NASA Technical Memorandum 106788

AIAA-95-0692

//v -/5-

3/¢'.__5f. /3

Conceptual Design of the Space StationCombuStionM0dule .........

Daniel R Morilak, Dennis W. R0hn, and Jennifer L. RhatiganLewis Research Center

Cleveland, Ohio

Prepared for the

33rd Aerospace Sciences Meeting and Exhibit

sponsored by the American Institute of Aeronautics and AstronauticsReno, Nevada, January 9-12, 1995

National Aeronautics and

Space Administration

(NASA-TM-I06788) CONCEPTUAL DESIGN

OF THE SPACE STATION COMBUSTION

MODULE (NASA. Lewis Research

Center) 13 p

G3/I5

N95-17419

Unclas

0031423

https://ntrs.nasa.gov/search.jsp?R=19950011004 2018-05-26T15:28:43+00:00Z

CONCEPTUAL DESIGN OF THE SPACE STATION COMBUSTION MODULE

Daniel P. Morilak, Dennis W. Rohn, and Jennifer L. RhatiganNASA Lewis Research Center

Cleveland, OH

Abstract

The purpose of this paper is to describethe conceptual design of the Combustion Modulefor the Intemational Space Station Alpha (ISSA).This module is part of the Space StationFluids/Combustion Facility (SS FCF) underdevelopment at the NASA Lewis ResearchCenter. The Fluids/Combustion Facility is one ofseveral science facilities which are beingdeveloped to support microgravity scienceinvestigations in the US Laboratory Module of theISSA. The SS FCF will support a multitude of fluidsand combustion science investigations over thelifetime of the ISSA and return state-of-the-art

science data in a timely and efficient manner to thescientific communities. This will be accomplishedthrough modularization of hardware, with planned,periodic upgrades; modularization of like scientificinvestigations that make use of common facilityfunctions; and through the use of orbitalreplacement units (ORUs) for incorporation of newtechnology and new functionality.

The SS FCF is scheduled to becomeoperational on-orbit in 1999. The CombustionModule is presently scheduled for launch to orbitand integration with the Fluids/Combustion Facilityin 1999.

The objectives of this paper are todescribe the history of the Combustion Moduleconcept, the types of combustion scienceinvestigations which will be accommodated by themodule, the hardware design heritage, thehardware concept, and the hardwarebreadboarding efforts currently Underway.

"Copyright @ 1994 by the American Institute of AeronauticsandAstronualics, Inc.

No copyrightis asserted in the United States under Title 17, U.S. Code.The U.S. Government has a royalty-free license to exercise all rightsunderthe copyright claimed herein for Government_ purposes. AIJother rights

are resew'ed by the copyright owner."

NASA Lewis Research Center (LeRC)received approval from NASA Headquarters tobegin a definition study and conceptual designeffort for a Modular Combustion Facility in June of1987. The objective of the study was to assessthe feasibility, effectiveness, and benefits topotential users of a modular, multi-user facilityforperforming combustion science and applicationsexperiments aboard the Space Station Freedom 1.Facility class hardware has been considered as analternative to experiment specific hardware forseveral reasons; 1) modular, multi-user facilitiescan provide resources or services to users whichare non-standard to space station, 2) the modularapproach allows for growth in capabilities over time,3) common subsystems developed across facilitiesimprove maintainability and minimize logisticsrequirements, 4) minimizing the individualinvestigators experiment hardware should reducethe individual experiment development time, and5) the facility approach can minimize cost to theoverall science discipline program whilemaintaining operational flexibility.

A study team was formed with the purposeof accomplishing five tasks: 1) define requirementsfor a modular combustion facility (MCF), 2) developdesign concepts, 3) perform trade studies onthese design concepts, 4) develop a plan forfuture development, and 5) obtain independentassessment of the concept and plan. A facilityproject scientist from The LeRC SpaceExperiments Division (SED) combustion sciencegroup was chosen to work with the engineeringteam and to define science requirements forformulation of a concept. The process used todefine the requirements started with a referenceset of microgravity combustion scienceexperiments. This set of reference experimentswas an extrapolation of the (then) currentmicrogravity combustion experiment program andwas intended to represent a majority of theprogram with potential combustion experiments.

This initial reference experiment list contained thefollowing experiment types?-:

1. StabilizedGaseous Combustion

2. Freely Propagating Rames3. Flaming and Smoldering Combustion in LowVelocity Flows4. Effects of Extinguishants on Flaming andSmoldering Combustion5. Pool Fires

6. Droplets Combustion7. Metals Combustion

There were other facilities beingconceptualized as well for operation on the spacestation, such as a containerless processing facility,a fundamental science facility, a biotechnologyfacility, and a furnace facility. In September of1988 this set of reference experiments allocatedto be performed in the Modular CombustionFacility was evaluated by the Combustion ScienceDiscipline Working Group (DWG) and NASAHeadquarters, and deemed to have appropriatecommonality and scientificsignificance to require aunique facility dedicated to microgravitycombustion investigations.

Specific experimental requirements weredeveloped for each of the above listed experimentcategories in the reference set. These experimentspecific requirements were then used as the basisfor the LeRC team to develop a conceptual designof a Space Station Freedom based ModularCombustion Facility.

At this point in the effort, a Space StationFreedom Modular Combustion FacilityAssessment Workshop was held at the LewisResearch Center. The purpose of that workshopwas to obtain science and engineeringassessments of the Modular Combustion Facilitydesign and operational concepts as well as theselected microgravity combustion sciencerequirements used to develop those concepts.

II. Combustion Science Accommodations

As a result of this workshop, the studyteam further developed the experiment specificrequirements and the conceptual design of theMCF. The facility scientist continued to refine thescience requirements and developed a ScienceRequirements Envelope Document (SRED). Thisdocument encompassed the science

requirements by which the hardware concept wasbeing developed and were specified so thatindividual experiment science requirements wouldmost often fall within this envelope. The envelopeincluded seven representative experimentrequirements:

I.

II.

III,

IV.

V,

Vl.

Vll.

Effects of Buoyancy on Laminar Gas JetDiffusion FlamesStructure of Flame Balls at Low LewisNumber

Ignition and Flame Spread Over LiquidFuel PoolsDiffusive and Radiative Transport in FiresSmoldering CombustionDroplet Combustion

Soot Processes in Turbulent DiffusionRames

These seven experiments were proposedby Principle Investigators (PIs) in the 1990Combustion NASA Research Announcement.The SRED is also representative of other gaseous,liquidand solid fuel experiments, such as metalscombustion and spray combustion. Theconceptual design effort continued by focusing onaccommodating these seven experiments in theMCF. A review of the MCF conceptual design washeld December of 1991. This review coveredspecific concepts for accommodating six of theseven representative experiments in theCombustion SRED. Another review was held inSeptember 1992, which covered theaccommodations for the seventh experiment. As aresult of these reviews the concept for the MCFwas approved. Also, the Combustion ScienceDWG reviewed this SRED and the engineeringdesign concept and endorsed both in January1993.

During this time the Space StationFreedom Program was evolving to become what iscurrently known as the International Space StationAlpha (ISSA). Changes also occurred intheconcept of the MCF in that it was now envisionedas a combined facility with the FluidPhysics/Dynamics Facility, sharing commonfunctions, such as data handling, communications,and carrier interfaces. These combined facilities

are now called the Space StationFluids/Combustion Facility (SS FCF') which housesa Fluids Module for performing microgravity fluidsscience (formerly the FP/DF"), and a CombustionModule for performing microgravity combustion

science (formerly the MCF'), with shared resourcesfor both. The combustion SRED, in conjunctionwith fluids SRED and Space Station carrier andsafety requirements will be used in theengineering specification development processfor the SS FCF. As specific investigations areassigned to the SS FCF, investigation-specificrequirements will be checked against the SRED'sand any new requirements will either beaccommodated in the system specification and thehardware design or negotiated with experimentspecific development teams.

III. Hardware Heritag_

The design of the SS FCF will draw uponthe design of as many previous space experimentsas possible. Since the science requirementsenvelope includes many investigations that havepreviously operated on orbit or are beingdeveloped, previous development efforts will beutilized to minimize cost and schedule. The areasof heritage include diagnostics, fluid systems,combustion chamber and combustion apparatus.The design of the SS FCF Combustion Module willbe based heavily on the design of the CombustionModule- 1 (CM-1)for the Microgravity ScienceLaboratory - 1 mission which is a Spacelab Missionscheduled to be launched in 1997. CM-1 is aderivative design from an initial concept whichwould have accommodated all of the classes ofexperiments within the Combustion SRED. CM-1is designed to accommodate two specificinvestigations, Laminar Soot Processes andStructure of Flame Balls at Low Lewis Numbers.However, much of the design will be common withthe SS FCF Combustion Module. The areas thatwill be modified are those required to interface withSpace Station and to provide the flexibility toaccommodate the full science envelope.Depending on project schedules and sparesavailability, some of the hardware componentsfrom CM-1 may be utilized.

The SS FCF Combustion Module will alsodraw heavily on designs of subsystems,components and test apparatus developed atLeRC on other combustion experiment projects,many of which fall into one of the classes ofexperiments covered by the science envelope.

IV. Hardware Description

The concept for the SS FCF has beendeveloped based on the envelope of sciencerequirements disciJssedin section III and those forthe fluids module portion of the project. Theconcept is a three rack facility as shown in figure IV-1. The right hand rack contains the hardwarerequired to support fluid physics and dynamicsexperiments. The left hand rack contains thehardware required to support combustionexperiments and the central rack provides corefunctions and system control. A HardwareCapabilities Document (HCD) is being drafted thatwill provide details on capabilities of the SS FCF.An Accommodations Handbook is also planned toaid currently planned and potential users in thedevelopment of experiments to use the facility.The discussion that follows will address the CoreSystems and the Combustion Module. The FluidsModule concept is described in reference 3.

The hardware in the racks fall into three

groups: core systems, combustion module, andexperiment specific. A detailed discussion of eachof these groups follows and is shown pictorially infigures IV-2, Core Systems Diagram, and IV-3,Combustion Module Diagram.

A. Core System CapabUities/Description

The core system hardware concept isshown in figure IV-2. The core systems are theprimary interface to space station systems and thecrew. The core systems also provide space for,interfaces to, and control of the combustionmodule and experiment specific hardware.Following is a description of the various functionsperformed by the core systems.

Structural SuDpod The core systemsprovide structural support for all of the coresystems packages and theCombustion Modulehardware. This support is accomplished throughthe use of International Standard Payload Racks(ISPR's) which mount directly into the spacestation U.S. Laboratory Module.

Facility.Command. Control and DataHandling Facilitycommand, control and datahandling (CCDH) will be accomplished byimplementing a distributed control, Versa ModuleEurope (VME) bus system architecture. One VMEbus system will be located in the core rack toprovide facility level CCDH and one will be locatedin the combustion rack to provide CCDH to thehardware located in that rack. A Fiber Distributed

Data Interface (FDDI) system is planned for inter°rack communications due to the high data ratesrequired. The CCDH has three interfaces withspace station: a Mi1-1553 B data bus, an Ethernetdata bus, and a fiber optic high rate data bus. Data,including digitized and compressed video, will bestored in high volume mass storage devices until itcan be downlinked to the ground.

Crew Interface The crew interface will

provide a system for the crew to view sensor andvideo data and control the facility. This system willinclude a video monitor and a laptop computer.

Video Image Control and ProcessingCore systems will provide for routing andprocessing of video images generated by thefacility. A dedicated VME card cage will be used toprovide this control, and digitization andcompression of images so that the images can bestored (digitization and compression of images isrequired so the data can be stored on a reasonablysized storage device and sent to the ground withina reasonable time).

F._ Core systemswillprovide for conditioning, conversion anddistribution of 120 VDC power provided by spacestation. The core rack will provide for 28 VDC and120 VDC to the combustion rack and thecombustion rack will additionally provide 5 VDCand 12 VDC.

Thermal Control Core systems will rejectheat from the facility via an interface with the spacestation moderate temperature water system. Boththe core and fluids racks will have an avionics air

system tied into the water systems to provid egeneral surface cooling. In addition, the core rackwill contain heat exchanger/pump assemblies toroute cooled water to specific hardware in thefacility that requires large amounts of cooling.

Vibration Data Processing A SpaceAcceleration Measurement System II (SAMS II)Remote Triaxial Sensor Electronics Enclosure(RTS-EE) will be located in the core rack to providedata processing and measurement support for thesensor head that will be located in the combustionmodule.

B. Combustion Module Capabilities/Description

The combustion module, as shown infigure IV-3, consists of an experiment package, afluid supply package and an exhaust/ventpackage. Each of these packages, along withportions of each, will be capable of being replaced

on orbit in order to upgrade and/or provideadditional functionality.

Experiment Package The experimentpackage is the primary element of the combustionmodule. It is comprised of two major elements, thecombustion chamber and the diagnosticsmounted around the chamber. The combustion

chamber is cylindrical with domed heads, hasapproximately 80 liters internal free volume andhas a maximum design pressure of 1000 kPA. Anumber of window ports provide optical access tothe interior of the chamber. The windows in these

ports are concepted to be replaceable on orbit sothat they can be tailored to the diagnostictechnique using the window. An instrumentationring and slide rails provide a standard set ofinterfaces inside the chamber. An ExperimentMounting Structure (EMS), which is unique to theparticular science investigation being conducted,mounts within the chamber on these slide rails and

interfaces to the instrumentation ring for gases,power, command, control and data. One enddome of the combustion chamber will be openedon orbit for access to the inside of the chamberand installation of EMSs. A glovebox can beprovided which interfaces with the chamber, ifrequired, to maintain containment of materialswithin the chamber while the door is open,

There are three types of diagnosticsmounted around the chamber: optical, chemicaland sensor. The optical diagnostics are mountedon an optical plate that allows for reconfigurationon orbit, and the combustion event is viewedthrough windows in the combustion chamber.These windows are of various size and are chosen

to be optically compatible with the diagnostic toolwhich will utilize that viewport. The chemicaldiagnostics consist of a gas chromatograph usedto sample the contents of the combustionchamber to determine the products ofcombustion. The sensor diagnostics PrOvideinformation such as chamber pressure, chamberwall temperature, and temperatures of gasesflowing into the chamber. A SAMS II sensor headwill also be mounted near the chamber to measurethe vibration disturbances during test runs.

The standard optical diagnostics plannedfor the facility are two orthogonal intensified blackand white video cameras, two orthogonai standardcolor video cameras, soot volume fractionmeasurements and soot temperaturemeasurements. Filters and lenses can be changedto provide a variety of field of views and resolution

combinations for selected experiments. Some ofthe other diagnostics that are being studied todetermine if they can be accommodated are colorschlieren imaging, infrared imaging, ultravioletintensified imaging, color intensified imaging,infrared intensified imaging, laser dopplervelocimetry, and both gas and liquid phase particleimaging velocimetry.

Ruid Supply Package The fluid supplypackage provides all gaseous fuels, diluent andoxygen required to perform the envelopecombustion experiments. The package consists ofgas storage and gas flow control functions. Puregases and nominal mixtures will be stored inbottles at pressures up to 20 MPa. Some of thegases will be stored as pressurized liquids. Thecombustion module will utilize nitrogen providedby space station. The storage bottles will bedesigned to be easily changed out on-orbit, forresupply, with filled ones that have been broughtto the space station. The flow control will allow forconversion of any liquified fuels or diluents back toa gaseous state, mixing of gases to theconcentrations required, filling of the combustionchamber to prescribed pressures, flowing of gasesinto the combustion chamber during combustionand venting or purging of the fluid systems andchamber. In addition the system will provide anycontrols of the gases required to assure the safetyof the FCF and crew.

Exhaust/Vent Package The exhaustvent package is the interface from the experimentand fluid supply packages to the space stationvent system and allows the fluid system andcombustion chamber to be evacuated. The primaryfunction of this package is to process the gasesbeing vented So they meet the interfacerequirements of space station. The packageincludes a recirculation loop and a vent path. Therecirculation loop will convert post-combustiongases into species that are acceptable to vent,remove water from the gas, and filter particles outof the gas by circulating the gases from thecombustion chamber through processingcanisters and back into the chamber until the bulkgas in the chamber is acceptable for ventingthrough the space station vent system.

The current concept for these packages isthat they can accomodate the entire scienceenvelope, if however, it is determined that thepackage needs to be upgraded or modified, it willbe able to be removed from the rack and replaced.

C. Experiment Specific Hardware

The combustion module provides anempty combustion chamber with standardinterfaces and a set of standard diagnosticsmounted around the chamber. As experiments areidentified to use the FCF, additional hardware willbe required to fully implement the science. Eachexperiment will need an EMS to mount within thecombustion chamber and interface to thechamber. These EMS's may include hardware toignite the fuel, hardware to deploy droplets,radiometers, thermistors, fuel holders, nozzles ortrays, liquid fuel supplies or solid fuels, sootsampling mechanisms, hardware to seed gas orliquid phases for imaging purposes, or a pressurevessel in which to perform higher pressurecombustion, such as for metals. Diagrams of EMSsfor several different classes of experiments areshown in figures IV-4, IV-5 and IV-6.

Some investigations may require specificoptical diagnostics that are not provided by thefacility. The optical plate that surrounds thecombustion chamber will have the capability to bereconfigured to support new types of opticaldiagnostics and the chamber windows, asmentioned above, will be replaced as needed.

The SS FCF project will provide themajority of the software required. This software willreside on the VME bus systems, except in twocases. If there are specific controlalgorithms/software required that have beendeveloped by the specific science investigationteam which can be integrated with the facilitysoftware, these could be loaded into the VME bussystem in the combustion rack; or if a controller isincluded in the experiment specific hardware, thenthe specific science investigation team would beresponsible for software that would reside on thecontroller.

E. Logistics Scenario:

A logistics scenario is the concept forgetting experiments to the space station,operating them in the FCF, and bringing thescience results back to Earth. The current conceptfor getting experiments to the space station is ascargo aboard a space vehicle. Once on-orbit, anEMS would be installed into the Combustion

Module by an astronaut. Installation of the EMSwould include making all hardware connectionswith the FCF (e.g. power, data, vacuum/vent,nitrogen), ve,,'Jfyingthese connections, andperforming functional check-out of the EMS,including hardware and software. The astronautwould then install the experiment specificdiagnostics, if necessary, around the chamber bymaking all hardware connections between theexperiment specific diagnostics and the opticalplate, verify these connections, and performfunctional check-out of the experiment.

The operations of the experiments arevery dependent on the experiment beingperformed. The concept for operations is tomaximize the effectiveness of crew time byautomating experiment functions when it isexperimentally and technologically practicalas wellas cost efficient.

Resources which need replenishment willbe planned for and the resupply of these will benegotiated with the #SSA and the resupply vehicleprograms.

Experiments which are completed will beremoved by an astronaut and packed for return toEarth in the appropriate carrier. Another EMS willbe installed into the FCF chamber. This concept ofcontinual resupply of experiments for the FCF willensure that the NASA microgravity combustionscience program has a consistent and constant on-orbit platform for performing microgravitycombustion science research.

V. Breadboard Plans/Accomplishments

The SS FCF Project is currently in theprocess of capturing all of the requirements thatwill have to be met. A necessary part of this phaseis to demonstrate early in the life cycle of a projectthat systems can be designed to meet keyperformance parameters. This may includedevelopment of new technologies to meet theseneeds. Most often, this is addressed bybreadboard testing of systems that potentially willbe used in the final design. Two breadboards arecurrently in work and another is being planned bythe SS FCF project. In addition, a number of otherprojects are currently performing breadboards thatare associated with the specific type of scienceinvestigation. The SS FCF breadboards and anumber of the breadboards external to the projectare described below.

A, Automated Fill

There are two methods for supplyinggases to the combustion chamber. One methodinvolves bringing pre-mixed gases to the stationand flowing them into the chamber. This limitstheability to change concentrations. The other optionis to perform mixing of gases on orbit. This involvestransporting pure gases, or nominal mixtures toorbit, and then mixing or adjusting theconcentrations as needed for the test points.Since this provides the greatest flexibility, on-orbitmixing is the preferred method. In order todemonstrated the feasibility of on-orbit mixing toprecise concentrations, the FCF projectdeveloped and tested an automated fillbreadboard. This breadboard utilized the partialpressures method for mixing the gases. A flowmeter was used to reduce the flow rate as pressurelevels were reached, allowing for improvedaccuracy. An evaluation of the final mixture wasmade using a gas chromatograph. Results haveshown accuracies of 1-2% of the smallestconstituent (down to 4%) in mixtures of helium andnitrogen. This technology can be extended toflight hardware.

B. Liquid Vaporization

A number of the diluents, including C02

and SF6, that are planned to be used in the facilityliquify at fairly low pressures. In order to minimizethe volume of the gases that will be transported tothe space station, it is desirable that these diluentsbe transported as room temperature liquids. Thisrequires a method to allow them to return to gas onorbit. This 'also requires that on orbit mixing be

implemented. Breadboard tests are on going toprove methods to convert the liquids back intogases as they are being used. This breadboardexpected to be completed by early 1995.

G, ExhausWent

The combustion module utilizes the spacestation vent system to remove unused gases andproducts of combustion. The current requirementson what can be vented into the space station ventsystem are very restrictive. A breadboard isplanned tOdetermine the feasibility andperformance of various methods of processing thegases so that they meet the interface

6

requirementsonspeciesandconcentration.Someofthetechniquesto beevaluatedaremolecularsievesandcatalyticoxidation.Thistestingwillincludeactualcombustionofcandidatetestpointssothattheproductsof combustioncanbe characterized before being processed. If thischaracterization is known from previous tests, thengas mixtures will be prepared to simulate theproducts of combustion.

D. $S FCF Breadboard Summary_

Other breadboards, beyond thosedescribed above, may be identified andimplemented during the next few years to reducetechnical risk and demonstrate feasibility. One ofthe breadboards being considered is a breadboardto demonstrate high resolution video imaging thatmight be required for droplet type combustionexperiments. There are also a number ofbreadboards being conducted for the fluidsmodule that may have potential for use in thecombustion module. One of these is called the

Automated Positioning and Tracking (APT)breadboard. The APT breadboard is

demonstrating that two orthogonal cameras withmicroscopic lenses can be used to image smallfeatures of interest, such as droplets, and track themotion of the feature. The system will be able torecognize a feature of interest, such as a droplet offuel, determine the camera motion required tokeep it within the field of view, translate thecameras while keeping the image in focus andretain image resolution, and maintain knowledge ofthe camera image relative to a fixed pointofreference.

E. External Breadboard_

There are currently a number of projectsthat fall into the SS FCF combustion scienceenvelope that are also doing breadboard testing.Although the exact science may not be performedin the SS FCF, many of the techniques developedin the breadboards may be applicable, and will beadapted as necessary.

CM-1 The CM-1 project has performed anumber of breadboards during the developmentphase. Silica gel, lithium hydroxide and hopcalite inprocessing products of combustion werecharacterized. The thermal effects of gas bottledischarge and pressurization of the combustionchamber was studied. The effect of microgravity on

mass flow contrgllers was studied. The ability ofsoot sampler mechanisms to meet sciencerequirements was demonstrated. Many of thediagnostics used by CM-1 were also demonstratedto be acceptable for use in the CombustionModule.

Droplet Combustion Experiment(DCE)The DCE project has demonstrated the ability todeploy a droplet with minimal residual velocity andigniteit, which is critical to future microgravitydroplet combustion experiments.

Spread Across Liquids(SAL) The SALproject has demonstrated the use of a spaceflightoperational color schlieren imaging system.

DARTfire The DARTfire project hasdemonstrated the capability to acquire videoimaging data over a wide range of frequencies.

F. LeRC Microgravity Combustion AdvancedDiagnostics Work

The Microgravity Combustion AdvancedDiagnostics Group at LeRC is working to developmany of the advanced diagnostics techniques thatmay be required in the future. The FCF project willwork closely with this group to transitiontechniques as they are developed into thecombustion module. This group is pioneeringsuch systems as rainbow schlieren imaging, gasphase particle imaging velocimetry and multipointlaser dopier velocimetry.

VI, Summary

A conceptual design of a CombustionModule, which is part of the Space StationFluids/Combustion Facility, has been presented.The concept was developed to maximize use ofcommon hardware and software in order to

minimize development time and effort for a largenumber of combustion science investigations, andto provide maximum scientific return.

These objectives are met throughprovision of standard interfaces which support likeexperimental investigations in a commoncombustion chamber with common diagnostics.The Combustion Module provide a maximum ofcommon hardware and software with clearlydefined interfaces and standard data acquisitionand control capabilities.

The Combustion Module conceptsupports all of the classes of microgravity

7

combustionscientificinvestigationscurrentlyenvisionedbytheMicrogravityCombustionDisciplineWorkingGrouptobeperformedaboardtheInternationalSpaceStationAlpha.

P_ferences

[1] Thompson, R. L., et al, "ConceptualDesign for the Space Station Freedom ModularCombustion Facility", NASA TM 102037, January,1990.

[2] NASA, "Space Station Freedom ModularCombustion Facility Assessment WorkshopProceedings", May 17-18, 1989.

[3] Rohn, D. W., Morilak, D.P., Rhatigan, J.L.,and Peterson, T.T., "Conceptual Design of theSpace Station Fluids Module", SecondMicrogravity Fluid Physics Conference, 21-23June, 1994.

©

Figure IV-1 Space Station Fluids/Combustion Facility Concept

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Figure IV-2 Core Systems Diagram

FigureIV-3

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Figure IV-4 Structure of RameBalls at Low Lewis Number Expenment Mounting Structure

lO

VA °

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Solenoid ValveAssembly

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RemovableFuel Nozzle

Figure IV-5 Laminar Soot Processes Experiment Mounting Structure

Droplet Deployment

Needle (Shown Retracted)

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Figure IV-6 "D;'or_l_(Combustion Experiment Mounting Structure

11

FormApprovedREPORT DOCUMENTATION PAGE OMB No. 0704-0188

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1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE 3. REPORT TYPE AND DATES COVERED

November 1994 Technical Memorandum

4. TITLE AND SUBTITLE S. FUNDING NUMBERS

Conceptual Design of the Space Station Combustion Module

6. AUTHOR(S)

Daniel P. Morilak, Dennis W. Rohn, and Jennifer L. Rhatigan

7. PERFORMINGORGANIZATIONNAME(S)ANDADDRESS(E5)

National Aeronautics and Space AdministrationLewis Research Center

Cleveland, Ohio 44135-3191

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National Aeronautics and Space AdministrationWashington, D.C. 20546-0001

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NASA TM- 106788

AIAA-95-0692

Prepared for the 33rd Aerospace Sciences Meeting and Exhibit sponsored by the American Institute of Aeronautics and

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13. ABSTRACT (Maxlmum 2OO'words)

The purpose of this paper is to describe the conceptual design of the Combustion Module for the International Space

Station Alpha (ISSA). This module is part of the Space Station Fluids/Combustion Facility (SS FC'F) under developmentat the NASA Lewis Research Center. The Fluids/Combustion Facility is one of several science facilities which are being

developed to support microgravity science investigations in the US Laboratory Module of the ISSA. The SS FCF will

support a multitude of fluids and combustion science investigations over the lifetime of the ISSA and return state-of-the-

art science data in a timely and efficient manner to the scientific communities. This will be accomplished through

modularization of hardware, with planned, periodic upgrades; modularization of like scientific investigations that make

use of common facility functions; and through the use of orbital replacement units (ORUs) for incorporation of new

technology and new functionality. The SS FCF is scheduled to become operational on-orbit in 1999. The CombustionModule is presently scheduled for launch to orbit and integration with the Fluids/Combustion Facility in 1999. The

objectives of this paper are to describe the history of the Combustion Module concept, the types of combustion science

investigations which will be accommodated by the module, the hardware design heritage, the hardware concept, and thehardware breadboarding efforts currently underway.

14. SUBJECT TERMS

Microgravity; Combustion; Space station facilities

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