Heating
Material Thermal Response
Nosetip Heating/Ablation
RF Attenuation
Analysis Tools Currently Under Development
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Flowfield/Aerodynamic
Heating Codes
HANDI Set of correlations for computing heating on several
standard geometries (spheres, flat plates, cylinders, . . .)
BLUNTY Correlation-based heating code for sphere-cone
geometries
Ideal for trade studies and quick investigations
2IT/SANDIAC/HIBLARG Set of inviscid/integral boundary layer codes
Used for spherically-capped analytical geometries atangle-of-attack
SACCARA Finite-volume Navier-Stokes code
Used for obtaining flowfield solutions on complexgeometries at all speed ranges
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Material Thermal
Response Codes
Charring Materials Ablation code (CMA)
One-dimensional code with in-depth decomposition
Q* and equilibrium chemistry ablation models available
Sandia One-Dimensional Direct and Inverse Thermal code
(SODDIT)
One-dimensional code with direct and inverse capabilities
Q* and equilibrium chemistry ablation models available
Radiation gap model included
Ablating Version of COYOTE
Two and three-dimensional finite element code modified to include
aeroheating and ablating boundary conditions and moving mesh
capabilities for modeling surface recession
Used as both production tool and research tool for investigating
coupling approaches for aerothermal problems
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Material Thermal
Response Codes
Sample Results:
Reentry vehiclethermal response
Heating computed
with 2IT/SANDIAC/
HIBLARG
Heatshield responsecomputed with CMA
Tem
perature
Time
Measurement, 0.025 in.
Measurement, 0.100 in.Calculation, 0.025 in.
Calculation, 0.100 in.
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Material Thermal
Response Codes
Sample Results:
Hypersonic vehiclecontrol fin thermal
response
Heating computedwith HANDI
Fin thermal responsecomputed with the
ablating version of
COYOTE
1600
1500
1400
1300
1200
11001000
900
800
700
600
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Material Thermal
Response Codes
Sample Results: Coupled Ablation / Material Thermal Response
X
Y
Z1500
1400
1300
1200
1100
1000
900
800
700
600
500
400
300
200
100
0
qconv
(W/cm2)
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Nosetip Heating/Ablation
ABRES Shape Change Code (ASCC86)
Inviscid flowfield computed with correlations andengineering-based approaches
Heating computed with Momentum/Energy Integral
Technique (MEIT)
Steady state and transient conduction options available
Ablation computed with an equilibrium chemistry model
Numerous atmospheres and transition models available
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Nosetip Heating/Ablation
ASCC Sample Solution
Axial Position (in)0 1 2 3 4 5 6
220kft
100kft
76 kft
56 kft
43 kft
28 kft
16 kft
- Ablated Shape
Axial Position (in)0 1 2 3 4 5 6
3400
3200
3000
2800
26002400
2200
2000
1800
1600
- Temperature Contours
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RF Attenuation
Poly-Iterative Reacting Aero-Thermal Evaluation (PIRATE)
Performs iterative thermal response analysis until body surfacetemperature convergence is reached over the entire trajectory
Calls numerous aerothermal codes including:
TAOS/SIXDOF- Trajectory simulation program
BLUNTY - Reference boundary layer heating
(used in iterative process)
2IT/SANDIAC/HIBLARG - Reference boundary
layer heating
BLIMP - Reacting boundary layer blown
heating
ACE Surface chemistry
CMA - Thermal response
EMLOSS - Plane wave plasma
interaction
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Analysis Tools Currently
Under Development
Advanced Simulation and Computing (ASC)
Codes
Premo Compressible Fluid Mechanics Code Full Navier-Stokes capability
Unstructured mesh
Equilibrium and finite-rate chemistry (under development)
Calore Conduction Code
Unstructured mesh finite element conduction code
Aeroheating and ablating boundary conditions (underdevelopment)
ASC code architecture will allow communication
between Premo and Calore for coupledaeroheating/material thermal response solutions
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Analysis Tools Currently
Under Development
High Speed Tool for Computing Aeroheating on
Arbitrary Geometries
New capability currently under development will couple
Premo (inviscid solutions) with SAPHIRE (boundary
layer solutions)
Coupled set of codes will permit rapid heating solutions
to be computed on complex, non-spherically-capped
geometries
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Analysis Tools Currently
Under Development
Chaleur
1-D Material Thermal Response Code
Planar, Cylindrical, and Spherical
Geometries
Q* and Equilibrium Chemistry AblationModels
Aerodynamic Heating Capability
In-Depth Decomposition
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Analysis Tools Currently
Under Development
Chaleur (cont.)
Differences from (Improvements over) CMA
Residual Formulation of Governing Equations
Control Volume Finite Element SpatialDiscretization
Implicit and Trapezoidal Time Integrators
Contracting Grid Scheme Nonlinear Iteration on Entire Equation Set
No thermal property or surface recessionrate lag
Continuity Equation and Porous FlowMomentum Equation
Predicts pressure in porous char layer
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Flight Vehicle
Thermal Instrumentation
Thermocouple Plugs
Acoustic Recession Gages
Photodiode Transition Indicators
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Flight Vehicle
Thermocouple Plug
Typical Thermocouple Plug
Tungsten-5% Rhenium vs. Tungsten-26% Rhenium
thermocouples
Published voltage output values up to 4,660 oR
Up to three thermocouples per plug
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Flight Vehicle
Thermocouple Plug
Typical Plug Design:
Heatshield Material Plug, 0.375 Dia
T/C Hole, 0.0145 Dia, 0.2 Deep
T/C Groove, 0.015 Wide, 0.047 Deep
Enlarged Hole for Wire Junction
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Flight Vehicle
Thermocouple Plug
All Dimensions in InchesThermocouple Design:
T/C Junction
Boron Nitride Potting
T/C Wire, 0.0007 Dia
Quartz Double Bore Tubing, 0.003 OD
Tantalum Sheath, 0.008 OD
Ceramic Potting
Compensated Lead Wire
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Flight Vehicle
Thermocouple Plug
Installation: Heatshield Material
T/C Plug
Insulation Substructure
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Flight Vehicle
Thermocouple Plug
Sample Flight Data
Temperatu
re
Time
Measurement, 0.025 in.
Measurement, 0.100 in.
Calculation, 0.025 in.
Calculation, 0.100 in.
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Flight Vehicle
Nosetip Recession Gage
Acoustic Recession Gage
Used successfully on nosetips, antenna windows, and flaps
Transducer mounted directly on the back face of the
ablating material
Acoustic wave transmitted by the transducer and reflected
off the ablating surface
Acoustic time of flight used to determine instantaneous
ablator thickness
Fli ht V hi l
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Flight Vehicle
Nosetip Recession Gage
Nosetip recession measured acoustically
Ultrasonic Module
On-Board
Processor
Telemetry System & Digitizer
Control Logic
&
Master Clock
Memory
Averaging
& Slow Rate
Write to the DAC
DACstretched
waveforms
AnalogSignal
Output forOne
TelemetryChannel
On-Board Processor for Each Telemetry Channel
ToTransducer
Group
Pulser/ReceiversMultiplexer &
Digitizer
Transmitted toGround Stations
Nosetip
Fli ht V hi l
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Flight Vehicle
Nosetip Recession Gage
Sample Waveform:
nt the A-scan waveform byity modulated line where
e bright and troughs are
A-scan waveform of aft Flap 1
Mainbang & ringdown Thickness echo
Fli ht V hi l
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Flight Vehicle
Photodiode Transition Indicator
Photodiode Transition Indicator
Optical technique for determining boundary layertransition
Photodiode mounted beneath a transparent quartz window
Voltage across a resistor used as the photodiode signal
Technique would require additional development to be usedagain
Flight Vehicle
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Flight Vehicle
Photodiode Transition Indicator
Photodiode Transition Indicator Hardware
Flight Vehicle
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Flight Vehicle
Photodiode Transition Indicator
Sample Flight Data
Summary
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Summary
Sandia has extensive hypersonic
and reentry vehicle flight testing
experience
Analysis capabilities exist which
cover nearly all aspects of vehicle
aerothermal performance
Sandia has developed and worked
with numerous types of flight
vehicle instrumentation for measuring
aerothermal characteristics during flight