Technology Demonstration

National Aeronautics and Space Administration

A Researcher’s Guide to:
2

This International Space Station (ISS) Researcher’s Guide is published by the NASA ISS 

Program Science Office.

Author: 

David. M. Hornyak

Executive Editor: Amelia Rai

Technical Editor: Neesha Hosein

Designer: Cory Duke

Cover and back cover: 

a. The ISS is seen from an unusual angle during the shuttle Atlantis’ final 

fly-around in July 2011. The moon is visible above and to the right of the station. 

b. Art concept of Robonaut (R2) hand reaching out to EMU gloved hand with space and stars in the 

background. Photo taken in Building 32 - Robonaut Lab at NASA Johnson Space Center. 

c. Several tiny satellites are featured in this image photographed by an Expedition 33 crew member 

on the ISS. The satellites were released outside the Kibo laboratory using a Small Satellite Orbital 

Deployer attached to the Japanese module’s robotic arm on Oct. 4, 2012. Japan Aerospace 

Exploration Agency astronaut Aki Hoshide, flight engineer, set up the satellite deployment gear 

inside the lab and placed it in the Kibo airlock. The Japanese robotic arm then grappled the 

deployment system and its satellites from the airlock for deployment. A portion of the station’s solar 

array panels and a blue and white part of Earth provide the backdrop for the scene. 
3

Preface 5

ISS Technology Demonstration Program 6

Overview 6

Technology Readiness Level Advancement 7

In-Space Propulsion 7

Space Power and Energy 7

Robotics, Tele-Robotics and Autonomous Systems 8

Communication and Navigation 8

Life Support and Habitation Systems 8

Exploration Destination Systems 9

Science Instruments 9

Entry, Descent and Landing Systems 9

Materials, Structures and Manufacturing 10

Thermal Management Systems 10

Operational Processes and Procedures 10

ISS Accommodations 11

Internal 11

EXPRESS Rack 11

Station to Internal Facility Rack Resources 13

Aisle Deployed Payloads 13

Internal/External 13

Japanese Experiment Module Airlock 13

External 14

EXPRESS Logistics Carrier 21

Columbus Exposed Facility 21

Japanese Experiment Module - Exposed Facility 22

Robotic capabilities 23

Mobile Servicing System 23

Japanese Experiment Module Robotic Manipulator System 24

Access to the External Environment 24

Robotic Interfaces 24

Special Considerations 24

Deployable Small Satellites 25

Table of Contents
4

Software and Avionics, ISS Command and Data Handling 25

Health and Status Data 25

Broadcast Ancillary Data 25

Unique Ancillary Data 26

ISS Data Interfaces 26

Data Downlink Availability Downlink and Storage 27

Command/Data Latency 28

Payload Software and Displays 29

Telescience Resource Kit – Payload Operations Interface 29

ISS Characteristics 30

Internal Atmosphere 30

Orbit Characteristics 30

Guidance, Navigation and Control Characteristics 31

Microgravity Environment 32

External Contamination 32

Transportation to ISS 33

ISS Cargo Vehicles 33

Payload Integration Process 34

Application to ISS Technology Demonstration 34

Mapping to Identified Need 35

ISS Provided Assistance 35

Assigned Points of Contact 35

Hardware/Software Provided to Payload Developers 36

ISS Services 37

Hardware and Ground Handling Capabilities 38

Testing Capabilities 38

Top Level Payload Integration Milestones and Deliverables 39

Acronyms 43

Table of Contents continued...
5

The mission of the International Space Station (ISS) Program is to advance science 

and technology research, expand human knowledge, inspire and educate the 

next generation, foster the commercial development of space and demonstrate 

capabilities to enable future exploration missions beyond low Earth orbit (LEO).

To execute this mission — specifically, technology advancements — the ISS 

Program is utilizing the space station as a test bed to demonstrate operational 

techniques and capabilities, and demonstrate technologies and advanced systems 

that benefit space science capabilities and human and robotic exploration beyond 

LEO. Working with the international exploration community, the Global 

Exploration Roadmap was developed to provide an internationally, phased approach 

defining capabilities that will be needed for future exploration. Demonstration of 

these advanced capabilities is a primary objective of the ISS Program mission.

This booklet has been developed to provide prospective technology and advanced 

system developers the information that will aid in the formulation of demonstration 

concepts and as an introduction of station capabilities, characteristics and processes. 

The following pages begin by describing the technology development areas of 

greatest interest to the National Aeronautics and Space Administration (NASA) 

followed by descriptions of ISS interfaces and the manifesting process. Finally, 

points of contact are identified before a description of the processes and capabilities 

that are available to selected and manifested payloads.

Preface

Top right: This panorama is a mosaic of images taken by the Mast Camera (Mastcam) on the NASA Mars rover Curiosity while 

the rover was working at a site called “Rocknest” in October and November 2012. Image Credit: NASA/JPL-Caltech/Malin Space 

Science Systems. Bottom Right: This picture of the Earth and Moon in a single frame, the first of its kind ever taken by a spacecraft, was recorded September 18, 1977, by NASA’s Voyager 1 when it was 11.66 million km (7.25 million miles) from Earth.
6

Overview

The ISS Program provides an infrastructure capable of demonstrating prototypes 

and systems that may advance spaceflight technology readiness. The space station, 

the in-orbit crew, the launch and return vehicles, and the operation control centers 

are all supporting the demonstration of advanced systems and operational concepts 

that will be needed for future exploration missions.

The ISS is the only long-duration platform available in the relevant space 

environment with an integrated space systems architecture that can be used to 

demonstrate advanced technologies and operations concepts. Working in close 

cooperation with the exploration community, the ISS Program is enabling 

technology and systems investigations in support of future exploration endeavors. 

NASA has identified 11 exploration technology areas of interest that ISS is capable 

of supporting. These 11 technical areas are described in the following pages. 

Details of exploration and technology needs are documented in NASA Technical 

Paper TM-2012-217670.

The ISS Program aims to demonstrate these and other technologies on the space 

station where they can be evaluated without significant risk to crew or vehicle in 

order to accelerate development and reduce risks for future exploration missions. 

Project developers who have formulated a technology demonstration project and 

are ready to contact the ISS Program should reference the “Application to ISS 

Technology Demonstration” section starting on page 32 of this book.

ISS Technology 

Demonstration Program
7

Technology Readiness Level Advancement

The ISS Laboratory is available to conduct research and/or engineering 

investigations to advance Technology Readiness Levels (TRL) by demonstrating 

system performance in the unique space environment offered by station or its 

visiting vehicles. Additionally, station-based demonstrations support proofing 

the concepts of operations, training, crew interfaces and logistics as well as 

maintainability and reliability. Performing these demonstrations on the space 

station provides an opportunity to obtain operational knowledge in a relevant 

environment without the added costs and risk associated with integrating a new 

technology or advanced system into an operational system.

In-Space Propulsion

Systems for in-space propulsion can benefit from in-space demonstration by gaining 

operational run time in the microgravity, vacuum and thermal environments 

of space while gaining experience in fuel flow management and performance. 

Demonstrations providing integrated system operations or subsystem investigations 

demonstrating supporting elements of a system can be performed. 

If scaled to not adversely impact ISS, in-space propulsion systems can be demonstrated 

on the space station, potentially on visiting vehicles or deployed free fliers.

Space Power and Energy

Solar array and solar cell demonstrations 

in space are important because they allow 

the demonstration of performance absent 

the solar filtering and diffusion caused 

by the atmosphere. At the same time, 

they provide the appropriate thermal and 

dynamic loading conditions that will be 

seen in an implemented system. 

Fuel cells and other systems that 

operate with fluids, especially 

two-phased fluids, benefit from 

demonstrating performance in the 

microgravity environment.
8

Robotics, Tele-Robotics and Autonomous Systems

Robotic and tele-robotic systems operating in and 

around a spacecraft, with or without crew-robot 

interaction, will demonstrate performance and 

operational concepts of robotic systems in the 

manned and unmanned spacecraft environments. 

Tele-robotic demonstrations on ISS show the ability 

to perform and develop concepts of operation for an 

in-space crew to perform remote operations. 

Communication and Navigation

Navigation systems can be demonstrated on ISS with 

system performance compared to the spacecraft’s 

known position. Advanced or automated rendezvous 

and docking systems can be demonstrated with ISS 

and visiting vehicles or dedicated free fliers. 

Communication systems can utilize the space station 

infrastructure to demonstrate delay tolerance and 

the elimination of space communication architecture 

bottlenecks, thus increasing throughput of the 

integrated systems.

Life Support and Habitation Systems

The job of maintaining a habitable environment for 

the crew over the duration of a human spaceflight 

mission is performed by Environmental Control & 

Life Support Systems (ECLSS). Living in space for 

long durations with little or no resupply from Earth 

is a fundamental capability that is being matured 

through day-to-day operations on the only platform 

capable of that task – ISS. For long-duration 

exploration beyond LEO, spacecraft systems must 

provide a stable, self-contained micro-environment 

around the clock by revitalizing the air, collecting 
9

and processing wastewater streams to recover and provide safe drinking and hygiene 

water for the crew, and managing solid wastes (metabolic and trash). ISS presents 

the opportunity to perform limited upgrades to the current systems to increase 

operational availability and reduce system mass, consumables and power needs 

beyond the current capability. At the same time, ISS provides a directly relevant 

operating environment to perform demonstrations of technologies and prototype 

systems to reach capabilities necessary to enable an exploration-class mission. 

Operational demonstrations aboard ISS will ensure that the ECLSS needed for 

exploration beyond LEO has been verified properly to keep the crew alive and safe 

for more than a year away from Earth.

Exploration Destination Systems

Human Exploration Systems are exploration-specific capabilities that do not 

clearly fall into other technology categories. As such, the technologies in this area 

are diverse and expansive. Many of these technologies are related to extravehicular 

activity (EVA), or spacewalks, and general habitation. These systems can benefit 

from the microgravity environment and utilization within the operation of the 

station-habitable environment.

Science Instruments

As advances in scientific technology enable more capable science and sensor 

systems, prototype systems can be demonstrated on ISS to evaluate performance 

in the space environment and in relevant conditions. On ISS, these systems can 

be evaluated by the in-orbit crew or within the existing station commanding and 

data infrastructure, such that confidence can be gained and risks reduced in the 

system before it is used on a dedicated science mission. Additionally, science system 

demonstrations can be used to evaluate and assist in down selecting systems that are 

under consideration. 

Entry, Descent and Landing Systems

ISS visiting vehicles re-enter Earth’s atmosphere following station-docked missions. 

There are several methods to deploy small satellites from the space station that 

will re-enter the atmosphere. These opportunities can be used to demonstrate 

capabilities and techniques and increase knowledge of atmospheric re-entry.
10

Materials, Structures and Manufacturing

Long-duration exploration missions will experience 

the ultraviolet, thermal and energized particle 

radiation environment of space requiring the use 

of materials on spacecraft that can survive these 

harsh conditions. ISS offers long-duration space 

exposure in which materials can be evaluated. 

Space station return vehicles can also be utilized to 

expose sample materials being considered for the 

return environment.

Thermal Management Systems

Besides re-entry thermal protection, spacecraft thermal technologies are needed 

to maintain cryogenic systems and thermal control of a spacecraft’s systems and 

internal environment. 

Cryogenic systems contain fluids in two-phased regimes. Thermal insulation and 

recapture, fluid flow, and level measurement of these fluids are uniquely affected by 

the space and microgravity environment. Demonstrating system capabilities in the 

relevant environment of ISS would demonstrate needed exploration capabilities.

Heat rejection technology should operate efficiently and reliably across a wide range 

of thermal environments. Future spacecraft will benefit from advanced technologies 

and systems that can efficiently maintain heat loads in both the hot and cold 

environments of space.

Operational Processes and Procedures

ISS is continuously managed and operated from several distributed control 

centers around the globe. The processes, procedures and software tools used in 

station operations are continuously evolving and maturing with future missions 

in mind. Where possible, operational concepts (processes, software tools, training 

and procedures) are advancing toward the type of operations expected from an 

exploration mission, with delayed communications, increased in-space crew 

autonomy and reduced routine ground-to-space interactions.
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ISS provides investigators with a variety of accommodations and resources. 

Accommodations include: internal, or pressurized habitable volume; external, 

exposure to the space environment; transportation to and from the space station 

and deployable options.

A few of the accommodations more commonly utilized by technology demonstration 

payloads are highlighted here. For a more comprehensive description of the facilities 

and accommodations on ISS, the reader is referred to the International Space 

Station Facilities Book.

Internal

Internal to ISS, the technology and system demonstrations will be exposed to the 

nominal habitable station environment.

Expedite the Processing of Experiments for Space Station (EXPRESS) Rack 

Internal to the space station habitable volume, technology demonstrations can 

be installed in the EXPRESS racks. EXPRESS racks support multi-discipline 

investigations and provide several resources that can be utilized in the technology 

demonstration.

ISS Accommodations

System

Structural

Power

Air Cooling

Thermal Control System 

Water Cooling

Command & Data Handling

Video

Vacuum Exhaust System

Nitrogen

Middeck Locker Locations

Volume: 2 cubic feet

Internal Dimensions: 

20.32 x 17.34 x 9.97 inches

28 Vdc, 0 - 500 W

< 200 Watts

500 Watts (2 positions per rack)

RS422 Analog

Ethernet 5 Vdc Discrete

NTSC/RS170A

1 payload interface per rack

1 payload interface per rack

ISIS Drawer Locations

Volume: 1.26 cubic feet

Internal Dimensions: 

23.25 x 16.62 x 6.0 inches

28 Vdc, 0 - 500 W

< 100 Watts

500 Watts (2 positions per rack)

RS422 Analog

Ethernet 5 Vdc Discrete

NTSC/RS170A

1 payload interface per rack

1 payload interface per rack

Rack-Level Accommodations

8 Mid deck Lockers

2 ISIS Drawers (4 Panel Unit)

2000 Watts 28 Vdc power

1200 Watts

2 positions per rack

RS422 Analog

Ethernet 5 Vdc Discrete

NTSC/RS170A

1 payload interface per rack

1 payload interface per rack

EXPRESS Rack Resources
12

Station to Internal Facility Rack Resources

The resources listed below are available in various rack locations on ISS. 

Features 

4 rear captive fastener

attachments 

Friction hinge 

Dual door locks 

Installation tool

guides on 4 corners 

Weight – 12 lbs 

Middeck Locker International Sub rack Interface

Standard Drawer 

Features 

 4 PU (Panel Unit) 

 Blind Connectors 

 Locking Handles 

 Weight – 27 lbs 

 Rated to at least 37 lbs 

Sub Rack size payload capability with 

standard utilities such as power, data, 

cooling and gases 

EXPRESS Rack 

EXPRESS 8/2 Configuration 

8/2 Payload Configuration 

(8 Middeck Lockers, 

2 Powered ISIS Drawers) 

International

Standard 

Payload Rack 

 Secondary 

Structure & 

Subsystems 
13

Aisle-Deployed Payloads

In some cases, small technology demonstrations can be installed or demonstrated 

outside of racks in a manner that does not interfere with crew passage or operations. 

In these instances, power and data resources can be provided to a payload from an 

EXPRESS Rack.

Internal/External

Japanese Experiment Module (JEM) Airlock

The JEM is unique within ISS in that it has an airlock, which is located on the 

end of the JEM that faces the JEM Exposed Facility (JEM-EF). The airlock 

allows the transfer of payloads between the internal pressurized cabin and space. 

The JEM airlock can accommodate a payload up to 300 kg in mass that fits within 

the dimensions of the airlock. The general dimensions and form of the airlock 

volume are shown on the next page and are 32 inches in width. 

A slide table allows the JEM-EF robotic arm to access the payload. The JEM-EF 

POWER 3, 6 or 12kw, 114.5-126 voltage, direct current (VDC)

DATA

GASES

COOLING LOOPS

VACUUM

Low Rate

High Rate

Ethernet

Video

Nitrogen

Argon, carbon dioxide, helium

Moderate Temperature

Flow Rate

Low Temperature

Flow Rate

Venting

Vacuum Resource

MIL-STD-1553 bus 1 Mbps

100 Mbps

10 Mbps

NTSC

Flow = 0.1 kg/min minimum;

517-827 kPa nominal; 

1379 kPa, maximum

517-768 kPa nominal; 

1379 kPa, maximum

16.1oC – 18.3oC

0 – 45.36 kg/h

3.3oC – 5.6oC

233 kg/h

10-3 torr in less than 2h for single payload 

of 100 L

10-3 torr (to maintain vacuum only, not for 

venting)
14

arm moves the payload between the JEM airlock and external ISS locations. JEM 

airlock usage is negotiated on an as-needed basis.

External

ISS provides a variety of external sites and services to conduct payload 

investigations.
ISS-Tech Demo Book-foldout 6-25-13.indd 1 6/26/13 
SSRMS 

Columbus 

JEM PM 

ELM-PS

JEM-EF

ELC 3 

(ULF6) 

P3 Upper 

Outboard 

[U1]

ELC 1 

 (ULF3) 

P3 Lower

Inboard 

[U2]

AMS 

(ULF6) 

S3 Upper 

Inboard 

[P2]

ELC 4 

(ULF5)

S3 Lower

Inboard 

[P4]

ESP 2 

(LF1)

Airlock

ESP 3 

(ULF3) 

S3 Lower

Outboard 

[P3]

ELC 2 

(ULF3) 

S3 Upper 

Outboard 

[P1]

SPDM MCAS

ESP 1 

(5A.1) 

Lab

EIBA OSE 

Columbus 

Payload Sites 

(1E) 

[P#] = PAS 

[U#] = UCCAS 

ISS Attach Sites

20

ISS-Tech Demo Book-foldout 6-25-13.indd 2 6/26/13 
21

EXPRESS Logistics Carrier (ELC)

Technology demonstrations performed externally on ISS can be attached to one of 

the ELCs. The ELC locations offer viewing options ranging from nadir to zenith 

and points in between. Payload demonstrations attaching to the ELC will require 

the use of a Flight Releasable Attachment Mechanism (FRAM). The FRAM 

provides mechanical, electrical, thermal, data, EVA, and robotic interfaces to ISS.

The medium rate data interface will be updated at each ELC location to 100 Mbps 

two-way wireless LAN. 

Columbus Exposed Facility (EF)

Located on the starboard side of space station, the European Space Agency (ESA)

Columbus module also provides an external facility to accommodate external 

technology demonstrators. Similar to the FRAMs, the technology demonstration 

payload will be provided a Columbus External Payload Adapter (CEPA) to interface 

to the space station services.

ELC Single Adapter 

Resources Mass capacity

Volume

Power

Thermal

Low-rate data

Medium-rate data

Sites available per ELC

Total ELC sites available 

227 kg (500 lb)

1 m3

750 W, 113 – 126 Vdc;

500 W at 28Vdc per adapter

Active heating, passive cooling

1 Mbps (MIL-STD-1553)

6 Mbps (shared)

2 Sites

8 Sites

ELC External Research Accommodations
22

JEM-EF

On the port side of ISS, the JEM provides accommodations for attaching external 

payloads. The JEM-EF is a multipurpose experiment platform where various 

investigations/demonstrations can be performed. The JEM-EF has 12 attachment 

ports for external payload and can accommodate up to ten payloads simultaneously. 

The attachment port on the JEM-EF provides mechanical, thermal and electrical 

interfaces to the attached payloads. This interface mechanism is called Experimental 

Exchange Unit (EEU).

Location

SOZ

SOX

SDX

SDN

Viewing

Zenith

Ram

Ram

Nadir

Payload Size

226kg +CEPA

Power

1.25 kW at 120VDC

2.5 kW max

Data

1553 -1 Mbs

ethernet - up to 10 Mbs

Columbus EF Resources

JEM EF Resources Mass Capacity

Volume

Power

Thermal

Low-rate data

High-rate data

Sites available to NASA

550 kg (1150 lb) at standard site

2250 kg (5550 lb) at large site

1.5 m3

3 – 6 kW, 113 – 126 Vdc;

3 – 6 kW cooling

1 Mbps (MIL-STD-1553)

43 Mbps (shared)

5 Sites

JEM External Resources
23

Robotic Capabilities

EVAs (spacewalks) at ISS are reserved to address critical maintenance activities. 

With limited spacewalk opportunities, external technology demonstration 

payloads must be robotically manipulated and installed. Currently, there are two 

robotic manipulator systems aboard ISS. These robotic systems were responsible 

for much of the construction of the space station and are now available for 

payload utilization. 

Mobile Servicing System (MSS)

The MSS is part of the Canadian Space Agency’s contribution to ISS. It consists 

of the Space Station Remote Manipulator System, the Special Purpose Dexterous 

Manipulator, and the Mobile Base System. These, along with two robotics 

workstations, to operate the robotic systems from inside the space station, and the 

Mobile Transporter, which is used to transfer hardware along the length of the truss, 

are now assisting with payload utilization. 
24

JEM Robotic Manipulator System (RMS)

The JAXA-provided RMS resides on the JEM-EF. This manipulator can be used to 

remove payloads from the JEM airlock for placement on the EF and can also be used 

with ISS small satellite deploying systems to launch deployable payloads.

Access to the External Environment

Payloads can gain access to the external environment in one of two ways. For large 

payloads that are destined for one of the payload accommodation sites, they 

can be launched to ISS inside the SpaceX Dragon Trunk. Once the Dragon has 

been captured and berthed to the space station, the MSS can be used to remove 

the payload and install it at its destination. Smaller payloads can be launched to 

ISS in the pressurized environment in one of the many launch vehicles and then 

transferred to the space environment through JAXA’s JEM airlock. 

Robotic Interfaces

FRAMs and CEPAs are provided to technology payload developers as Government 

Furnished Equipment. Robotic interfaces are pre-integrated with the FRAMs 

and CEPAs.

Special Considerations

Special consideration should be given to externally-attached demonstration 

payloads in the following areas:

Contact Loads - Payloads that are maneuvered with a robotic manipulator are 

generally moved into and out of areas of tight clearance with station hardware. 

While every effort is made to prevent collision, there are some unpredictable failure 

cases where contact may occur. Ideally, payloads should be designed to withstand 

the energy imparted from this inadvertent contact.

Thermal Environment - In an effort to preserve as much in-orbit crew time 

as possible, a majority of in-orbit robotic operations are performed by ground 

controllers from the Mission Control Center (MCC). Applied constraints on 

the ground-controlled robotic motion can result in a long-duration transit to the 

payload’s destination. Given the thermal extremes that can be experienced during 

this timeframe, a payload developer should consider this when designing a payload’s 

thermal control system.
25

Deployable Small Satellites

ISS has limited capability to deploy small satellites from the space station for free 

flight and ultimate re-entry to Earth’s atmosphere.

Software and Avionics, ISS Command and Data Handling

Health and Status Data

All payloads are required to generate health and status data and transmit it to the 

ground. Health and status data includes all of the parameters needed by Payload 

Operations on the ground to insure that the payload is operating normally and 

correctly responding to commands.

Broadcast Ancillary Data (BAD)

MIL-STD-1553 System distributes ISS BAD to all payloads Remote Terminals 

(RTs). BAD data contains most of ISS vehicle information that experiments need 

like station location, position and pointing vector information. In addition, the ISS 

BAD data contains information about the current pressure, temperature and other 

environmental information data about the space station modules where payloads 

are located. If there is data a payload needs that is available and not currently in 

BAD, it is possible to have it added to BAD if the request is made early enough. 

J-SODD

CYCLOPS

Space X

Size, Approximate

mm (Inches)

1U - 100 x 100 x 113.5 mm

 (3.9 x 3.9 x 4.7 inches)

2U - 100 x 100 x 227.0 mm

 (3.9 x 3.9 x 8.9 inches)

3U - 100 x 100 x 340.5 mm

 (3.9 x 3.9 x 13.4 inches)

1117.6 x 762 x 279.4-533.4 

mm (44L x 30W x 11-21H 

inches)

1U - 100 x 100 x 100 mm

 (3.9 x 3.9 x 3.9 inches)

2U - 100 x 100 x 200 mm

 (3.9 x 3.9 x 6.8 inches)

3U - 100 x 100 x 300 mm

 (3.9 x 3.9 x 10.7 inches)

Mass (Max, of Deployed 

satellite)

1.33 Kg/1U

100 kg

1.33 kg/1U

Location of Deployment

Deployed from ISS (JEM EF)

Currently in-orbit

Deployed from ISS (JEM EF)

In-orbit post SpX3 launch

Deployed from Space X prior to 

ISS docking

Available post SpX3
26

Unique Ancillary Data

Data available from within the Payload Multiplexer De-Multiplexer (PL MDM) 

that is not present in BAD can be transmitted to the payload via the definition of a 

unique ancillary data service. When initialized in the PL MDM, data is transmitted 

to the payload on the 1553 bus. 

ISS Data Interfaces

Table Notes: (1) All station data links are shared resources. The data rate listed is the maximum data rate the link can support. 

(2) Because of the high demand for video downlink and high bandwidth use, it is recommended that the experiments encode 

and downlink video via MRDL when possible.

Typical Utilization of ISS Downlink Shared by all Payload Users:

1. 37.5 Mbps of video (3 lines of video at 12.5 Mbps each)

2. 8 Mbps of MRDL data (Science return)

3. 5 Mbps for payload still imagery downlink

4. 20 Mbps utilized for payload data recorded over Loss of Signal (LOS)

Data Interface

Low Rate Data Link

(LRDL)

Medium Rate Data Link

(MRDL)

High Rate Data Link

(HRDL)

Video (2)

Wireless Data Link

Format

MIL-STD-1553

Ethernet 802.3

TAXI Fiber-optic

NTSC

WiFi Ethernet 802.11b/g

Data Rate (1)

12kbps

10/100Mbps

100Mbps

12.5Mbps

100Mbps

Notes

Nominally used for payload commanding 

and to gather health and status. Limited 

telemetry downlink is also available. 

Ethernet input and output (downlink) is available at most internal locations. Downlink is 

via UDP is available at most external sites. 

HRDL input and output is available at most 

internal sites. HRDL is not available at most 

external sites.

Only available at internal International 

Standard Payload Rack ISPR sites. 

Available to internal and external sites that 

are within range of the access point.

ISS Payload Data Links
27

ISS Command and Data Handling C&DH Interfaces to 

the Communications and Tracking System

Data Downlink Availability Downlink and Storage

Tracking and Data Relay Satellite System (TDRSS) S-Band and Ku-Band coverage 

varies based on ISS attitude, location and beta angle. Typically, coverage ranges 

from 70 to 85 percent. Payloads should plan to internally store and retain any 

data essential for the success of the experiment until it can be verified that the data 

has been transmitted to the principle investigator. Downlinked data is stored by 

payload operations and can be transmitted to the payload user if they are unable 

to receive the data when it is downlinked. During periods of LOS between 

station and TDRSS, the ISS Integrated Communications Unit (ICU) (1.6 Tbits 

total storage capability) nominally records payload data that would have been 

transmitted during that LOS. The ICU will routinely store all low- to medium-rate 

payload data during TDRSS communication outage periods, and some or most of 

the high-rate payload data. This depends on how much data is being downlinked 

and how much of the data can be downlinked when station has Acquisition of 

Signal with TDRSS. 

C&DH

S-band Uplinked Commands/

Data, C&T System Status Data/Audio

Data/Video

Downlink

Video

(4 channels)

Uplink/Downlink

Audio

S-band Commands/

Downlink System Status

Audio System Status

Ku-band System Status

Ku-band Commands,

PLSS Status, Ancillary,

Payload Data

Video System Status

Audio System Commands

Video System Commands

C&T

S-band

C&T TDRSS

Audio

C&T

Ku-band

C&T

Video
28

Command/Data Latency

During periods of TDRSS coverage, the following command uplink and data 

downlink latencies can be achieved, if automatic enabling of payload commanding 

during Ku-band coverage has been worked out ahead of time with NASA Marshall 

Space Flight Center Payload Operations Integration Facility:

1. Data Downlink Latency, station payload-to-payload developer remote site: 

5 seconds

2. Command Uplink Latency, payload developer remote site to station payload: 

10 seconds (with payload command confirmation – up to 15 seconds round trip).

Commands and data sent to ISS via S-Band is encrypted at MCC – Houston prior 

to transmission for security reasons. Station does not offer any encryption data that 

is downlinked via Ku-Band. Payload data that must be protected as crew health or 

medically sensitive data is and must be properly protected by the payload prior to it 

being downlinked.

TDRSS

Commands, Uplinks,

Voice

Vehicle Telemetry,

Voice, Video

Payload/Ku-band &

Vehicle Telemetry

Commands, Uplinks

US Payload Commands, Uplinks

Internet Payload/Ku-band & Anc llary Telemetry

Planning Products, Voice, Ops Mgmt

MCCH to

International

Partner

Services

Planning Products, Voice, Ops Mgmt, Other

Mission

Control Center

Houston

International

Partner

Fac lities

NASA

Telescience

Support

Centers

Payload

User Sites

TReK

Payload Ops

Control Center

Huntsville

Russia

Europe

Japan

Italy

Canada

GRC

ARC

JSC

MSFC

White Sands Complex, New Mexico

ISS

Data Security and Encryption
29

Payload Software and Displays

A unique payload software Interface Control Document (ICD) is developed for 

each payload to document the software and data interfaces. Payloads are required 

to contain and control all of their hazards internally and are not permitted to use 

any station C&DH interface or data as a required control of a hazard. Software 

and firmware used in support of an experiment on ISS must be configuration and 

quality controlled. Software that will need to be uplinked to ISS during the mission 

must be virus scanned and delivered to NASA prior to being uplinked. ISS uses a 

single laptop on orbit; currently, it is the IBM T61p. Displays that are to be used 

by the crew in-orbit in support of an experiment must be delivered to NASA well 

in advance of being used. Delivery cycle requirement are established to a standard 

template based on the flight increment the payload is to be flown, installed and 

operated. Payload displays are reviewed by the crew for usability and in support of 

payload training long before the start of the increment.

Telescience Resource Kit – Payload Operations Interface

The Telescience Resource Kit (TREK) is a suite of PC-based software applications 

provided to payload developers by the ISS Program that is used by scientists and 

engineers to monitor and control payloads aboard the space station. 

The PC running the TReK software can be located anywhere in the world. 

This provides a way for scientists and engineers to monitor and control experiments 

located in space from their offices and laboratories at home.

TREK can be used to receive payload data from ISS, distributed by the Payload 

Operations and Integration Center and to perform local data functions such 

as processing the data, storing it in local files and forwarding it to other computer 

systems. 

Users can extend TREK capabilities by using the TREK Application Programming 

Interface together with commercial software products to utilize local telemetry and 

command functions.
30

Internal Atmosphere

The nominal station atmosphere is shown in the table below:

Orbit Characteristics

Over the course of 72 hours and terrestrial weather conditions permitting, all 

geographic locations between 51.6 north and south latitude can be observed. 

ISS provides coverage of 85 percent of the Earth’s surface and 95 percent of the 

world’s populated landmass every one to three days.

The station altitude generally varies with the solar cycle, with the altitude 

maintained higher during solar maximum. Eccentricity of the station’s orbit is 

maintained at <0.003. In support of visiting vehicles, the altitude is adjusted to 

accommodate the visiting vehicles’ performance parameters. In general, the space 

station altitude will remain within 395-417 km (245-259 miles).

ISS Characteristics

Atmospheric Conditions on ISS 

Pressure

Dew point

Carbon dioxide partial pressure

Oxygen partial pressure

Cabin air temperature

Nominal Value

14.7 PSI

4.4 to 15.6°C (40 to 60°F)

5.3 mm Hg

Peak exposure 7.6 mm Hg 

3.1 PSI ppO2

17 to 28°C (63 to 82°F)
31

Guidance, Navigation and Control Characteristics

ISS Attitude Torque Equilibrium Attitude (TEA) & Wobble Oscillation 

Description – for stage configurations in the foreseeable future (i.e., no orbiter or 

orbiter-sized vehicles docked on the space station), the predicted TEA ranges are: 

Roll: -1.0~+3.0 deg.

Pitch: -7.0~+2.0 deg. 

Yaw: -15~+15 deg.

ISS coverage in 24 hrs for a 70°-swath optical payload. (Courtesy of ESA)

Performance Descriptions

Non-Micro-Gravity (Assembly Stages) Non-Propulsive (Momentum 

Manager) Attitude Control Performance Requirement 

Micro-Gravity (Assembly Complete) Non-Propulsive (Momentum 

Manager) Attitude Control Performance Requirement

Typical Steady-State Performance of Minimum CMG momentum 

oscillation Momentum Manager Contro ler 

Typical Steady-State Performance of Minimum Att tude oscillation 

Momentum Manager Controller 

Typical Steady-State Performance of Minimum CMG momentum 

& Att tude oscillation Blended Momentum Manager Controller 

Peak to Peak Attitude

Oscillations Per Orbit

Peak Attitude Variation from Steady 

State Orbit Average Attitude 

Roll (X)

(deg)

10.0

7.0

1.6

1.6

1.6

Pitch (Y)

(deg)

10.0

7.0

1.6

0.4

0.7

Yaw (Z)

(deg)

10.0

7.0

2.0

0.2

1.2

Roll (X)

(deg)

+/- 5 

+/- 3.5 

+/- 0.8 

+/- 0.8

+/- 0.8

Pitch (Y)

(deg)

+/- 5 

+/- 3.5 

+/- 0.8 

+/- 0.2

+/- 0.35

Yaw (Z)

(deg)

+/- 5 

+/- 3.5 

+/- 1 

+/- 0.1

+/- 0.6
32

Microgravity Environment

The following illustration indicates typical observed microgravity characteristics. 

External Contamination

ISS provides an exceptionally clean environment to external payloads and science assets.

External contamination control requirements limit contaminant deposition to 

130Å/year on external payloads and station sensitive surfaces.

Specified levels are lower than any previous space station (Mir, Skylab, Salyut) by 

several orders of magnitude. Measurements of contaminant deposition on ISS-returned 

hardware have demonstrated that requirements are met at station payload sites.

10-2 10-1 100 101 10-1

100

101

102

Freq

Microg RMS

SDMS S3 Max 1/3 Octave Band - GMT 076, 085, and 086

Experiment

MISSE 2

Node 1 nadir 

window cover

Side

ram

wake

nadir

Requirement (130Å/year)

520 Å (4 years)

520 Å (4 years)

390 Å (3 years)

Measured

50 Å

500 Å

50 Å

Analysis concluded peak ELC rotations on the order of 0.03 degrees per axis (in the quiescent mode).
33

Transportation to ISS

ISS Cargo Vehicles

Several transport vehicles are available to launch payloads to ISS. When a 

technology demonstrator becomes a station payload, the ISS Program manifests 

the payload on the appropriate vehicle. Payload developers do not manifest directly 

with the launch provider for transport to ISS. Currently, only the SpaceX vehicle is 

capable of transporting external FRAM or CEPA payloads to ISS. 

Payload Allowable Up-Mass & Volume Summary Table

ATV (ESA) Cargo Capacity 5,500 kg Soyuz HTV (JAXA) Cargo Capacity 5,500 kg

Cygnus (Orbital Sciences Corp)

2,000 kg

Dragon (SpaceX)

Cargo Capacity 3,100 kg ascent
34

This section describes activities and information to assist prospective payload 

developers in formulating work plans, working with NASA to assess manifest 

options and ensuring a successful mission.

Application to ISS Technology Demonstration

The first points of contact for investigations from other government agencies and 

commercially-funded demonstrations are the NASA National Lab Office and their 

agent, the Center for the Advancement of Science in Space (CASIS). Both work 

closely with the ISS Technology Demonstration Office. 

All other organizations proposing to perform a technology demonstration on ISS 

should contact the ISS Technology Demonstration Office. Contact information 

and additional station information can be found at: http://www.nasa.gov/mission_

pages/station/research/index.html 

Those proposing to perform a technology demonstration on ISS are encouraged to 

use the information in this booklet to develop project goals, concept of operations 

and integration needs such as the resources or utilities that will be required from the 

ISS Program.

When contacting the ISS Technology Demonstration Office, please provide the 

following information as applicable to assist in evaluation.

1. Proposed payload name

2. Lead point of contact information

3. What capabilities are to be demonstrated 

(project demonstration or scientific goals)?

4. How do these capabilities map to identified exploration needs 

(not required, but please provide if applicable)?

5. Who are the sponsoring organizations?

6. Brief description of the demonstration: (Is it internal or external, what resources 

are required like power, data, etc.) What is the expected size/mass, and is there an 

expected time duration required in orbit?

7. When is it anticipated that the demonstration can be ready for turnover to the 

ISS Program for launch to ISS?

Payload Integration Process
35

Once the initial contact is made, there may be further interactions to exchange 

information unique to the project. The ISS Technology Demonstration Office 

will notify the prospective payload developer of available station accommodations 

and launch opportunities and will make the appropriate manifesting and ISS 

integration approvals.

Mapping to Identified Need

The ISS Program intends to advance the state-of-the-art for as many technical areas 

as possible. It is desired that all advanced capabilities that can be demonstrated on 

the space station are identified. Proposers are encouraged to bring these advanced 

capability options to the ISS Technology Demonstration Office. 

Though not a requirement, it is helpful to know when a technology demonstration 

can be linked directly to advancing identified exploration capability needs. 

When possible and appropriate, the technology payload developer should identify 

which technology area, discussed previously in this book, may be advanced by 

successful demonstration of the payload.

ISS Provided Assistance

Once the prospective payload developer has been sponsored by the ISS Technology 

Demonstration Office and identified as an ISS technology demonstration payload, 

the program will assign personnel to assist in completing the activities required to 

successfully integrate and perform the investigation on the space station.

Assigned Points of Contact

For each payload destined to be performed on the space station, there are several 

points of contact in the ISS Program identified to work directly with the payload 

developer. These points of contact will be identified after the payload has been 

sponsored by the ISS Technology Demonstration Office.

Technology Demonstration Lead: The Technology Demonstration lead is 

a member of the ISS Technology Demonstration Office. The technology 

demonstration lead will work with the payload developer to define the 

demonstration objectives and support the payload developer to ensure those 

technology demonstration objectives are met.
36

Payload Integration Manager (PIM): Each ISS payload is assigned a PIM 

who will be their main point of contact for all activities and interfaces to the 

ISS Program. The PIM will develop an integration schedule, identifying all 

the activities and products that will occur and be needed between the payload 

developer and the ISS Program. The PIM will communicate between all 

organizations and coordinate all the activities required for nominal integration 

of payloads into ISS.

Research Integration Manager (RIM): Each payload will be assigned a RIM. 

The RIM will assist with issues or unique needs that the payload developer may 

have from the ISS Program. 

Payload Operations Lead: Each payload will be assigned a payload operations 

lead. This individual will be the interface to operations and will assist in 

developing in-orbit operational procedures, regulations, training and all other 

operational activities.

Safety Engineer (SE): The SE serves as the NASA Safety and Mission Assurance 

representative for station experiments/payloads. The SE reviews payload safety 

data packages (generated by the payload developer) to identify potential areas 

of noncompliance and technical safety issues. The SE supports and advises 

the payload developer and the chair of the Payload Safety Review Panel in 

the review and acceptance of payload hazard reports. The SE also coordinates 

technical interchange meetings and working group meetings to discuss and 

resolve technical issues between various technical representatives and payload 

providers. The SE supports the payload developers through the completion of 

safety review activities and assurance of flight readiness.

For the most up to date information on specific points-of-contact, please refer to 

http://www.nasa.gov/mission_pages/station/research/ops/research_information.html.

Hardware/Software Provided to Payload Developers

There are some standard hardware items that can be provided if available and 

requested by the payload developer. In most cases, the hardware items listed here 

are provided free of charge to the payload developer.
37

Internal payloads: 

• Middeck Lockers – Lockers that will be installed in an EXPRESS rack can be 

provided to install the demonstration unique hardware. 

External payloads: 

• FRAMs or CEPAs – (depending on if the payload is destined for the ELC 

or Columbus EF respectively) A FRAM or CEPA is provided to attach the 

demonstration-unique hardware. The FRAMs and CEPAs provide interfaces 

to the launch vehicles and external station payload locations.

All payloads: 

• TREK workstation – The TREK is a software suite required to interface 

to the ISS Payload Operations Center. All data and commanding from the 

payload will be routed through the TREK workstation. The user will need 

to add payload-unique software to read and manipulate the payload-unique 

commands and data. However, all interfaces with station operations are 

provided. The TREK system can be installed and operations performed at the 

user’s desired location.

Payload developers will coordinate requests for hardware and services through their 

assigned PIM.

ISS Services

The ISS Program will provide the following services to assist with demonstration of 

the payload. These capabilities are generally provided free of charge to the payload 

developer.

• Launch to the space station

• Installation on station at identified site

• In-orbit utilities and operations support including crew or robotics time 

(if needed)

• Data handling and delivery (to the TREK)

• End-of-life removal and disposal
38

Hardware and Ground Handling Capabilities

Mostly utilized by larger external payloads, 

the ISS program has ground handling and ground 

support equipment that can be made available to 

payload developers. Lifting equipment, mobile 

mounting plates and other handling equipment 

may be utilized on an as-available basis, so payload 

developers do not need to design and build all 

this equipment. 

Use of this hardware can be requested and 

coordinated with the ISS Program through the 

PIM assigned to the payload. 

Testing Capabilities

The payload developer is responsible for scheduling, resourcing and performing all 

tests of their payload system. When ISS test capabilities are requested, approval and 

scheduling the use of these assets can be negotiated with the ISS Program via the 

PIM assigned to the payload.

To assist in the software development of the payload, the ISS Program can provide 

small test equipment that emulates the space station side of the software interface. 

These systems are portable and can be used at the payload developer location. 

The systems are the Suitcase Test Environment for Payloads that simulates the 

space station facility interfaces; the EXPRESS Suitcase Simulator that simulates 

the EXPRESS/Window Observational Research Facility (WORF) Rack interfaces 

and the EXPRESS Logistics Carrier Suitcase Simulator that simulates the 

ELC interfaces.

The Payload Rack Checkout Unit (PRCU) is utilized to test payload experiment 

interfaces to ISS. In this capacity, the PRCU serves as a high-fidelity emulator of 

in-orbit station interfaces and allows experiment developers to ensure that their 

payload will interact properly once connected in-orbit. PRCUs provide interfaces 

to the standard station payload interfaces (120VDC, C&DH, video, Thermal, 

N2 supply and vacuum access). The PRCU is not portable.
39

Tests with the PRCU can be conducted as near end-to-end tests. Data and 

commands are transmitted to the ISS Payload Operations Control Center and 

back to the payload’s TREK work station to confirm data and commanding in the 

integrated system.

The EXPRESS Rack Functional Checkout Unit is utilized to test EXPRESS payload 

interfaces to the EXPRESS Rack. It provides flight-like interfaces for the structural/

mechanical, power, data, thermal, vacuum and GN2 EXPRESS resources. It can be 

used to conduct end-to-end testing with the Payload Operations Control Center. 

It can also be used to test WORF power and data interfaces.

Top Level Payload Integration Milestones and Deliverables

Top level description of the milestones payload developers perform in the 

integration process (PIM schedule):

When a payload is sponsored by the ISS Technology Demonstration Office and 

a PIM is assigned to support the payload, the PIM will assist in developing an 

integrated schedule of activities with the ISS Program and the payload developer. 

Those details will be unique to each payload and each scheduled launch. The details 

cannot be accurately duplicated as a generic schedule and task description.

Programmatic 

Payload 

Research Plan

Approved 12 months

prior to Increment start 

Payload

Developer

Inputs

Post Flight Operations 

(Hardware, Data Return) 

ISS Crew 

Rotation 

Launch 

Real-Time Operations 

(Research) 

Crew Return 

Strategic Tactical Operations 

Launch Launch Launch 

ISS Crew 

Rotation 

Post-Flight 

Increment 

Research Plan 

Hardware Operations 

Products

Payload Tactical Plan

Hardware Development 

Products

COUP 

Up to 4 years 

prior to Launch 

Research Sponsor 

Research Integration Manager / Payload Integration Manager 

Lead Increment Scientist 

Increment Payload Manager 

Research Plan 

Operations Lead 

Stage Stage Stage 
40

However, to assist in early project planning, listed below are many of the top level 

activities in which payload developers will participate. Payload developers can 

expect, at a minimum, to support the following activities:

• Support research planning

– Templates are provided by the ISS Program to assist the payload developer 

in providing the initial inputs (i.e.: mass, dimensions, experiment summary, 

estimates on crew time and power requirements.)

– Payload developers’ efforts include filling out these templates with 

explanations of their system and on-orbit demonstration plan.

• Document hardware and software interface requirements

– Interface Requirement Documents and templates are provided as an initial step 

in the development of a unique station payload ICD.

– An ICD developer is assigned to each payload developer to aide in the generation 

of a unique payload ICD. The payload developer will provide payload specific 

information in these documents representing the system design and interfaces.

• Interface requirements verification 

– Each payload developer will submit verification to show compliance 

to interface requirements (i.e.: power, data, thermal, robotics, launch 

environment, crew handling as defined in the payload unique ICD.)

– Each payload organization can request guidance on the approach to show 

compliance to interface requirements via the PIM and RIM, however, the 

payload developer is responsible for completing verification or approval of 

non-compliances.

– The payload developer is responsible for test labs and equipment. Where 

station-specific test hardware is required, the payload developer can coordinate 

this use with the PIM assigned to the payload. 

• Support station safety reviews for flight and ground activities

– These reviews ensure safe operation of the payload during transport to ISS, 

while at the station and for any pre- or post-flight activities.
41

– Hazards that could be created by the payload system, or through its 

operations, are identified and reviewed in these safety reviews. The hazard 

controls provided by the payload developer to mitigate the identified hazards 

are also coordinated and approved in these reviews.

– Each payload developer will receive safety requirements and process 

documentation. From this data the payload developer will develop the safety 

data packages used in the safety reviews.

– Each payload developer will be assigned a safety engineer who will coordinate 

and guide the payload developer through the safety process.

• Support ground processing operations

• When required for launch vehicle integration or other pre- or post-flight 

operations, the payload developer will support activities to ensure that the 

payload systems are handled as desired.

• Each payload developer is expected to provide CAD, thermal and structural 

models of the payload

– Payload models are used to support multiple station-integrated assessments.

– These models are scheduled, described and documented in the PIM schedule 

and ICDs. Assistance in coordinating the details of these models will be 

provided by the PIM assigned to the payload.

Post Flight Operations 

(Hardware, Data Return) 

ISS Crew 

Rotation 

Launch 

Real Time Operations 

(Research) 

Crew Return 

Strategic Tactical Operations 

Launch Launch Launch 

Post-Flight 

Increment 

Stage Stage Stage 

Programmatic Research Plan 

Payload Hardware Operations Products

Payload Tactical Plan

Hardware Development 

Products

COUP 

Up to 4 years 

prior to Launch 

Tailored 

ISS Crew 

Rotation 

Nominal 

WHO: Po nts of Contact 

WHAT: Requ rements Defin tion 

WHEN: 

WHERE: 

Operat ons Plan 

Launch and On Orb t Requirements 

WHY: Inves igat on Object ves 

Payload Developer Inputs 

• Investiga or Partic pation Real Time

 (e g Console Operat ons) 

• Crew Conferences

• Anomaly Resolution

• Data Collection and Samp e Return

Payload Developer Inputs 

Payload Developer Inputs 

Research Plan

Approved 12 months

prior to Increment start 

• Changes to Basel ned Research P an 

• Tra ning Products and Procedures

• Safety Rev ew Packages

• Hardware Verif cat on Data

• Software Ver fication Data

Payload Developer Inputs 

• Research Summary Updates

• 30 Day Reports 

• Formal Publ cat ons
42

• Participate in operations training 

– This participation ensures successful in-orbit operations. Payload training 

is provided by the ISS Program to the payload developer. This training 

provides guidance on how to operate through the Payload Operations Center, 

communicate with operators, schedule operations time and address offnominal situations.

– Each payload developer will be provided an operations lead to aide in the 

generation of training products as well as other operational activities.

• Provide input and develop operational procedures and flight rules

– Inputs allow payload developers to ensure proper operation of their payload. 

– Payload developers will provide system and concept of operations information 

to support development of procedures and rules. 

– In cases where the crew interacts with the system, the payload developer will 

provide input for the development of the crew procedures.

– Each payload developer will be provided an operations lead to aide in the 

development of these and other operational products.

• Operations

– Payloads on ISS are operated by the payload developer and/or principal 

investigator in coordination with the Payload Operations Control Center. 

– Payload developers operate their payload via the station-provided TREK 

system from any location desired. Payload operators are not required to be 

co-located with any ISS operations control center.
43

BAD Broadcast Ancillary Data

C&DH Command and Data Handling

CEPA Columbus External Payload Adapter

ECLSS Environmental Control & Life Support Systems

EEU Experimental Exchange Unit

ELC EXPRESS Logistics Carrier

ESA European Space Agency

EVA Extravehicular Activity (spacewalk)

EXPRESS Expedite the Processing of Experiments for Space Station Rack

FRAM Flight Releasable Attachment Mechanism

ICD Interface Control Document

ICU Integrated Communications Unit

ISS International Space Station

JEM Japanese Experiment Module

JEM-EF JEM Exposed Facility

LEO Low Earth Orbit

LOS Loss of Signal

MCC Mission Control Center

MSS Mobile Servicing System

NASA National Aeronautics and Space Administration

PIM Payload Integration Manager

PL MDM Payload Multiplexer De-Multiplexer

PRCU Payload Rack Checkout Unit

RIM Research Integration Manager

RMS Robotic Manipulator System

SE Safety Engineer

TDRSS Tracking and Data Relay Satellite System

TEA Attitude Torque Equilibrium Attitude

TREK Telescience Resource Kit

TRL Technology Readiness Levels

WORF Window Observational Research Facility

Acronyms
44

The Complete ISS Researcher’s 

Guide Series

1. Acceleration Environment

2. Cellular Biology

3. Combustion Science in Space

4. Earth Observations

5. Fluid Physics in Space

6. Fruit Fly Research

7. Fundamental Physics

8. Human Research

9. Macromolecular Crystal Growth

10. Microbial Observatory

11. Microgravity Materials Research

12. Plant Science

13. Rodent Research

14. Space Environmental Effects

15. Technology Demonstration

44
45

For more information...

Space Station Science

http://www.nasa.gov/iss-science

Facilities

http://www.nasa.gov/mission_pages/station/research/

facilities_category.html

ISS Interactive Reference Guide:

http://www.nasa.gov/externalflash/ISSRG/index.htm

Researchers

http://www.nasa.gov/mission_pages/station/research/

ops/research_information.html

45
National Aeronautics and Space Administration

Johnson Space Center

http://www.nasa.gov/centers/johnson

www.nasa.gov

NP-2013-06-008-JSC