Liquid Sloshing Behavior in Microgravity with Application ... · PDF fileLiquid Sloshing...
-
Upload
nguyenthuan -
Category
Documents
-
view
226 -
download
2
Transcript of Liquid Sloshing Behavior in Microgravity with Application ... · PDF fileLiquid Sloshing...
Liquid Sloshing Behavior in Microgravity with Application to
Spacecraft Propulsion Systems
Florida Institute of Technology
Department of Mechanical and
Aerospace Engineering
Gabriel Lapilli
Richard Schulman
Charles Holicker
Brian Wise
Sunil Chintalapati
Hector Gutierrez
Daniel Kirk
NASA Kennedy Space Center
Launch Services Program
Paul Schallhorn
Brandon Marsell
Jacob Roth
Massachusetts Institute of
Technology
Space Systems Laboratory
Dustin Hayhurst
David Miller
Alvar Saenz-Otero
Overview: Introduction
• Introduction
– Why Study Liquid Propellant Slosh?
– Sample Results
– Goal and Objectives
– ISS Slosh Experiment
• Slosh Experiment on the International Space Station
• Conclusions
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 2
Upper-Stage Propellant Modeling
http://www.boeing.com/defense-space/space/delta/delta4/d4h_demo/book04.html
Lockheed Martin
Atlas V 401
Boeing Delta IV Heavy
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 3
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 4
http://www.osd.noaa.gov/GOES/ULA_GOES-P_Mission_Book.pdf
Why Study Liquid Propellant Slosh?
• Delta IV launch postponed because of CFD
– Left: Original prediction of LH2 slosh
– Middle: Independent prediction of LH2 slosh
– Right: Redo of original prediction of LH2 slosh
• Two users get same result using same code, but is it true?
• How to validate models? What experimental data is there?
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 5
Value
• NASA KSC LSP must ensure safety and performance of launch vehicles
• Current CFD slosh models lack benchmarking data and limited in predictive abilities
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 6
Sample Results
• Data to improve CFD fluid slosh model predictions, benefiting spacecraft and launch vehicle design and operations
CFD Model Experiment
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 7
Rationale for ISS Slosh Research
• ISS offers opportunity to acquire low-gravity slosh data
• Leverage proven SPHERES hardware on ISS
• World’s first long duration liquid slosh database 7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 8
Goal and Objectives
• Goal
– Acquire long-duration, low-gravity slosh data for calibration of
detailed Computational Fluid Dynamics (CFD) models of
coupled fluid-vehicle behavior
• Objectives
– Utilize existing SPHERES satellites to propel transparent liquid-
filled tank
– Acquire system and liquid position data for known applied forces
using IMU and imaging systems
– Benchmark CFD model predictions
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 9
SPHERES Slosh Experiment (SSE)
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 10
• Picture above shows assembled SPHERES Slosh Experiment (SSE)
• SPHERES (x2) and VERTIGO (x2) already on ISS – items sent to ISS
referred to as ‘Slosh Payload’
Slosh Payload
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 11
• Designed by Florida
Tech in collaboration
with NASA KSC LSP
• Slosh Payload
manufactured by Florida
Tech with exception of
– 3D printed plastic
– Liquid Slosh tank
– Electronics
3D Printed Parts
• First SPHERES experiment to use 3D
printed Ultem parts
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 12
3D printed tanks, optical polish, pressure
tested to 1.5 atmospheres
3D printed backdrop, hood, saddles and
avionics boxes
SPHERES Slosh Experiment (SSE)
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 13
Overview: Slosh Experiment
• Introduction
• Slosh Experiment on the International Space Station
– Hydrodynamic Regimes
– Simulating Maneuvers on ISS
– Space to Ground interaction
– Test Sessions
– Initial Conditions
– Execution
• Conclusion
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 14
Application of Non-dimensional Parameters
• Impossible to match all numbers
simultaneously
• Flow regimes and individual non-
dimensional numbers can be matched
• Settling Thrust maneuver: By Froude
number matching
• Pitch to Reorient maneuver: By matching
rotation rates for each individual upper-
stage non-dimensional number
• Passive Thermal Control maneuver: By
matching scaled rotation rate
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 15
Hydrodynamic Regimes
• Ratio of Weber to Bond
provides insight to
either inertial
dominated regime or a
gravitational dominated
regime
• Ratio of Reynolds to
Froude provides insight
to either gravitational
dominated regime or a
viscous dominated
regime
Froude=1
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 16
Example Maneuver: BBQ Roll
• BBQ roll performed for an upper-stage propellant tank to ensure even solar heating
• What are impacts of BBQ roll on liquid distribution inside a tank?
17 7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL
Example Maneuver: Turn to Attitude
18 7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL
Maneuvers on ISS • Maneuver 1: Simulate an Engine shut down
– Accelerate system along major axis of tank for a fixed duration
– Apply reverse thrust to accelerate system in opposite direction for a fixed duration
• Maneuver 2: Simulate a turn to attitude
– Spin tank about a minor axis to settle all propellants
– Make sharp 45 degree turn out of spin plane to 2nd burn attitude
• Maneuver 3: Simulate a thermal roll
– Slowly spin tank about minor axis to attain constant spin rate and settle fluid
– Thermal roll about major axis while maintaining constant major axis spin rate
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 19
Control Room
• Purposely-setup control room at Florida Tech to support live ISS operations
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 20
Test Sessions • Checkout Session: Jan 22nd, 2014
– Test Systems
– Execute first set of tests:
• Translation (engine shut down)
• Rotation (thermal roll)
• Turn to Attitude
• Results showed:
– Sensitivity to initial conditions
– Bubble count reduction required
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 21
Initial Conditions
• Initial distribution of liquid in slosh tank unknown before experimentation
• Modeling feasibility is critical
Option 1: Abrupt acceleration and braking
Not effective at reducing bubble count
Option 3: Spinning about major axis
Effective at reducing bubbles, easy to execute. Attempted Initial Conditions
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 22
Option 2: Spinning about offset axis
Effective at reducing bubbles, hard to achieve
(large experiment, small space to move)
Test Sessions • Science 1 Session: Feb 28th, 2014
• Executed with 40% fill level tank
– Crewmembers found best way to create
bubble-free initial condition with cover
off
– Executed tests
• Translation (engine shut down)
• Rotation (thermal roll)
• Turn to Attitude
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 23 (Playback speed 2x)
Overview: Conclusion
• Introduction
• Slosh Experiment on the International Space Station
• Conclusion
– Conclusions
– Summary
– Future Research
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 24
Conclusions
• Slosh Experiment launched in January 2014
• Two Tanks (20% fill level, 40% fill level)
• Three test sessions
• Slosh Experiment testbed ultimately handed over to SPHERES
Program office at NASA AMES for continuing research
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 25
Summary
Slosh experiment on ISS fills a gap in available data to benchmark models
Agreement
Being determined
Agreement
± 8%
Agreement
± 3%
Comparison Simulation Experiment Testing Platform
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 26
Future Research Possibilities
• Create and improve control algorithms that
include sloshing liquid behavior control and
prediction for trajectory optimization
• Study Propellant Management Devices
• Study cryogenic propellants
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 27
Courtesy of ATK – Alliant Techsystems
Acknowledgements
NASA KSC – Launch Services Program
NASA Game Changing Development Program
NASA AMES
NASA Johnson Space Center
NASA Marshall Space Flight Center
MIT – Space Systems Laboratory
Florida Tech team – Aerospace Systems And Propulsion (ASAP) laboratory
Crewmembers in the ISS
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 28
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 29
Supplemental Slides
Flammability/Off-gassing
• Flammability and Off-gassing analysis/assessment performed on all components of Slosh
payload
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 31
OpNom Material Flammability Assessment Status
Aluminum 2024 T351 On MAPTIS list of approved material
ULTEM 9085Passed flammability and offgassing test, reference:
Slosh_ULTEM_Flammability Assessment
Center Hub Aluminum 2024 T351 On MAPTIS list of approved material Passed
IDS UI-5580CP-C GigE camera
Acceptable by analysis (reference: discussion at
flammability and offgassing meeting via
teleconference on March 29, 2013)
Stainless-steel On MAPTIS list of approved material
Aluminum 2024 T351 On MAPTIS list of approved material
ULTEM 9085Passed flammability and offgassing test, reference:
Slosh_ULTEM_Flammability Assessment
LED light panel
Acceptable by analysis (reference: discussion at
flammability and offgassing meeting via
teleconference on March 29, 2013)
Lexan sheet On MAPTIS list of approved material
BellowAcceptable by analysis (reference: email from Dr.
Mike Pedley on May 8, 2013)
Aluminum 2024 T351 On MAPTIS list of approved material
ULTEM 9085Passed flammability and offgassing test, reference:
Slosh_ULTEM_Flammability Assessment
LED light panel
Acceptable by analysis (reference: discussion at
flammability and offgassing meeting via
teleconference on March 29, 2013)
Lexan sheet On MAPTIS list of approved material
L20 Tank 3D printed LexanAcceptable by analysis (reference: email from Dr.
Mike Pedley on February 12, 2013)Passed
L40 Tank 3D printed LexanAcceptable by analysis (reference: email from Dr.
Mike Pedley on February 12, 2013)Passed
S40 Mass ULTEM 9085Passed flammability and offgassing test, reference:
Slosh_ULTEM_Flammability AssessmentPassed
Internal electronic components
Acceptable by analysis(reference: discussion at
flammability and offgassing meeting via
teleconference on March 29, 2013)
ULTEM 9085Passed flammability and offgassing test, reference:
Slosh_ULTEM_Flammability Assessment
Slosh Flash Drive
Small printed circuit board carrying
the circuit elements and a USB
connector, insulated electrically and
protected inside a plastic, metal, or
rubberized case
Acceptable by analysis (reference:
SSE_Flammability_Offgassing_Summary.pdf)Passed
Slosh Hard Drive
Flash Hard Disk is manufactured by
InnoDisk, contains no magnets, (this
is similar to a USB thumb drive,
except uses the SATA port)
Hard Drives manufactured identically as VERTIGO
Hard Drives, Acceptable by analysis (reference:
SSE_Flammability_Offgassing_Summary.pdf)
Passed
Frame Arm
Camera
Hood
Backdrop
Slosh Avionics Box
Passed
Passed
Passed
Passed
Passed
NASA WSTF
flammability
and
offgassing
test results of
3D printed
plastic
Tank Pressure
• Requirement from Safety Data Package, standard hazard form are:
– Have a maximum delta pressure of 1.5 atmospheres (22 psia, 1.5 bars)
• Four different pressure tests performed
– Gradual increase of pressure within Wet Slosh tank (full of water)
– Rapid increase of pressure within the Wet Slosh tank (full of water)
– Gradual increase of pressure within Dry Slosh tank (no water)
– Rapid increase of pressure within the Dry Slosh tank (no water)
• Leak check performed with dry towel (for Wet tank test) and soap solution (for Dry tank
test)
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 32
Touch Temperature Test
• Requirements for touch temperature are based of SSP 50005, section 6.5.3
• Minimum temperature of 4 ºC (39 ºF) and a maximum temperature of 45 ºC (113 ºF)
• Touch Temperature testing was performed at NASA MSFC, EMC/EMI facility for Slosh
hardware articles in the ISS configuration
– Temperature readings were taken at pre-defined locations on surface of the SSE
– Temperature readings were taken every five minutes after SSE startup for a total
duration of 60 minutes.
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 33
Vibration Test
• Slosh hardware vibration tested in its
stowage configuration (bubble
wrapped and packed in class III triple
CTB)
• Maximum flight random vibration
envelope as specified in SSP 50835
• Post-vibration analysis, inspection,
and verification performed
– Functioning of Slosh Avionics
Box
– Structural integrity of the Slosh
tank
– Camera lens (shatter)
– Slosh hardware (fit check)
– LED panels (shatter) in Hood and
Backdrop
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 34
EMI/EMC Test
• EMI testing is required to verify that the SSE
meets EMI requirements set forth in SSP
30237
• SSE did not pass the RE02 test, but waiver
has been issued for flight certification
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 35
• Two tests
performed for
entire SSE
– Radiated
Emissions
– Radiated
Susceptibility
Clamp Functionality
• A frame arm consisting of a directional
positioning system (saddle) and a sliding screw
clamping mechanism is utilized for attachment
of SPHERES to the Slosh Experiment frame.
• Two types of buffer materials are used on either
side of clamp mechanism.
– An Ultem buffer that is part of saddle
extends into clamping region from top.
– A thick rubber buffer is used on sliding
portion of clamp to ensure a spread contact
force.
• SPHERES is positioned into saddle with tank
protruding through clamp mechanism.
• Thumbscrew is tightened to a high finger tight
torque securing SPHERES unit to Slosh
Experiment.
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 36
Clamp Over Tightening
• Multiple methods to prevent over-torquing
are implemented:
– Small knob size reduces amount of
torque an astronaut can apply
– Mechanical stop ramps ensure that tank
cannot be deflected by more than 0.072”
– Rubber buffer can compress by more
than 0.072”
– Carrier mount screws sized shear/deform
prior to thumbscrew pull out
• DOT-SP 10776 Rev. 10 §178.42 (f) (2) states
tank certification hydrostatic test:
– Conducted at 3000 psi and flattened with
60° wedges containing a 1/2” radii nose.
Must not rupture under six times the
seam thickness of deformation.
– Tank seam of 1/8” allows for 3/4” of
deflection. Far less than 0.072”
maximum mechanically allowed by
system
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 37
NASA-STD-3000 207 lists maximum
torque applied by an astronauts hands.
Design numbers used worst case hand
torque over lesser finger torque.
Structural Failure of CO2 Tank due to Clamp Mechanism Cause 1
• Over torqueing of tank clamp thumbscrew has potential to damage SPHERES CO2 tank
Control 2.A: Tank must not Must not rupture under six times the seam thickness of deformation per DOT-
SP 10776 Rev. 10 §178.42 (f) (2). SPHERES CO2 tank has 0.125” seam therefore allowing 0.750”
deflection.
Test/Verification 1:
• Verification 1.1 Micrometer 4 CO2 tanks diameter, two empty and two full, in three different
orientations each to take average. Secure CO2 tank in clamp, tighten thumbscrew to maximum
supination torque as define by NASA-STD-3000 207 and micrometer diameter in three different areas.
Verify no value exceeding maximum deflection criteria.
• Verification 1.2 Leave CO2 tank clamped for 3 hours and recheck tank diameter
dimensions. Verify no value above the maximum deflection.
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 38
Retaining Pin
Free Spinning
End
Cross-Sectional View Bottom View
Experimental Validation Overview
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 39
• Two tanks and two SPHERES units used
in MSVP experimental validation.
• CO2 tanks are flight size, but do not
include thermal coating used on ISS flight
tanks.
• Tank diameters measured at three different
stations from the non-threaded end of the
tank: 1.75 inches, 3.50 inches and 5.00
inches on each tank.
• Tank 1 diameter: 2.01 – 2.013 inches
• Tank 2 diameter: 2.008 – 2.0195 inches
• BLUE sleeve diameter: 2.055 inches
• ORANGE sleeve diameter: 2.065 inches
• Nominal gap on radius: 0.021 inches (0.53
mm) between tank wall and sleeve
CO2 Tank – Sleeve Contact
• CO2 tank (tank 2) threaded into
blue SPHERE
• Zoom-in picture shows nominal
gap between CO2 tank and metal
sleeve
• Nominal gap on radius: 0.021
inches (0.53 mm)
• Pushing in any orientation (left,
right, up, down) it is ‘easy’ to push
the CO2 tank into the wall of the
SPHERES metal sleeve using just
finger pressure.
• It is easy to push either CO2 tank
into the sleeve of either SPHERES.
• No change to operation (no
damage) occurs when the CO2 tank
is pushed into the sleeve.
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 40
Metal sleeve
CO2 tank
Example of Clamp Mechanism Holding CO2 Tank
• Upper Left: photo of underside of
clamp assembly. No CO2 tank inserted.
Clamp is fully retracted.
• Upper Right: photo of underside of
clamp assembly with CO2 tank fully
clamped into place. Thumb screw is
finger tightened. Notice compression of
orange rubber pad, no compression of
ULTEM sleeve occurs.
• Lower Left: Example of measurement
of tank diameter with thumb screw
tightened.
• Lower Right: Example of CO2 tank
clamped in one of three positions used
to measure possible deflection of CO2
tank diameter
• Conclusion: with tank clamped under
thumb screw torque no tank
deformation measured.
• Conclusion: using maximum finger
tightening, clamp can not be over-
torqued – stop works as intended.
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 41
Completed: Verification 1.1 and Verification 1.2
Structural Failure of Frame arm due to Collision Cause 2
• Collision of SPHERES Slosh Experiment has potential to damage frame arm and tank clamp
mechanism.
Control 2: Frame arm and tank clamp must not yield and maintain functionality under loading conditions
defined in section 7.18 of SLOSH FSDP Phase-I-II .
Test/Verification 2.A:
• Verification 2.A.1 Clamp SPHERES in with nominal finger torque. Mount frame arm
vertically so that the CO2 tank axis is parallel with the floor. Apply a total static load of 36.6 N to the
end of spheres. Verify no yielding by dimensional and visual inspection.
• Verification 2.A.2 Clamp the SPHERES in with nominal finger torque. Mount frame arm
horizontally with CO2 tank axis parallel with the floor. Apply an incremental static load of 50 N up to a
maximum load of 227 N to the upward facing side of SPHERES. Verify no yielding by dimensional
and visual inspection after each load increment.
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 42
V 2.1
V 2.2
Examples of Clamp Holding SPHERES in Various Orientations
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 43
Maximum Loading Summary
• Upper: Blue SPHERES with CO2 tank (tank 2) loaded
into cantilevered test fixture.
• Note that blue SPHERE with CO2 tank is about 4.2 kg
(9.2 lb).
• Force transmitted to CO2 tank and saddle is about 40 N
• Visual inspection indicates that CO2 tank contacts wall
sleeve
• Lower: Blue SPHERES with CO2 tank (tank 2) loaded
into cantilevered test fixture.
• Additional weight: 25.4 kg (56 lb).
• Force transmitted to CO2 tank and saddle is about 250 N
• Visual inspection indicates that CO2 tank contacts wall
sleeve
• Test repeated on three sides of SPHERES unit (not
repeated on side that holds VERTIGO).
• Test repeated by placing weight on top of SPHERES
with saddle on bottom
• Conclusion: no loss of functionality or damage to
SPHERES, CO2 tank, saddle, clamp, etc.
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 44
Completed: Verification 2.A.1
and Verification 2.A.2
Testing of Both Clamps
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 45
Notes/Observations/Comments
• Orientation saddle performs as intended
– Alignments of SPHERES with frame axis arm is better than 2 degrees (note cosine 2
degrees = 0.99939)
– Clamp mechanism/grip itself prevents rotation of the CO2 tank once clamped down
• With thumb screw tightened down using nominal finger torque, I was not able to pull CO2
tank out of clamping mechanism
• With thumb screw tightened down using nominal finger torque, placing 250 N (56 lb) on
top of SPHERES did not cause tank to slide or move within clamping mechanism or create
any measureable deflection of saddles (indicated good base contact).
• Shaking frame arm with SPHERES unit attached did not result in any movement of clamp
relative to CO2 tank. Works exactly as anticipated.
• Tests repeated multiple times – no instances of clamp not working as intended.
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 46
Liquid Slosh Tank Design • Bo can be maximized for given fill level (balance between r2 and
m)
– Approaching peak from small radius, acceleration ↓, and Bo ↑
– Past peak, radius ↑, acceleration ↓, and Bo ↓
• Purpose: Bond analysis not sufficient – how much impact does fill
level have on creating a slosh event that alters system trajectory
• Liquid impacts tank and entire system is ‘pushed’ to a new
velocity, given by conservation of momentum
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 47
Surrogate Fluid Options
• Surrogate fluid options Novec Fluid and Silicone Fluid (vs. water)
• Both fluid have low viscosity, surface tension and contact angle
• Non-dimensional numbers reflect Novec fluid has high Bond number and Weber number
ranges
• High Bond and Weber numbers would favor slosh as fluid tends to be in gravity or inertia
dominated regime
Water Novec Silicone
Bond Number 1.62 12.95 5.61
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 48
PTC Maneuver: Non-dimensional Mapping Results
• For a specified rotation rate (deg/s) for an rocket upper-stage, can the non-dimensional number suggest
rotation rates for ISS slosh experiment?
• Table below shows expected rotation rate (in deg/s) for slosh experiment to match non-dimensional numbers for
typical rocket upper-stage
• Bond, Weber and Reynolds numbers from upper-stage are used to derive individual rotation rates for specified fluid
and slosh experiment dimensions (tank radius) and each non-dimensional number provides a unique rotation rate
Rotation Rate (Deg/s) 0.1 0.1 0.1 0.1 0.1 0.1
Velocity (m/s) 4.36E-03 3.49E-03 2.66E-03 4.36E-03 3.49E-03 2.66E-03
Acceleration (m/s2) 7.62E-06 6.09E-06 4.65E-06 7.62E-06 6.09E-06 4.65E-06
Bond Number 1.29E+00 6.61E-01 2.93E-01 4.12E+00 2.11E+00 9.35E-01
Weber Number 1.29E+00 6.61E-01 2.93E-01 4.12E+00 2.11E+00 9.35E-01
Reynolds Number 5.65E+04 3.62E+04 2.10E+04 6.34E+04 4.06E+04 2.36E+04
Froude Number 1.00E+00 1.00E+00 1.00E+00 1.00E+00 1.00E+00 1.00E+00
Rotation Rate (Deg/s) 27.1 19.4 12.9 48.4 34.7 23.1
Rotation Rate (Deg/s) 27.1 19.4 12.9 48.4 34.7 23.1
Rotation Rate (Deg/s) 515.8 330.1 191.9 578.8 370.4 215.4
Bond Number 1.29E+00 6.61E-01 2.93E-01 4.12E+00 2.11E+00 9.35E-01
Weber Number 4.24E+03 2.17E+03 9.62E+02 1.35E+04 6.92E+03 3.07E+03
Froude Number 3.28E+03 3.28E+03 3.28E+03 3.28E+03 3.28E+03 3.28E+03
Reynolds Number 1.70E+05 1.22E+05 8.11E+04 3.04E+05 2.18E+05 1.45E+05
Bond Number 4.24E+03 2.17E+03 9.62E+02 1.35E+04 6.92E+03 3.07E+03
Weber Number 1.29E+00 6.61E-01 2.93E-01 4.12E+00 2.11E+00 9.35E-01
Froude Number 3.05E-04 3.05E-04 3.05E-04 3.05E-04 3.05E-04 3.05E-04
Reynolds Number 2.97E+03 2.13E+03 1.42E+03 5.31E+03 3.80E+03 2.53E+03
Bond Number 1.53E+06 6.28E+05 2.12E+05 1.93E+06 7.91E+05 2.67E+05
Weber Number 4.67E+02 1.91E+02 6.47E+01 5.88E+02 2.41E+02 8.14E+01
Froude Number 3.05E-04 3.05E-04 3.05E-04 3.05E-04 3.05E-04 3.05E-04
Reynolds Number 5.65E+04 3.62E+04 2.10E+04 6.34E+04 4.06E+04 2.36E+04
Water
LH2 LOX
Rocket Upper-Stage
Tank Slosh Experiment
Bond Matching
Weber Matching
Reynolds Matching
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 49
Surrogate Fluid
• Deviation in displacement between frozen solid
and liquid is:
– CG Displacement: 100 mm
– Velocity: 2 mm/s
– No rotations induced in this case
• Deviation in displacement between frozen solid
and liquid is:
– CG Displacement: 38 mm
– Velocity: 2 mm/s
– No rotations induced in this case
LIQ SOL LIQ SOL LIQ SOL LIQ SOL LIQ SOL LIQ SOL LIQ SOL LIQ SOL LIQ SOL
Man Fill Vol X X Δ Y Y Δ Z Z Δ X X Δ Y Y Δ Z Z Δ X X Δ Y Y Δ Z Z Δ
1 20 -1 0 1 813 713 100 -14 -13 2 0 0 0 143 145 2 0 0 0 0 0 0 0 0 0 0 0 0
1 20 -1 0 1 725 686 38 -24 -12 12 -1 0 1 142 140 2 -1 0 1 0 0 0 0 0 0 0 0 0
POSITION (mm) VELOCITY (mm/s) ROTATION (Deg/s)
7/21/2014 AAS 3rd ISS Research and Development Conference - Chicago, IL 50