NASA /TM--2001-210202

Microgravity Combustion Science and Fluid

Physics Experiments and Facilities for the ISS

Richard W. Lauver, Fred J. Kohl, Karen J. Weiland, Robert L. Zurawski,

Myron E. Hill, and Robert R. Corban

Glenn Research Center, Cleveland, Ohio

Prepared for the

Spacebound 2000

sponsored by the Canadian Space Agency

Vancouver, British Columbia, Canada, May 15-18, 2000

National Aeronautics and

Space Administration

Glenn Research Center

February 2001

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Microgravity Combustion Science and Fluid Physics

Experiments and Facilities for the ISS

Richard W. Lauver, Fred J. Kohl, Karen J. Weiland, Robert L. Zurawski,

Myron E. Hill, Robert R. Corban

National Aeronautics and Space Administration

Glenn Research Center

Cleveland, Ohio 44135

Abstract

At the NASA Glenn Research Center, the Microgravity Science Program supports both

groundbased and flight experiment research in the disciplines of Combustion Science and Fluid

Physics. Combustion Science research includes the areas of gas jet diffusion flames, laminar

flames, burning of droplets and misting fuels, solids and materials flammability, fire and fire

suppressants, turbulent combustion, reaction kinetics, materials synthesis, and other combustion

systems. The Fluid Physics discipline includes the areas of complex fluids (colloids, gels, foams,

magnetorheological fluids, nonNewtonian fluids, suspensions, granular materials), dynamics and

instabilities (bubble and drop dynamics, magneto/electrohydrodynamics, electrochemical

transport, geophysical flows), interfacial phenomena (wetting, capillarity, contact line

hydrodynamics), and multiphase flows and phase changes (boiling and condensation, heat

transfer, flow instabilities).

A specialized International Space Station (ISS) facility that provides sophisticated research

capabilities for these disciplines is the Fluids and Combustion Facility (FCF). The FCF consists

of the Combustion Integrated Rack (CIR), the Fluids Integrated Rack (FIR) and the Shared

Accommodations Rack and is designed to accomplish a large number of science investigations

over the life of the ISS. The modular, multiuser facility is designed to optimize the science

return within the available resources of onorbit power, uplink/downlink capacity, crew time,

upmass/downmass, volume, etc. A suite of diagnostics capabilities, with emphasis on optical

techniques, will be provided to complement the capabilities of the subsystem multiuser or

principal investigatorspecific experiment modules. The paper will discuss the systems concept,

technical capabilities, functionality, and the initial science investigations in each discipline.

Introduction

Through the first decades of the 21 st century, the International Space Station will provide

convenient, longterm access to the environment of nearEarth orbit at an unprecedented scale.

The station is truly international in scope and offers multiple opportunities for unique and

cooperative activities in both scientific and engineering endeavors. The United States

Laboratory Module will contain multiple facilities developed by the NASA Microgravity

Science Program to enable the implementation of both fundamental science experiments and

technology development demonstrations.

The potential for significant scientific and technical advances through conduct of experiments in

the unique environment of microgravity remains a key element for justification of the

NASA/TM----2001-210202 1
Intemational Space Station. Such advances have been demonstrated during the recent history of

microgravity experiments on the Space Shuttle and the promise of expanded access and extended

times in orbit provide increased opportunity for improved understanding of Earthly processes

and demonstration of technologies required to explore the universe.

Glenn Research Center provides leadership for the NASA Microgravity Science Program in two

scientific disciplines, Combustion Science and Fluid Physics, which will provide a primary focus

of the Microgravity Program for both scientific and technological activities. These discipline

program elements have initiated a facilityscale development project which will evolve from

independent, standalone capabilities for combustion (the Combustion Integrated Rack or CIR)

and fluid physics (the Fluids Integrated Rack or FIR) to a fully integrated 3 rack facility called

the Fluids and Combustion Facility (or FCF) with addition of a third rack of hardware (called the

Shared Accommodations Rack or SAR). The fully integrated FCF will provide existing

capabilities (as well as great flexibility for upgrades and customization) to implement most, if

not all, the experiments brought to the program. The full potential of the modular, integrated

FCF will support the longterm, lowgravity requirements of investigators from academia,

industry, and our international partners throughout its 10 to 15 year lifetime.

This paper briefly summarizes the early science and facility hardware to be flown by the

Combustion Science and Fluid Physics discipline programs and endeavors to describe the overall

capabilities of the Fluids and Combustion Facility.

Combustion Science Experiments

The Fluids and Combustion Facility (FCF) will support extensive study of combustion in

microgravity. The combustion experiments that may be conducted in the FCF include, but are

not limited to, the study of laminar flames, reaction kinetics, droplet and spray combustion,

flame spread, fire and fire suppressants, condensed phase organic fuel combustion, turbulent

combustion, soot and polycyclic aromatic hydrocarbons, and flamesynthesized materials. The

facility will provide most of the capability with a small amount of unique hardware developed

for each investigation and, when possible, similar investigations will be flown at the same time

to increase the use of common hardware and diagnostics. To further reduce hardware

requirements, an initial set of three multiuser chamber inserts is being designed. The inserts will,

to the greatest extent possible, include experimentspecific hardware needed for a class of

investigations. Custom inserts for singular investigations having requirements not amenable to

the multiuser inserts will be developed as resources permit and it is expected that commercial

and international investigations will provide their own chamber insert (or barter other resources

in exchange for use of a multiuser insert). A total of fourteen flight and flightdefinition

investigations supported by the NASA Microgravity Science Program and one or more

commercial investigations are currently foreseen to use the CIR over the first few years of

operation. Several international investigations are at the conceptual stage, and additional

microgravity science investigations will be solicited every two years through NASA Research

Announcements. The order in which a particular investigation flies is subject to change based

upon results from science reviews, engineering development time, and other factors. A more

extensive description along with figures of the hardware inserts are in Ref. 1.

NASAfrM---2001-210202 2
Fourinvestigationsarebeingplannedto studythecombustionof smalldropletsof pureand

bicomponentalcoholandhydrocarbonfuels. Liquid fuelsareaprimarysourcefor energy

productionin theworld andthestudyof their combustionhasbeenongoingfor decades.Nearly

all practicalusesof combustioninvolvenonpremixedconditions;thesearemoreeasilystudied

usingawelldefinedsystemsuchasanisolateddropletandthestudyof dropletcombustion

remainsaclassiccombustionproblem. Oneinvestigation,DropletCombustionExperiment2,is

areflight;theremainingthreearein earlyphasesof development.A multiuserhardwareinsert

basedupontheapparatusdevelopedfor theDropletCombustionExperiment(Ref. 2) will be

utilizedaspossible.This insertcontainsthedropletdeploymentmechanisms,hot wire igniters,a

fuel supplysystem,anda gasmixingfan. Thedropletisgeneratedby issuingfuel from apair of

needlesbroughttogetherin thecenterof thetestregion. Thedropletis formedbetweenthetips

of theneedles;thetipsarestretchedapartslightly afterthedropletreachesthepropersize( 1to 6

mm diameter)andthenarewithdrawnrapidly to deploythedroplet. At themomentof

deployment,thehotwireignitersareactivatedto ignitethedropletandthentheytoo are

withdrawn. Thedropletmaybedeployedinto freespaceor ontoa smallceramicfiber. The

insertstructureis open to permit viewing of the droplet and flame. It is anticipated that at least

two droplet investigations will be the first users of the Combustion Integrated Rack after its

launch.

Six investigations are currently planned for the study of the combustion of small solid fuel

samples. Such studies are important for the development of improved material flammability

tests and predictions, and for development of improved modeling of ignition, spread, and

extinction of flames in solid materials. Enhanced fire prevention and extinguishment on the

Earth and in spacecraft are potential benefits of this research. Unwanted fires result in a

significant number of deaths and lost property each year on the Earth, and the possibility of an

accidental fire in a spacecraft remains a concern. Two solid fuel investigations are in the

requirements definition and engineering concept formulation phase. The remainder are

beginning the initial phase of science concept formulation. Preliminary requirements from these

investigations are guiding the development of a multiuser chamber insert capable of

implementing the proposed experiments. Most of the investigations require a sample holder, a

flow duct to provide a low speed convective flow environment, an ignition system, and a clear

volume for imaging of the flame and solid fuel surface. It is anticipated that at least two solid

fuel investigations will be performed in the CIR using this new apparatus.

Six investigations are currently planned for the study of various types of gaseous fuel

combustion. Premixed and nonpremixed gaseous combustion using nozzles of various sizes,

flame vessels and tubes, and porous spherical burners will be studied. Gaseous combustion

occurs in many practical systems as well as in unwanted fires. The use of gaseous fuels

simplifies the study of the main processes in combustion, chemical reaction and heat and mass

transfer. All of these investigations are in the experiment concept formulation phase and will

undergo several science reviews prior to flight. For as many experiments as possible, the

hardware insert will be based upon the chamber insert developed for the Laminar Soot Processes

experiment flown in the shuttlebased Combustion Module (Ref. 3). This structure contains a

small fuel nozzle with a hot wire igniter, a farfield thermocouple rake, a flame radiometer, and

thermophoretic soot samplers. During these experiments, fuel issues from the nozzle into a

quiescent chamber filled with oxidizer where it is ignited by the hot wire igniter (positioned near

NASA/TM----2001-210202 3
the nozzle tip). When the data collection is complete, the fuel flow is ended and the flame

extinguishes. The reflight of a commercial investigation studying the efficacy of water mist as a

fire suppressant is also planned.

Combustion Science Facility

Microgravity combustion experiments will be performed onboard ISS in the Combustion

Integrated Rack (Ref. 4). Experimentspecific equipment installed on orbit in the CIR will

customize it to perform many different combustion experiments during the ten or more years that

it will operate on orbit. The CIR will be the first FCF rack deployed to the Space Station in

2003. Once the other FCF racks are deployed, the CIR will function with the integrated FCF to

provide enhanced capability as a complete onorbit combustion research facility. As noted above,

a diverse range of combustion experiments will be conducted in the CIR. When the FCF is fully

deployed, the CIR will accommodate a minimum of five and as many as ten combustion

experiments per year, depending upon the availability of ISS resources.

In order to meet performance requirements, the CIR (Ref. 5) is designed as a permanent, modular

facility that can perform sustained, systematic research in microgravity combustion science on

board ISS. It will function on board ISS for ten or more years without the need for major rack

refurbishment or changeout and will, along with associated ground equipment, provide the

majority of hardware and infrastructure required to perform combustion science investigations in

ISS. The CIR will be capable of operating independently or in conjunction with added services

and capabilities provided by other FCF racks (i.e., SAR and/or FIR). The modular and flexible

design of the CIR will enable it to support a diverse range of experiment equipment in various

configurations. Key components of the CIR are onorbit replaceable to enable upgrades,

incorporate new technology and/or provide for onorbit maintenance during life span of the

facility. The CIR is designed to conserve ISS resources. For example, the CIR design supports

autonomous operation of experiments and rapid reconfiguration, minimizing required flight crew

time for experiment set up and allowing experiments to be primarily operated, monitored and

controlled from the ground. The CIR also includes a standard set of sensors and imaging

equipment to measure typical combustion phenomena, so as to minimize the need for PIunique

equipment.

The CIR primary subsystems and hardware elements, include an International Standard Payload

Rack (ISPR) with rack doors, an Active Rack Isolation Subsystem (ARIS), an optics bench

assembly with combustion chamber to accommodate the experiment insert, a fuel/oxidizer

management assembly (FOMA) for gas supply and distribution and exhaust venting,

environmental control subsystems (air/water thermal control, gas supply and fire

detection/suppression), avionics, software, electrical power supply and science diagnostics, as

shown in Figure 1 (Ref. 6).

The CIR ISPR provides structural support and connections to Stationprovided utilities such as

cooling water, electrical power, data interfaces, gaseous nitrogen and vacuum resources. A door

on the front of the rack provides thermal containment, acoustic attenuation, crewsafe operations

and full access to the internal contents of the rack. ARIS provides racklevel vibration isolation

to meet acceleration requirements for combustion experiments conducted in the CIR. It

attenuates onorbit, low frequency (<l 0 Hz), low amplitude mechanical vibrations transmitted

NASA/TM--2001-210202 4
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from the ISS US Laboratory Module to the CIR. For frequencies between 0.01 and 10 Hz, ARIS

is expect to limit accelerations in the CIR to microg levels. A Space Acceleration Measurement

System (SAMS) sensor is mounted in the CIR to measure the microgravity acceleration

environment in the rack. SAMS measures accelerations from 1.0 x l0 6 g to 1.0 x 102 g at

frequencies from 0.01 to 200 Hz.

An optics bench (Figure 2) supports the CIR combustion chamber, fuel and oxidizer

management assembly (FOMA), science diagnostics packages, image processing avionics and

experimentspecific electronics in the rack. Items frequently accessed by the crew such as gas

bottles, filters and the combustion chamber lid are located on the front of the optics bench.

Diagnostics and avionics packages are mounted on the rear of the optics bench at one of nine

mounting locations that provide standard mechanical, data, power and air cooling interfaces. The

CIR combustion chamber accommodates an experiment insert that is 60.0 cm long and 39.6 cm

in diameter. The chamber has a 100 liter free volume and a design pressure of 827 kPa (120

psig) which will permit combustion studies at ambient and elevated pressures (initial gas

pressures of 0.02 to 3 atmospheres). Diagnostic packages are arranged outside of the chamber

on the optics bench and are aligned to view the combustion event through one of eight optical

windows (11.5 cm dia). The windows are removable and interchangeable from inside the

chamber to match the spectral requirements of the diagnostics and/or for window

cleaning/replacement.

The CIR Fuel and Oxidizer Management Assembly (FOMA) is used to deliver gaseous fuels,

diluents and oxidizers to experiments in the combustion chamber. Up to four gas bottles can be

installed simultaneously. The maximum gas pressure in each bottle is 13,790 kPa (2,000 psi).

Gases are bottled in three sizes: 1.0 liter, 2.25 liter and 3.8 liter and can be either pure or

premixed. Premixed gases are used if an experiment requires a unique gas mixture or very

precise constituent accuracy exceeding the FOMA onorbit gas blending capability. However,

onorbit gas blending will typically be used since it reduces upmass and onorbit stowage needs

for experiments. The FOMA can provide a desired gas ratio using either a static and dynamic

gas mixing technique. The static mixing method uses the partial pressures to establish the

desired gas ratio. For experiments requiring gas flow during a test, the desired gaseous fuel

mixture and chamber atmosphere is provided using the mass flow controllers. Realtime venting

is performed to maintain the desired pressure in the combustion chamber.

The FOMA also controls the venting of chamber gases at acceptable concentration levels to the

ISS exhaust system. An exhaust vent system includes an adsorber cartridge and a recirculation

loop and is used to condition the chamber gas environment for sequential test points or to convert

postcombustion gases into species that are acceptable to vent. Chamber gases are pumped

through the recirculation loop using two recirculation pumps. The vent package scrubs

combustion gases to acceptable compositions for venting by removing moisture, particulates,

trace amounts of unburned fuels and chemically alter some trace species (e.g., CO to CO2). The

combustion chamber gases are sampled using a gas chromatograph to verify that the chamber

gases meet ISS requirements for venting or to measure pre and postcombustion gas composition

in the chamber as part of the experiment.

NASA/TM----2001-210202 6
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CIR environmental control subsystems remove waste heat, provide racklevel fire detection and

suppression and provide interfaces to ISSsupplied gases and vacuum. These subsystems include

a Water Thermal Control Subsystem, Air Thermal Control Subsystem (ATCS), Fire Detection

and Suppression Subsystem and Gas Interface Subsystem. The ATCS removes up to 1500 Watts

of waste thermal energy via air flow through avionics equipment. A primary water loop cools all

nonscience hardware via cold plates in the CIR power controller, ARIS controller and CIR air to

water heat exchanger. A secondary loop supplies water to experimentspecific equipment in the

combustion chamber. The Gas Interface Subsystem provides access to ISSprovided nitrogen,

exhaust and vacuum services.

CIR avionics provide power, command processing, caution and warning, health and status

monitoring, data processing, data storage, time synchronization, and hardware control functions

associated with the operation of the CIR. Image processing and storage units (IPSU) in the CIR

control the operation of science diagnostics packages, acquire and store images from the diagnostics,

capture and record ancillary data such as date and time, transfer images and ancillary data to the IOP

for downlinking and provide for realtime analog video output. Each IPSU can control one imaging

diagnostic package. A fiber optic umbilical connects the three FCF racks to allow high speed data

transfer between racks, independent of the ISS data system. The fiber optic interface enables

control and acquisition of images from diagnostics in the CIR using IPSU computers located in

other FCF racks. An Electrical Power Control Unit supplies up to 3kW of 28 Vdc power to loads

in the CIR on fortyeight, faultprotected, 4 amp circuits. Six, faultprotected 120 Vdc x 4 amp

circuits are also available for large, singleexperiment loads.

Seven standard diagnostic packages (Figure 3), constructed from modular elements, are planned

as initial capabilities for the CIR. Science diagnostics consist of modules (i.e., imaging module,

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Figure 3._onfiguration of Modular Diagnostic Subsystems.

NASAM'M---2001-210202 8
optics modules, diagnostics control module) which are connected at standard interfaces. The

diagnostic package operates together with an illumination package and an image processing and

storage unit to collect image data from an experiment. The modularity of these packages permits

performance and technology upgrades to the basic capabilities. The initial suite of CIR

diagnostics will includes a High Bit Depth/Multispectral Imaging Package (HiBM), High Frame

Rate/High Resolution (HFR/HR) Package, two Low Light Level (LLL) Packages, a Color

Camera Package, an Infrared Imaging Package and an Illumination Package.

The HiBM Package is used to measure soot volume fraction and soot temperature of

sootproducing flames. Soot temperature is measured using a two (or more) wavelength

pyrometry technique. Soot volume fraction is determined by measuring the percentage of laser

illumination, from the Illumination Package, that is blocked by soot in the flame region.

Measurements are made at the wavelength of the Illumination Package laser diode (675 nm) and

at the wavelengths chosen for soot temperature measurements.

The HFR/HR Diagnostic provides programmable frame rates up to 110 fps and high optical

resolution performance (1024 x 1024 pixels at frame rates up to 30 fps). It is capable of

automatically tracking an object within the total field of view, while maintaining a sharp focus

over a full object distance displacement range of 30 mm. The HFR/HR package may be used

with the Illumination Package which provides object backlighting and can be set to operate with

a laser diode or an incandescent light. The HFR/HR package can also serve as a high resolution

broad band imaging package. The addition of a liquid crystal tunable filter could allow for

+narrow band multispectral imaging including two or three wavelength pyrometric

measurements to determine soot temperature. When combined with a suitable external

illumination source, the package can also be used for Particle Image Velocimetry (PIV).

The Low Light Level (LLL) packages provide images of events or objects at low radiance levels.

The Packages provide imaging capabilities in the 280700 nm spectral range (UV shifted) for OH

imaging and 500875nm (IR shifted) for H20 imaging. The LLL packages are positioned on the

Optics Bench to provide orthogonal views of an experiment. The investigator will have the

option to configure these packages by selecting the utilization of two identical LLL units or to

view the combustion event in two different spectral regions. For low frame rate requirements, an

RGB liquid tunable filter could be installed in a LLL Package to acquire color images. A Color

Camera Package provides color images used by the crew and ground personnel for checkout and

verification during pre and postcombustion events. A midinfrared camera package produces

images of events or objects emitting from 3600 to 5000 nm.

The CIR illumination package is used in conjunction with diagnostics that require backlight

illumination. Illumination sources include a current stabilized tungsten halogen lamp for

radiometric calibration and laser diodes for coherence interference free illumination. The

illumination package provides a uniform illumination background for soot absorption

measurements in soot volume fraction applications. The package diffuse laser diode is used as

the background illumination source for shadowgraph measurements with the HiBMs package

and for droplet size measurements with the HFR/HR. The modular design of the illumination

package supports future growth considerations. The coherent laser diode illumination path could

be used for interferometric or Schlierren applications.

NASA/TM---2001-210202 9
Typically, theCIR will provideupto 90%of therequiredhardwareto performcombustion

experiments.Theremaininghardwarewill beprovidedby theexperiment.Experimentspecific

hardwareis launchedseparatelyfrom CIR andintegratedwith theCIR on orbit. An experiment

insertis installedin thecombustionchamberto controlthedesiredflamegeometryandperform

otherfunctionsuniqueto anexperiment.TheinsertmayincludePIuniquediagnostics(e.g.,

thermocouples,radiometers,cameras,etc.),igniters,samplecells,liquid or solidfuel supplies,

flow tunnels,translationstagesor otherequipmentattachedto theinsertmountingstructure,

nominally39.6cm in diameterby 60cm in length. Multiuserinsertsarebeingplannedto

accommodatemultipleexperimentswith commoncharacteristics.Thefirst suchinsertbeing

developedis aMultiUserDropletCombustionApparatusthatwill accommodatefour different

dropletcombustionexperiments.

TheCIR is in thedetaileddesignandfabricationphase(CrewReviewcompletedNovember

1998;Phase0/1Flight SafetyReviewcompletedin December1998;PreliminaryDesignReview

completedin April 1999).Engineeringmodelsfor mostCIR subsystemsarecurrentlybeing

fabricatedandprocuredandseveralarenow beingtested.Racklevelengineeringmodeltesting

is expectedto beginin thefall of 2000,andaCritical DesignReviewof theCIRis plannedearly

in 2001.

Fluid Physics Experiments

The Microgravity Fluid Physics program (Ref. 7) currently has four major research thrust areas:

Complex Fluids, Interfacial Phenomena, Dynamics and Instabilities, and Multiphase Flows and

Phase Change. There are currently more than 140 groundbased and 20 flight/flight definition

investigators conducting experimental research. Theoretical frameworks for understanding the

effects of gravity on processes involving fluids are being developed as well. Within the

subdiscipline areas, the following topics are included:

• Complex Fluids includes colloids, foams, granular media, rheology of nonNewtonian fluids,

and emulsions and suspensions;

• Interfacial Phenomena includes liquidvapor interface configurations, contact line dynamics,

capillary driven flows and shape stability and breakup of liquid bridges and drops;

• Dynamics and Instabilities includes thermocapillary and thermosolutal flows, biofluid

mechanics, geological fluid flows, pattern formation, and electrokinetics and electrochemistry;

• Multiphase Flows and Phase Change includes flow patterns in liquidvapor/gas flows in

microgravity, nucleate boiling and its control using acoustic and electric fields in microgravity,

and flows of gassolid and liquidsolid mixtures in microgravity.

To minimize the quantity of hardware required to implement these experiments, selected early

experiments have been grouped to permit development of multiuser modules which fit within the

FIR and take full advantage of its capabilities.

The first multiuser module is the Light Microscopy Module (LMM), Figure 4. LMM (Ref. 8) is

a selfcontained microscope which offers microscopy, sample changeout and fluid containment

capabilities, and an impressive array of optical diagnostics including various kinds of

microscopy (bright field, dark field, phase contrast, differential interference contrast, confocal,

NASAM'M---2001-210202 10
Figure 4.-_Concept for Light Microscopy Module for Fluids Integrated Rack.

and fluorescence); various kinds of light scattering (static, dynamic, and Bragg); and specialized

optical features (laser tweezers, spectroscopy, and interferometry).

There are four investigations which will be using LMM in the FIR:

• Physics of Colloids in Space2 (PCS2) PCS2 will study the nucleation, growth, morphology

and coarsening of crystal structures as well as rheological properties. Three general classes of

samples are planned: binary hard sphere alloys (highly ordered), colloid polymer mixtures, and

fractal aggregates.

• Physics of Hard Spheres Experiment2 (PHASE2) PHASE2 will study nucleation, growth,

rheological properties and morphology of crystal structures in the context of hard sphere

colloidal suspensions. The intent is to create novel structures, to study the dynamics of their

formation, and their phase transitions in order to differentiate kinetic and equilibrium structures.

• Colloidal Assembly in Entropically Driven LowVolumeFraction Binary Particle Suspensions

This experiment will study the nucleation and growth of surface crystal structures from colloidal

suspensions. The study will focus on lowvolumefraction particle suspensions of unagglomerated

spheres having small diameters so that thermodynamically driven Brownian motion maintains

the suspension. These entropicallydriven crystallization experiments will explore the creation of

new colloidal structures of potential industrial importance (e.g., photonic bandgap crystals). By

eliminating particle sedimentation effects, microgravity creates a purely "thermodynamic"

environment for the suspensions where particle size, volume fraction and interparticle

interactions are the primary determinants of the resulting structures.

NASA/TM---2001-210202 11
• Constrained Vapor Bubble Experiment (CVB) CVB will study vapor bubbles pertinent to the

understanding of heat pipes and heat transfer mechanisms. The experiment will improve our

understanding of the heat and mass transport mechanisms that are controlled by the interfacial

phenomena. Specific objectives are: to determine the overall stability of the device; to study

flow characteristics; to determine average heat transfer coefficients in the evaporative and

condensing parts of the CVB; and to determine these transfer coefficients as functions of void

fraction and heat transfer rates. A more detailed discussion of the experiments using LMM is

given in Ref. 9.

A second multiuser module is the Granular Flow Module (GFM). It will be designed to conduct

several experiments utilizing granular media - the first two of which are described below.

• Microgravity Segregation of Energetic Grains (pgSEG) The primary goal of pgSEG is to

induce and maintain particle segregation in a collisional flow of two different types of spheres.

In the absence of gravity, segregation will be driven by a gradient in the kinetic energy of the

mixture which is produced in a closed loop, annular shear cell (Figure 5). The inner and outer

walls of the shear cell provide moving boundaries which are rotated at different speeds.

Figure 5._ranular media cell showing shear flow with moving boundaries.

• Particle Interactions in lag Flow Cell The main objective is to study the interaction between a

flowing gas with relatively massive particles (constant diameter spheres) that collide with each

other and with the moving boundaries of the cell. Over the range of nonturbulent flow

conditions, the objectives are to characterize the viscous dissipation of the energy of the particle

fluctuations, to measure the influence of particlephase viscosity on the pressure drop along the

NASA/TM---2001- 210202 12
cell andto observethedevelopmentof localizedinhomogeneitieslikely to beassociatedwith the

onsetof clusters.Thecell, expectedto beessentiallythesameasfor theaboveexperiment,has

annulargeometrywith bumpyfrictionalboundariesto controltheenergyof particular

fluctuations.Specificto thisexperiment,cocurrentandcountercurrentgasflows will be

introducedinto theparticleflow. Themeasurementof theparticleandgasmeanvelocities,the

fluctuationenergyandtheparticleconcentrationsin thefully developedregionswill berequired.

A third multiuserfacility is thePoolBoiling Module (PBM). It wilt bedesignedto conductpool

boiling experiments- oneof whichis describedbelow.

• NucleateBoiling in Microgravity Theproposedstudywill providebasicknowledgeof the

phenomena(e.g.,heattransferand vaporgenerationandremovalprocessesduringnucleate

boiling conditions)thatenablesthedevelopmentof simulationmodelsandcorrelationsusedin

thedesignof spaceandEarthbasedboiling systems.

Fluid Physics Facility

The Fluids Integrated Rack (Figure 6) is a modular, multiuser scientific research facility

designed to accommodate a wide variety of microgravity fluid physics experiments noted above.

The FIR design is based on a "carrier" approach that provides common services needed by

nearly all fluids physics researchers to minimize the need to extensive experimentspecific

hardware required to be developed and launched for each experiment (Ref. 10).

Figure 6.--Concept for Fluids Integrated Rack.

NASAM'M---2001- 210202 13
Theuniquestructuralfeatureof theFIR is theincorporationof alaboratorystyleopticsbench

which providestheflexibility to removeandreplacedifferentsizeandshapedPI specific

experimentpackages.Theopticsbenchapproachis acommonfeaturebetweenall threeFCF

rackdesignsandofferstheadvantageof utilizing thesurfaceareaonbothsidesof thebenchand

efficient accessto theentirerackvolume. Standardizedinterfaceswill beutilizedto permit

flexibility in equipmentplacementandreplacement/upgrades.Thestandardinterfaceswill

provideelectricalpower,videoanddigital dataacquisition,andcontrol. Electricalharnessing

will beinsidetheplateto providemaximumvolumefor theexperimentandsimplify crew

interfaces.Thefront of theopticsbenchis dedicatedto theexperimenthardwaresetupwhilethe

backof thebench(Figures7 and8) is populatedwith severalmultifunction,nonintrusiveoptical

diagnosticspackages,andscienceavionicssupportpackages.In addition,thosediagnosticand

avionicspackagesmountedonthebackgeneratethemostheatandarethussegregatedto

provideabettertemperaturecontrolledenvironmentfor thescienceinvestigations.

Sinceasignificantportionof thefluid physicsexperimentsareimagingintensive,theFIR

Diagnosticsprovidesa suiteof imagingandillumination services.Theseservicesinclude

cameras,lasers,illuminationbacklighting, andopticsfor collimatedlaserbeams.High

resolutiondigital camerasandassociatedlenseswill beprovidedasthestandardmeansof image

acquisitionin theFIR. Thecamerasconsistof twomonochromatic(black andwhite) high

resolution(1024x 102412bitpixels,30framespersecond)digital cameras,oneanalogcolor

camerato achievecolorimages,anda highframeratecameracapableof acquiringimagesatup

to 1000framespersecond.Variousopticallenseswill beprovidedconsistingof fixed focus

andmotorizedzoomlensesthatcanbeinterchangeable.Therangeof fields of view FIR will

High Resolution Camera

Nd: YAG Laser

Scanning Mirror

High Resolution Camera

Figure 7.--Conceptual layout for front of Optics Bench with selected diagnostics subsystems.

NASA/TM---2001-210202 14
Image Processing

Optical Fibers

Collimating

Optics

Science Avionics

Color Camera

Diode Laser

White Light Source

LED Array

Figure 8._Conceptual layout for back of Optics Bench with selected subsystems.

accommodate will be (nominally) 300 pm by 300 pm to 100 mm by 100 mm. The zoom

function, as well as the focus and aperture functions of each lens will be motorized and remotely

controllable.

The FIR illumination sources will consist of white light, laser light, and collimated laser beams.

The light from each source will be transmitted to the experiment through an optical fiber; each

fiber will have an industry standard optical fiber interface that is accessible from the front of the

Fluids rack. The use of fiber optics also helps isolate the test cell from the heat that the light

source generates.

The FIR features the capability to remove and replace different PI specific experiment packages.

The experimentspecific package(s) may consist of a single selfcontained unit and/or several

separate components. The experiment hardware will typically reflect a unique design, but may

reuse hardware and designs from previous experiments. A set of similar experiments

investigating common phenomena and/or using similar diagnostics may permit the development

of a multiuser modules that can accommodate multiple PIs to significantly lower overall PI

development costs. The experiment package will typically consist of the fluids test cell(s),

precision optical diagnostic instrumentation (shearing interferometry, schlieren, surface

profilometry, etc.) that interface with FIR services previously discussed, and any support

equipment such as injection or mixing devices, motors, critical temperature hardware, magnetic

field generation, etc.

NASA/rM---2001-210202 15
The initial mission of the FIR will accommodate four investigations within a "minifacility"

called the Light Microscopy Module (LMM). The LMM package (Figure 4) combines a full

featured research imaging light microscope with powerful laser diagnostics, creating a

oneofakind, stateoftheart microscopic fluids research instrument. The imaging techniques of

high resolution color video microscopy, bright field, dark field, phase contrast, differential

interference contrast, fluorescence, and confocal microscopy are combined in a single

configuration. This suite of measurements allows a very broad characterization of fluids,

colloids, and twophase media. LMM may also incorporate sample manipulation techniques such

as singletrap scanning optical tweezers. The significant operational feature of the LMM is the

incorporation of a glovebox with the microscope to allow manipulation of sample trays within a

containment area that is sealed against escape of fluids and frangibles.

The FIR is being designed to minimize the crew time involved in reconfiguring diagnostics and

setting up the specific experiments. Each new experiment will require installation of experiment

hardware and configuration of the diagnostics by an astronaut. When setting up a new

experiment, the astronaut will fold open the FCF doors, slide out the optics bench, tilt the optics

plate to obtain access to the back side, unstow/install experimentspecific hardware and

diagnostics, reconfigure facilityprovided diagnostics on the back, translate/fold the optics plate

back to its upright position, unstow/install the experimentspecific hardware on the front to the

optics plate, return the optics plate to its operational position and, finally, close the doors for

checkout and experiment operations. The crew will not be the primary FCF operators since they

will have very limited time to dedicate to a specific facility due to their overall work load in

daytoday operations of the ISS. Instead, the ground team at the NASA Glenn Research Center

and the PI will monitor the health and status of FCF and the active experiments and will control

facility functions. During experiment operations, the FCF will provide nearrealtime data

downlink and command uplink to permit the PI to remotely interact with the experiment. The PI

will be provided with essential and timely data to react to unexpected scientific phenomena in

order to alter the experimental procedures.

Conclusion

The pending availability of the International Space Station offers significant opportunities for

research and development. The Combustion Science and Fluid Physics discipline programs will

have access to a major facility offering extensive capabilities and flexible implementation of

microgravity experiments. Preparation of the initial flight experiments and facility hardware has

begun and are planned for flight in 2003.

References

.

.

Weiland, K. J., "Progress on the Combustion Integrated Rack Component of the Fluids and

Combustion Facility," tkIP CP504, Space Technology and Applications International Forum

- 2000, ed. M. S. E1Genk, p. 389397 (2000).

Nayagam, V., Haggard, J. B., Jr., Colantonio, R. O., Marchese, A. J., Dryer, F. L., Zhang, B.

L., and Williams, F. L., "Microgravity nHeptane Droplet Combustion in OxygenHelium

Mixtures at Atmospheric Pressure," AIAA Journal 36, 13691378 (1998).

NASA/TM---2001-210202 16
, Urban, D. L., Yuan, Z.G., Sunderland, P. B., Linteris, G. T., Voss, J. E., Lin, K.C., Dai, Z.,

Sun, K., and Faeth, G. M., "Structure and Soot Properties of Nonbuoyant Ethylene/Air

Laminar Jet Diffusion Flames," AIAA Journal 36, 13461360 (1998).

,

.

Winsa, E., Corban, R., Malarik, D., and Zurawski, R., "Fluids and Combustion Facility,"

AIAA 99--0315, 37 th Aerospace Sciences Meeting & Exhibit, Rent, Nevada, 1999.

Zurawski, R., "The FCF Combustion Integrated Rack," AIAA 20000425, 38 th Aerospace

Sciences Meeting and Exhibit, Rent, Nevada, 2000.

6. FCF Combustion Integrated Rack Baseline System Description (BSD), Appendix A, Rev. B,

FCF-DOC-003, March 1999.

, Singh, B. S. and Alexander, J. I. D., "Microgravity Fluid Physics and Transport Phenomena

Experiments Planned Aboard the International Space Station," in Proceedings of STAIF

2000 Conference, Albuquerque, NM, January 2000.

8. Lant, C. T. and Resnick, A., "MultiFunction Light Microscopy Module for the International

Space Station," in Proceedings of STAIF 2000 Conference, Albuquerque, NM, January 2000.

9. Hill, M., Saavedra, S., "A Summary of Capabilities and Operations for the Fluids and

Combustion Facility Fluids Integrated Rack First Four Experiments," STAIF2000

Proceedings, January 2000.

10. Corban, R., "Fluids and Combustion Facility Fluids Integrated Rack," AIAA 20000427, 38 th

Aerospace Sciences Meeting and Exhibit, Rent, Nevada, 2000.

NASA/TM---2001-210202 17
REPORT DOCUMENTATION PAGE Form Approved

OMB No. 0704.0188

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1. AGENCY USE ONLY (Leave b/ank) ! 2. REPORT DATE 13. REPORT TYPE AND DATES COVERED

February 2001 ] Technical Memorandum

4. TITLE AND SUBTITLE 5. FUNDING NUMBERS

Microgravity Combustion Science and Fluid Physics Experiments

and Facilities for the ISS

6. AUTHOR(S) WU-398-20-4)C-00

Richard W. Lauver, Fred J. Kohl, Karen J. Weiland, Robert L. Zurawski,

Myron E. Hill, and Robert R. Corban

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) 8. PERFORMING ORGANIZATION

REPORT NUMBER

National Aeronautics and Space Administration

John H. Glenn Research Center at Lewis Field E-12322

Cleveland, Ohio 44135-3191

9. SPONSORING/MONITORINGAGENCYNAME(S) ANDADDRESS(ES) 10. SPONSORING/MONITORING

AGENCY REPORT NUMBER

National Aeronautics and Space Administration

Washington, DC 20546-0001 NASA TM--2001-210202

11. SUPPLEMENTARY NOTES

Prepared for the Spacebound 2000 sponsored by the Canadian Space Agency, Vancouver, British Columbia, Canada,

May 15-18, 2000. Responsible person, Richard W. Lauver, organization code 6724, 216--433-2860.

12a. DISTRIBUTION/AVAILABILITY STATEMENT 12b. DISTRIBUTION CODE

Unclassified - Unlimited

Subject Category: 88 Distribution: Nonstandard

Available electronically at htt-o.: //gltrs._Tc.nasa.cov/GLTRS

This publication is available from the NASA Center for AeroSpace Information, 301--621-0390.

13. ABSTRACT (Maximum 200 words)

At the NASA Glenn Research Center, the Microgravity Science Program supports both ground-based and flight experiment research in

the disciplines of Combustion Science and Fluid Physics. Combustion Science research includes the areas of gas jet diffusion flames,

laminar flames, burning of droplets and misting fuels, solids and materials flammability, fire and fire suppressants, turbulent combustion, reaction kinetics, materials synthesis, and other combustion systems. The Fluid Physics discipline includes the areas of complex

fluids (colloids, gels, foams, magneto-rheological fluids, non-Newtonian fluids, suspensions, granular materials), dynamics and

instabilities (bubble and drop dynamics, magneto/electrohydrodynamics, electrochemical transport, geophysical flows), interfacial

phenomena (wetting, capillarity, contact line hydrodynamics), and multiphase flows and phase changes (boiling and condensation,

heat transfer, flow instabilities). A specialized International Space Station (ISS) facility that provides sophisticated research capabilities for these disciplines is the Fluids and Combustion Facility (FCF). The FCF consists of the Combustion Integrated Rack (CIR), the

Fluids Integrated Rack (FIR) and the Shared Accommodations Rack and is designed to accomplish a large number of science

investigations over the life of the ISS. The modular, multiuser facility is designed to optimize the science return within the available

resources of on-orbit power, uplink/downlink capacity, crew time, upmass/downmass, volume, etc. A suite of diagnostics capabilities,

with emphasis on optical techniques, will be provided to complement the capabilities of the subsystem multiuser or principal investigator-specific experiment modules. The paper will discuss the systems concept, technical capabilities, functionality, and the initial

science investigations in each discipline.

14. SUBJECT TERMS

Fluids; Fluid physics; Combustion; Combustion science; Microgravity science;

Space Station facilities

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Unclassified

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23

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