Karen J. Weiland, Frank G. Gati, Myron E. Hill, and Terence F. O’Malley

Glenn Research Center, Cleveland, Ohio

Robert L. Zurawski

Johnson Space Center, Houston, Texas

The Fluids and Combustion Facility:

Enabling the Exploration of Space

NASA/TM—2005-213973

December 2005

IAC–05–A2.5.04
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Karen J. Weiland, Frank G. Gati, Myron E. Hill, and Terence F. O’Malley

Glenn Research Center, Cleveland, Ohio

Robert L. Zurawski

Johnson Space Center, Houston, Texas

The Fluids and Combustion Facility:

Enabling the Exploration of Space

NASA/TM—2005-213973

December 2005

National Aeronautics and

Space Administration

Glenn Research Center

Prepared for the

56th International Astronautical Congress

sponsored by the Japan Aerospace Exploration Agency

Fukuoka, Japan, October 17–21, 2005

IAC–05–A2.5.04
Acknowledgments

The NASA Headquarters Exploration Systems Mission Directorate and the Human Science and Research

Technology Program provides funding for the FCF and support for combustion and fluid physics experiments. The

authors gratefully acknowledge the FCF project team at ZIN Technologies, Inc. for their excellent work and

contributions to develop the FCF.

Available from

NASA Center for Aerospace Information

7121 Standard Drive

Hanover, MD 21076

National Technical Information Service

5285 Port Royal Road

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Trade names or manufacturers’ names are used in this report for

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Aeronautics and Space Administration.

Available electronically at http://gltrs.grc.nasa.gov
NASA/TM—2005-213973 1

The Fluids and Combustion Facility:

Enabling the Exploration of Space 

Karen J. Weiland, Frank G. Gati, Myron E. Hill, and Terence F. O’Malley 

National Aeronautics and Space Administration 

Glenn Research Center 

Cleveland, Ohio 44135 

Robert L. Zurawski 

National Aeronautics and Space Administration 

Johnson Space Center 

Houston, Texas 77058 

Abstract 

The Fluids and Combustion Facility (FCF) is an 

International Space Station facility designed to support 

physical and biological research as well as technology 

experiments in space. The FCF consists of two racks called 

the Combustion Integrated Rack (CIR) and the Fluids 

Integrated Rack (FIR). The capabilities of the CIR and the 

FIR and plans for their utilization will support the 

President’s vision for space exploration. The CIR will 

accommodate physical research and technology experiments 

that address needs in the areas of spacecraft fire prevention, 

detection and suppression, incineration of solid wastes, and 

power generation. Initial experiments will provide data to 

support design decisions for exploration spacecraft. The CIR 

provides a large sealed chamber in a near-weightless 

environment. The chamber supports many simulated 

atmospheres including lunar or Martian environments. The 

FIR will accommodate experiments that address needs for 

advanced life support, power, propulsion, and spacecraft 

thermal control systems. The FIR can also serve as a 

platform for experiments that address human health and 

performance, medical technologies, and biological sciences. 

The FIR provides a large volume for payload hardware, 

reconfigurable diagnostics, customizable software, active 

rack-level vibration isolation, and data acquisition and 

management in a nearly uniform temperature environment. 

Introduction 

In January 2004, President George W. Bush outlined an 

exciting new space exploration vision for NASA. The 

exploration programs will seek answers to profound 

questions of our origins, whether life exists beyond Earth, 

and how we could live on other worlds. The Fluids and 

Combustion Facility (FCF) is an International Space Station 

(ISS) facility designed to support physical and biological 

research as well as technology experiments in space that will 

support the new vision for space exploration. The FCF 

consists of two modular, reconfigurable racks: the 

Combustion Integrated Rack (CIR) and the Fluids Integrated 

Rack (FIR), as shown in figures 1 and 2. The racks will be 

in the U.S. Laboratory Module and will operate primarily by 

telescience with only reconfiguration and maintenance 

performed by the crew. 

The CIR will accommodate experiments that address 

critical needs in the areas of spacecraft fire prevention, 

detection and suppression, incineration of solid wastes, and 

power generation. Initial experiments will provide data to 

support design decisions for exploration spacecraft. The CIR 

provides a large environmental chamber in which the space 

environment or lunar, Martian, or other planetary surface 

environments may be simulated. It can also serve as a test 

bed to mature systems and concepts to high technology 

readiness levels for exploration missions. 

The FIR will accommodate payloads that address critical 

technology development and maturation needs for advanced 

life support (i.e., air revitalization, water reclamation, etc.), 

power, propulsion, and spacecraft thermal control systems. 

Payloads addressing boiling/condensation heat transfer, 

liquid vapor interface control, liquid/vapor 

evaporation/condensation, and multiphase flow, as they 

relate to the technology needs of various exploration 

spacecraft subsystems, will be the focus of investigations. 

The FIR provides a large, contiguous volume of about 

0.5 cubic meter for experimental hardware, easily 

reconfigurable diagnostics, customizable software, active 

rack-level vibration isolation, data acquisition and 

management, and various other subsystems that will support 

a wide range of uses. It can also serve as a platform for 

experiments that address human health and performance, 

medical technologies, and biological sciences. 

Common Rack Components 

This section describes the subsystems common to both 

FCF racks. The use of common hardware reduces the 

design, development and life cycle costs, increases crew 
NASA/TM—2005-213973 2

Figure 1.—The Fluids and Combustion Facility 

Combustion Integrated Rack. At the top is the 

Fuel/Oxidizer Management Assembly, in the 

center is the combustion chamber, and at the 

bottom are the Electrical Power Conversion Unit 

(left) and Input/Output Processor (right). 

efficiency by using common procedures, and allows for 

common sparing on orbit. (The sections on each individual 

rack describe the subsystems unique to each one.) 

International Standard Payload Rack 

The International Standard Payload Rack (ISPR) provides 

the supporting and mounting elements for the CIR and FIR 

subsystems and mechanical connections to the U.S. 

Laboratory Module. A set of slides mounted on the vertical 

sides of the rack provides attachment for an optics bench. 

The optics bench can translate out and rotate down for 

access to both sides as shown in figure 3. Both racks provide 

bi-fold doors with upper and lower halves. They provide 

acoustical, optical, and thermal isolation between the racks 

and the environment of the U.S. Laboratory Module. The 

doors contain six replaceable panel windows. The doors are 

closed during powered operations. 

Figure 2.—The Fluids and Combustion Facility 

Fluids Integrated Rack. In the center is the optics 

bench and at the bottom are the Electrical Power 

Conversion Unit (left) and Input/Output Processor 

(right). 

Electrical Power System 

The Electrical Power Conversion Unit (EPCU) functions 

as the main power conditioning unit and power supply for 

each rack. The EPCU takes the 120 VDC power provided by 

the ISS and converts it to the 28 VDC required by most FCF 

packages. In addition, it makes available 120 VDC for the 

Fire Detection and Suppression System smoke detector, the 

Active Rack Isolation System controller, and, if it is 

required, to the sub-rack experiment. A total of 1600 W is 

available at 28 VDC and 1450 W at 120 VDC. 
NASA/TM—2005-213973 3

Figure 3.—The Combustion Integrated Rack with the 

optics bench translated and rotated. Visible on the 

back of the optics bench is the combustion 

chamber. 

Environmental Control Subsystems 

The FCF provides environmental control subsystems 

(ECS) that remove heat, provide fire detection and 

suppression, and provide interfaces to the ISS-supplied 

gases and vacuum vent lines. 

The Water Thermal Control System (WTCS) provides 

water-cooling of all FCF equipment by removing their heat 

and transferring it to the ISS Internal Thermal Control 

System Moderate Temperature Loop. The WTCS provides 

cooling to the Air Thermal Control Unit (ATCU) and other 

FCF hardware in the primary loop. A secondary loop may 

cool payload hardware as required. Flexible hoses with 

quick disconnects allow for reconfiguration. The WTCS can 

remove up to 3000 W of waste thermal energy. 

The ATCU resides in the top of each rack. It contains an 

air/water heat exchanger and two fans that circulate cooling 

air to the rack packages. In the CIR, the fans draw warm air 

from the rear of the rack and push it through the heat 

exchanger into the optics bench. In the FIR, the fans draw 

air from the optics bench in the rear of the rack and push it 

through the heat exchanger into the front of the rack. The 

ATCU can remove up to 1650 W of waste thermal energy. 

The Fire Detection and Suppression System provides 

detection and suppression in case of fire in the rack. The 

ATCU provides rack air circulation past an ISS smoke 

detector. The ISS shuts off power to the rack if the detector 

triggers. Then, if required, a crewmember could discharge 

an ISS Portable Fire Extinguisher containing carbon dioxide 

into a hole on the front panel of the rack to extinguish any 

fire. 

The Gas Interface Subsystem provides access to ISSprovided gaseous nitrogen and Vacuum Exhaust and 

Resource Systems. Nitrogen gas is available up to 827 kPa 

(120 psia). The VES provides for removal of waste gases 

from the system. The VRS is a low-flow system used 

primarily to maintain rack sub-systems at a vacuum. The 

rack sub-systems or experiment gases must meet ISSallowable limits for contaminants to be eligible for venting 

through the ISS vent line. 

Avionics Subsystems 

The CIR and the FIR use several common avionics 

subsystems: the Input/Output Processor (IOP), Image 

Processing and Storage Unit (IPSU), Diagnostic Control 

Module (DCM), and the Station Support Computer (SSC). 

The IOP is the main processor within the CIR and the 

FIR. It provides rack-level health and status monitoring, 

command and data processing, data management, control 

functions, and time synchronization. The IOP provides 

communications with the ISS through Ethernet and low and 

high rate data lines. It stores data on two 180 GB removable 

hard drives prior to downlinking by the ISS. The IOP 

accepts commands from either the ground by uplink to the 

ISS, or from the SSC. 

Either rack can use common IPSUs. The IPSU supports a 

variety of camera formats. Two models of the common 

IPSU are available: the C-IPSU and the C-IPSU-A. The CIPSU supports image acquisition from high-speed digital 

and IEEE 1394 (Firewire). The C-IPSU-A supports image 

acquisition from IEEE 1394 or analog video. In the CIR, 

two IPSUs can be stacked at certain mounting locations on 

the optics bench. Both types of IPSUs have two 36 GB hard 

drives and provide analog video output for experiment 

monitoring. 

The DCM is a package module that provides power and 

control signals to the imaging portion of a camera package, 

or to an illumination package. It mounts on the optics bench. 

The SSC is a laptop computer supplied by the ISS that 

connects to the IOP. It mounts on the front of the rack. The 

SSC allows the crew to view all science, health and status, 

and command screens. The crew can use the SSC to 

communicate with the FCF racks. 

Space Acceleration Measurement System 

A Space Acceleration Measurement System (SAMS) 

triaxial sensor head measures the microgravity acceleration 
NASA/TM—2005-213973 4

environment in the rack at its location on the optics bench. 

In the CIR, it mounts on the front near the combustion 

chamber. In the FIR, SAMS can be located anywhere in the 

payload working volume. This allows payloads to place the 

SAMS unit close to the area of interest. SAMS can measure 

microgravity accelerations from 1×10–6 to 0.01 g and 

provide three orthogonal measurements from 0.01 to 

200 Hz. SAMS sends the data to the IOP, which then 

downlinks it as part of the telemetry. The Principal 

Investigator Microgravity Services (PIMS) team located at 

NASA Glenn extracts the SAMS data and provides it to the 

experiment team. 

Software 

The FCF makes extensive use of software because it is 

designed to operate primarily without crew involvement 

using telescience. The Telescience Support Center (TSC) at 

the NASA Glenn Research Center will support flight and 

some ground operations. The software accommodates new 

hardware and software upgrades. It is modular to minimize 

the amount of new software required for a new 

configuration. The ground operators can modify the flight 

software by uplinking new software from the ground. 

The FCF flight software performs command and data 

processing, control, caution and warning, health and status 

monitoring, and timing functions. The operating system is 

VxWorks®. Programming languages are C++ and Java. 

Common subsystems software interacts with the IOP, ECS, 

C-IPSU, C-IPSU-A, DCM, and SSC. Packages unique to the 

CIR or the FIR have rack-specific software written for them. 

The FCF ground software performs commanding of the 

flight unit, and receiving and viewing telemetry. FCF sends 

much of the data to the Earth via downlinking. The TSC 

receives and processes the payload data, and provides it to 

the experiment team, who can then use it to plan further 

experiment operations. The FCF operators at the TSC will 

have operator interfaces to display health and status, data, 

command and control, crew display, operator logs, and 

reporting. The TSC will archive the data for a ten-year 

period. Ground support units, crew trainers, and simulators 

also use ground software. 

CIR Components 

The CIR contains most of the hardware and software 

necessary for conducting combustion experiments. It will 

accommodate a range of combustion experiments while 

meeting the ISS requirements and limitations such as safety, 

power and energy, cooling, mass, crew time, stowage, 

resupply flights, and data downlink. The major subsystems 

of the CIR are the ISPR, Passive Rack Isolation System, 

optics bench, combustion chamber, diagnostics, 

fuel/oxidizer management assembly, environmental control 

subsystems, electrical power system, avionics subsystems, 

flight and ground software, and interfaces for experimentspecific hardware. The previous sections described the 

common subsystems. 

Each investigation will customize the facility with 

experiment packages that contain a small amount of 

hardware and software. The CIR design allows for the 

removal and replacement of different experiment packages 

within the combustion chamber. A replaceable Principal 

Investigator (PI) Avionics box mounts on the optics bench 

and provides for PI command and control of the experiment. 

Passive Rack Isolation System 

The ISPR contains a Passive Rack Isolation System 

(PaRIS) to isolate it from ISS and U.S. Laboratory 

vibrations. PaRIS isolates an entire ISPR. The PaRIS system 

provides passive attenuation by eight spring-damper 

isolators. The acceleration environment provided by PaRIS 

is frequency dependent, but for frequencies between 0.01 

and 10 Hz, a model predicts that PaRIS will limit 

accelerations in the CIR to the micro-g level (ref. 1). This 

prediction used a conservative model in which all potential 

disturbers are active. Further reduction of the microgravity 

environment beyond that possible by PaRIS may be 

accomplished through operational planning to limit the 

potential disturbers active during the experiment operation 

time. 

Optics Bench 

The optics bench provides structural support, electrical 

connections, and mounting locations for other hardware, 

such as a chamber, gas handling system, and diagnostics. It 

spans two-thirds of the rack vertically and mounts on slides 

so that it slides out from the rack and folds down for access 

to both sides. The wiring harnessing and cooling airflow are 

internal to the bench. Diagnostics are interchangeable via a 

quick-latch mechanism at any of eight universal mounting 

locations around the combustion chamber. These locations 

provide air-cooling, electrical power, and communication 

and data interfaces. 

Combustion Chamber 

The combustion chamber is a cylindrical pressure vessel 

with domed end caps that mounts centrally to the optics 

bench. It has a volume of 100 liters and an internal diameter 

of 0.40 m and a length of 0.78 m. The front lid opens for onorbit access to the inside of the chamber. The chamber has 

eight replaceable windows. The first launch set is made of 

sapphire. The chamber has a maximum design pressure 

differential of 827 kPa (120 psia). Four pressure transducers 

provide for pressure measurements. Electrical, vacuum, gas, 

venting, and other resources connect through an interface 

resource ring near the front of the chamber. 
NASA/TM—2005-213973 5

Chamber Insert Assembly 

An experiment connects its hardware to the chamber by a 

chamber insert assembly (CIA), as shown in figure 4, which 

mounts on guide rails in the chamber. The chamber insert 

assembly is a framework for the mounting of internal 

components such as a burner, a nozzle, or a sample holder, 

diagnostic sensors, flow tunnel, and interface hardware. Its 

maximum length is 0.60 m long if the chamber mixing fan is 

present. The experiment team supplies the CIA. 

Diagnostics 

The diagnostics measurement systems perform the 

required and desired measurements of the combustion 

phenomena. Some of these are imaging systems that include 

the imaging device, an illumination source, and an imageprocessing package. Digital imaging systems provide for 

data fidelity and ease in data transfer and storage. 

The diagnostics measurements segment into two 

categories. The CIR provides one set entirely, including the 

measurement device, power, control, and data collection and 

storage. These include visible and ultraviolet imaging, 

pressure measurement, gas composition, and accelerometry. 

The experiment team and the CIR jointly provide the other 

set of diagnostics. The diagnostics may include infrared and 

color imaging, temperature measurements, and flame 

radiation. 

The diagnostic devices provided by the CIR are the HighBit Depth Multispectral Imaging Package (HiBMs), the 

Illumination Package, and the Low-Light Level Ultraviolet 

Imaging Package (LLL-UV). The HiBMs consists of a 

telecentric optical system and a high resolution, 12-bit 

digital camera. The initial use of the HiBMs is for viewing 

backlit droplet images. A tunable liquid crystal spectral filter 

in conjunction with the Illumination Package allows for soot 

volume fraction and soot temperature measurements. The 

Illumination Package provides an illumination source to the 

chamber that consists of a collimated optical system and two 

identical light-emitting diode sources. The initial use of the 

Illumination Package is as a backlight source for the 

viewing of droplet images. The LLL-UV provides images of 

flames or objects at low radiance levels. The LLL-UV has 

an intensifier with a spectral range of 280 to 700 nm coupled 

to a monochrome camera. A filter at 310 nm provides for 

imaging of OH emission from flames. 

Other sections discuss pressure measurements, gas 

composition, and accelerometry. 

Fuel/Oxidizer Management Assembly 

The Fuel/Oxidizer Management Assembly (FOMA) 

provides gaseous fuels, oxidizers, and diluents to the 

combustion chamber. The FOMA also provides gas 

sampling and analysis of the chamber contents, and cleanup 

Figure 4.—This chamber insert assembly is used for 

studying flame suppression with droplet 

combustion. 

and venting to space through the ISS vacuum exhaust 

system. 

The gas delivery system contains gas supply bottles, 

valves, pressure regulators and switches, and mass flow 

controllers. The gas bottles may be 1.0, 2.25, or 3.8 liters 

and mount on the front of the optics bench for easy 

replacement by the crew. Up to four bottles may be used at 

one time. The maximum mole fraction of oxygen allowed in 

the bottle depends on its size: 1.0 liter up to 80 percent O2, 

2.25 liters up to 50 percent O2, and 3.8 liters up to 

30 percent O2. The maximum oxidizer flow rate is 

30 standard Liters per minute (slpm) per manifold for a total 

of 90 slpm (using three manifolds); maximum fuel flow rate 

is two slpm for propane. The gas delivery system performs 

on-orbit gas mixing by either partial pressure or by dynamic 

blending in the chamber. 

A gas chromatograph (GC) analyzes the chamber 

contents. The GC is a repackaged commercial unit with 

three independent column modules that use helium and 

argon carrier gases. Two 500 mL bottles, which are 

changeable by the crew, contain the carrier gases. The GC 

can detect oxygen, inerts such as nitrogen or helium, fuels 

such as hydrogen, methane, methanol, and propane, and 

combustion products such as carbon dioxide, carbon 

monoxide, benzene, and formaldehyde at compositions 

ranging from 0.1 to 100 percent. The GC is not planned for 

use at initial installation of the CIR in ISS. 

A filter cartridge removes particulates, water, and other 

contaminants from the gas to condition it for the next test 

point or prior to venting. One of two recirculation pumps 

pulls the gas through the recirculation loop at a rate of up to 

9 slpm. Each experiment customizes the adsorber cartridge, 

which may contain substances such as lithium hydroxide, 

activated carbon, silica gel, and molecular sieve. A mass 

flow controller controls the rate at which gas vents. An 
NASA/TM—2005-213973 6

oxygen sensor measures the concentration of oxygen in the 

vent line. The FOMA system will not vent unless the 

oxygen concentration is less than 28 percent. A dew point 

sensor also assures that the level of water in the vented gas 

stream is acceptable. 

FOMA Control Unit 

The FOMA Control Unit (FCU) controls the FOMA 

components in the CIR. It monitors and stores all pressures, 

temperatures, and mass flow rates during gas blending and 

experiment operations, controls the GC for chamber 

sampling, and monitors the status of all FOMA hardware for 

transmittal to the ground via the IOP. The FCU commands 

set points of devices such as valves and mass flow 

controllers. 

Principal Investigator Avionics Box 

The optics bench contains a mounting location for the 

Principal Investigator (PI) Avionics Box. The experiment 

team designs the box, which communicates to the IOP and 

the chamber insert assembly. It will typically contain circuit 

boards, power supplies, software, and other avionics that the 

CIR does not supply. 

FIR Components 

The FIR provides the necessary hardware and capabilities 

for conducting technology development and maturation 

experiments on-board ISS in support of space exploration in 

areas such as advanced life support, power and propulsion. 

Its flexible volume and interfaces can accommodate a wide 

range of payloads while meeting the ISS requirements and 

limitations such as safety, power, cooling, mass, crew time, 

stowage, resupply flights, and downlink. The major 

subsystems of the FIR are the ISPR, Active Rack Isolation 

System (ARIS), optics bench, diagnostics, data acquisition 

and control, environmental control, electrical power, flight 

and ground software, and interfaces for payload-specific 

hardware. As with the CIR, each payload can customize the 

facility with payload-provided hardware and software. The 

FIR design allows for payload-provided hardware on the 

front and back of the optics bench. FIR-provided hardware 

that is not being utilized can be removed if required and 

even replaced with payload-provided hardware. 

Common subsystems are described earlier in this paper. 

The following sections describe the FIR unique subsystems. 

Active Rack Isolation System 

If required, the Active Rack Isolation System (ARIS) can 

be used to enhance the microgravity environment for 

payloads in the FIR. Mounted in the ISPR, ARIS minimizes 

vibratory transmissions to and from the rack. ARIS utilizes 

three accelerometers to measure the microgravity 

environment in the rack. Based on the measured 

accelerations, the ARIS system, unlike CIR’s PaRIS system, 

applies reactive forces, between the FIR and ISS, through 

eight actuators to minimize transmission of vibratory 

disturbances. 

Optics Bench 

The centerpiece of the FIR structural subsystem is the 

optics bench. The optics bench provides a mounting surface 

for FIR light sources and avionics packages on the back of 

the bench and for payload hardware on the front or back of 

the bench. Depending on the use of the FIR-provided 

hardware, the optics bench will be able to accommodate up 

to 300 kg of payload hardware and provides a front 

mounting surface of 1100 by 895 by 495 mm. The front of 

the optics bench provides T-Slots and 1/4-28 threaded holes 

for mounting of payload hardware. The T-slots enable 

precise mounting of payload hardware, including optical 

components. 

The optics bench is designed so that, in the unpowered 

mode, it can be translated out of the rack and rotated 

forward, as shown in figure 5, to allow the crew easy access 

to hardware mounted on the back of the optics bench. 

During powered operations the FIR optics bench is in the 

stowed position and the rack doors are closed. 

Diagnostics 

FIR provides a color camera, Nd:YAG laser and white 

light source as part of the initial facility development. 

The Color Camera is a 24 bit, 3-chip Charged Coupled 

Device (CCD) analog color camera as shown in figure 6. 

The camera has a one-third inch array with a pixel density of 

768 by 484 pixels. The camera’s frame rate is settable up to 

30 frames per second (fps) and shutter speed is settable from 

1/60 of a second down to 1/10,000 of a second. In auto 

shutter mode, shutter speeds down to 1/50,000 of a second 

can be achieved. The color camera has a small remote head, 

32 mm wide by 40 mm high by 40 mm diameter, to 

facilitate camera integration in congested areas. The color 

camera utilizes a standard C-mount for lenses. 

The White Light Package, shown in figure 7, is located 

on the back of the FIR optics bench. The package consists of 

two 50 W metal halide bulbs subassemblies. Each 

subassembly has a fiber optic quick disconnect for 

attachment of a fiber bundle. 

Adjusting an aperture knob located on a subassembly will 

vary the light intensity delivered through the fiber bundle 

attached to that subassembly. While the FIR provides a fiber 

bundle with a lens attachment, payloads can provide a 

specialized fiber bundle such as a bundle incorporating a 

light panel or ring light. Fibers are routed to the front of the 

optics bench from the white light package on the back of the 

bench through the fiber feedthrough located on the side of 

the bench. 
NASA/TM—2005-213973 7

Figure 5.—The Fluids Integrated Rack with the Optics 

Bench translated and rotated. On the back of the bench 

are the White Light, Nd:YAG Laser, and the Fluids 

Science Avionics Packages. 

Figure 6.—Color Camera Package. The Color Camera 

Controller is on the left and the Color Camera Photo Head 

is on the right. 

The 532 nm Nd:YAG Laser Package, shown in figure 8, 

is located on the back of the FIR optics bench. When using 

the laser, a fiber optic cable from the laser is routed from the 

back of the bench through the fiber feedthrough to payload 

hardware on the front of the optics bench. A quick 

disconnect at the end of the fiber optic cable allows for easy 

hookup to payload hardware. 

The laser is capable of providing a minimum power of 

100 mW to the payload out of the FIR-provided fiber optic 

cable. The laser output power can be varied from 0 to 

100 percent of the maximum power. A tap coupler located at 

the output of laser measures laser power delivered to the 

payload. 

In addition to the FIR diagnostics discussed above, the 

CIR cameras can also be used in the FIR. 

Figure 7.—White Light Package. 

Figure 8.—Nd:YAG Laser Package. 

Data Acquisition and Control 

The Fluids Science and Avionics Package (FSAP) can 

provide the primary control in carrying out an experiment. 

Through the FSAP, the payload can execute an experiment 

by controlling the FIR diagnostics and avionics packages as 

well as payload hardware. Payload developers can download 

their own custom software into the FSAP for experiment 

control. The FSAP provides a standard set of computer data 

acquisition and control functions for use by the payload. The 

FSAP provides the following functions: motion control, 

analog to digital channels, digital to analog channels, digital 

inputs and outputs, external and internal triggers, RS-422, 

analog frame grabber and CAN bus. The FSAP has two 

36 GB hard drives for storing analog and digital data, as 

well as analog video images captured by the analog frame 

grabber. 
NASA/TM—2005-213973 8

Development Status 

NASA Glenn Research Center in Cleveland, Ohio is 

developing the FCF under a prime contract with ZIN 

Technologies, Inc. The overall system has concluded its 

flight hardware fabrication phase and package-level testing, 

and is in the process of completing rack-level testing. Upon 

completion of the testing at NASA Glenn, the racks will be 

shipped to the NASA Kennedy Space Center for additional 

testing in the Payload Test and Checkout System (PTCS). 

The PTCS provides a final functional checkout of the rackto-ISS interfaces, a check of the physical fit, and interface 

testing of the fluids, structure, communication, and 

command and data handling interfaces. The Multi-Purpose 

Logistics Module (MPLM) will contain the racks for launch. 

Several variables remain that will effect the ultimate FCF 

launch date, such as the Shuttle Return to Flight date, the 

revised ISS Assembly Sequence, ISS resources available to 

payloads, and the manifesting priority of the payload and its 

relevance to exploration research. The current schedules 

shows launch of the FCF in 2007. 

Initial Experiments 

Supporting the Exploration Vision 

In support of the exploration vision, NASA realigned the 

microgravity research program to support the major 

milestones such as a human moon landing and establishment 

of a lunar exploration test bed. Recent agency emphasis is 

on developing experiment areas that more directly support 

the technological needs of NASA missions. The design and 

operation of exploration spacecraft and partial-gravity 

habitats present new challenges for combustion in the areas 

of fire safety, waste incineration, and power generation. A 

major goal of NASA’s combustion research program is to 

support the exploration vision by gaining increased 

understanding and insight into the behaviors of microgravity 

and partial-gravity flames (ref. 2). The areas of emphasis for 

fluids physics include life support, power, propulsion, and 

thermal control systems. More specifically, research areas 

such as boiling/condensation heat transfer, liquid vapor 

interface control, and multiphase flow will be particularly 

applicable. 

Combustion Research Utilization 

The combustion areas of interest include but are not 

limited to spacecraft fire prevention, detection and 

suppression, incineration of solid wastes, and power 

generation. Near-term experiments will support the 

exploration vision. 

When possible, similar investigations will fly at the same 

time to increase the use of common hardware and 

diagnostics. A set of multi-user chamber inserts will support 

experiments in droplets and solid fuels. Commercial and 

international investigations will provide their own chamber 

inserts or other resources in exchange for using a NASA 

insert. Multiple flight investigations and one or more 

commercial investigations are currently planning to use the 

CIR over the first few years of operation. Several 

international investigations are at the conceptual stage. 

The initial investigations will study the combustion of 

small, spherical, individual fuel droplets. They will 

demonstrate the use of the CIR and will use a common 

insert and similar measurements. They will determine the 

flammability of a fuel droplet in limiting atmospheres of 

oxygen. Solid fuel experiments will focus on the 

quantification of material flammability in low pressure, 

increased oxygen atmospheres. The fuels include wire 

insulation, advanced composites, packing foam, and 

materials for inflatable structures. 

Fluids Research Utilization 

The Fluids Integrated Rack (FIR) will support technology 

development and maturation to enable storage/transfer of 

two-phase fluids, characterize two-phase heat transfer for 

potential power systems, support development of multiphase environmental controls for life support systems, and 

support human health in physiological/medical systems 

research to enable long term missions to the moon and Mars. 

Initial investigations on FIR will study thin film heat 

transfer applicable to wickless heat pipes, packed bed 

reactors and condensing heat exchangers. Development and 

utilization of wickless heat pipes and condensing heat 

exchangers will reduce the mass and complexity of thermal 

control systems for space exploration. Development and 

utilization of packed bed reactors are essential for compact 

and reliable water recovery systems. 

The flexibility of the FIR (i.e., large volume for 

experimental hardware, easily reconfigurable diagnostics, 

and customizable software) allows accommodation of such 

experiments, and even ones from other disciplines such as 

biotechnology. When possible, similar investigations will fly 

at the same time to increase the use of common hardware 

and diagnostics. One example is the Light Microscopy 

Module, which will be used to conduct a thin film heat 

transfer experiment and can also accommodate biology 

related experiments. 

Summary 

The Fluids and Combustion Facility (FCF) is an 

International Space Station facility designed to support 

physical and biological research as well as technology 

experiments in space. The FCF consists of two racks called 

the Combustion Integrated Rack (CIR) and the Fluids 

Integrated Rack (FIR). The CIR will accommodate 

experiments that address needs in the areas of spacecraft fire 
NASA/TM—2005-213973 9

prevention, detection and suppression, incineration of solid 

wastes, and power generation. Initial experiments will 

provide data to support design decisions for exploration 

spacecraft. The FIR will accommodate experiments that 

address needs for advanced life support, power, propulsion, 

and spacecraft thermal control systems. It can also serve as a 

platform for experiments that address human health and 

performance, medical technologies, and biosciences. 

References 

1. Just, Marcus, “Final CIR Microgravity Assessment for 

Verification Closeout, Rev. A,” FTS-TM-029A, ZIN 

Technologies, Inc., Brook Park, OH, Nov. 8, 2004. 

2. Ruff, Gary A., Urban, David L., and King, Merrill K., 

“A Research Plan for Fire Prevention, Detection, and 

Suppression in Crewed Exploration Systems,” AIAA–

2005–0341, 43rd Aerospace Sciences Meeting and 

Exhibition, Reno, NV, January 2005. 
This publication is available from the NASA Center for AeroSpace Information, 301–621–0390.

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15

The Fluids and Combustion Facility: Enabling the Exploration of Space

Karen J. Weiland, Frank G. Gati, Myron E. Hill, Terence F. O'Malley,

and Robert L. Zurawski

International Space Station; Research facilities; Fluids; Combustion; Fire prevention;

Biotechnology; Space exploration

Unclassified -Unlimited

Subject Category: 37

Prepared for the 56th International Astronautical Congress sponsored by the Japan Aerospace Exploration Agency,

Fukuoka, Japan, October 17–21, 2005. Karen J. Weiland, e-mail: Karen.J.Weiland@nasa.gov, Frank G. Gati,

e-mail: Frank.Gati-1@nasa.gov, Myron E. Hill, e-mail: Myron.E.Hill@nasa.gov, and Terence F. O'Malley, e-mail:

TFOMalley@nasa.gov, NASA Glenn Research Center; and Robert L. Zurawski, e-mail: Robert.L.Zurawski@nasa.gov,

NASA Johnson Space Center. Responsible person, Karen J. Weiland, organization code PTO, 216–433–3623.

The Fluids and Combustion Facility (FCF) is an International Space Station facility designed to support physical and

biological research as well as technology experiments in space. The FCF consists of two racks called the Combustion

Integrated Rack (CIR) and the Fluids Integrated Rack (FIR). The capabilities of the CIR and the FIR and plans for their

utilization will support the President’s vision for space exploration. The CIR will accommodate physical research and

technology experiments that address needs in the areas of spacecraft fire prevention, detection and suppression, incineration of solid wastes, and power generation. Initial experiments will provide data to support design decisions for exploration

spacecraft. The CIR provides a large sealed chamber in a near-weightless environment. The chamber supports many

simulated atmospheres including lunar or Martian environments. The FIR will accommodate experiments that address

needs for advanced life support, power, propulsion, and spacecraft thermal control systems. The FIR can also serve as a

platform for experiments that address human health and performance, medical technologies, and biological sciences. The

FIR provides a large volume for payload hardware, reconfigurable diagnostics, customizable software, active rack-level

vibration isolation, and data acquisition and management in a nearly uniform temperature environment.