Kibo HANDBOOK

September 2007

Japan Aerospace Exploration Agency (JAXA)
Human Space Systems and Utilization Program GroupKibo HANDBOOK

Contents
1. Background on Development of Kibo ............................................ 1-1
1.1

Summary ........................................................................................................................... 1-2

1.2

International Space Station (ISS) Program ........................................................................ 1-2

1.2.1
1.3

Outline ......................................................................................................................... 1-2

Background of Kibo Development...................................................................................... 1-4

2. Kibo Elements................................................................................... 2-1
2.1

Kibo Elements.................................................................................................................... 2-2

2.1.1

Pressurized Module (PM) ............................................................................................ 2-3

2.1.2

Experiment Logistics Module - Pressurized Section (ELM-PS) ................................... 2-4

2.1.3

Exposed Facility (EF) .................................................................................................. 2-5

2.1.4

Experiment Logistics Module - Exposed Section (ELM-ES) ........................................ 2-6

2.1.5

JEM Remote Manipulator System (JEMRMS)............................................................. 2-7

2.1.6

Inter-orbit Communication System (ICS)..................................................................... 2-8

3. Kibo Specifications .......................................................................... 3-1
3.1

Specifications of Kibo Components.................................................................................... 3-2

3.2

Kibo Operation Mode ......................................................................................................... 3-4

4. Kibo System Components ............................................................... 4-1
4.1

Pressurized Module (PM) .................................................................................................. 4-2

4.1.1

Brief Summary............................................................................................................. 4-2

4.1.2

Layout ......................................................................................................................... 4-3

4.1.3

System Components of PM......................................................................................... 4-6

4.2

Experiment Logistics Module- Pressurized Section (ELM-PS) ........................................ 4-12

4.2.1

Brief Summary........................................................................................................... 4-12

4.2.2

Layout ....................................................................................................................... 4-13

4.2.3

System Components of ELM-PS............................................................................... 4-14

4.3

Exposed Facility............................................................................................................... 4-17

4.3.1

Brief Summary........................................................................................................... 4-17

4.3.2

Layout ....................................................................................................................... 4-19

4.3.3

System Components of EF........................................................................................ 4-21

4.4

Experiment Logistic Module-Exposed Section (ELM-ES) ................................................ 4-24

4.4.1

Brief summary ........................................................................................................... 4-24

4.4.2

Layout ....................................................................................................................... 4-26iKibo HANDBOOK

4.4.3
4.5

System Components of ELM-ES............................................................................... 4-27

Japanese Experiment Module Remote Manipulator System (JEMRMS) ......................... 4-29

4.5.1

Brief Summary........................................................................................................... 4-29

4.5.2

Layout ....................................................................................................................... 4-31

4.5.3

System Components of JEMRMS ............................................................................. 4-32

4.6

Inter orbit Communication System (ICS).......................................................................... 4-34

4.6.1

Brief Summary........................................................................................................... 4-34

4.6.2

Layout ....................................................................................................................... 4-35

4.6.3

System Components of ICS ...................................................................................... 4-36

5. Kibo Operations................................................................................ 5-1
5.1

Launch and Flight Plan ...................................................................................................... 5-2

5.2

Kibo Assembly Sequence .................................................................................................. 5-3

5.2.1

1J/A Flight.................................................................................................................... 5-3

5.2.2

1J Flight....................................................................................................................... 5-6

5.2.3

2J/A Flight.................................................................................................................. 5-10

5.3

Kibo Operations Control................................................................................................... 5-13

5.3.1

Orbital Interface (between the ground to/from Kibo).................................................. 5-17

5.3.2

Ground Interface (between TKSC and NASA Mission Control Centers) ................... 5-18

6. Kibo Utilization ................................................................................. 6-1
6.1

Summary ........................................................................................................................... 6-2

6.2

Environment....................................................................................................................... 6-2

6.2.1

Microgravity ................................................................................................................. 6-2

6.2.2

Line of Sight and field of view from the ISS................................................................. 6-2

6.2.3

Background Atmosphere ............................................................................................. 6-3

6.2.4

Space Radiation .......................................................................................................... 6-4

6.2.5

Thermal Environment .................................................................................................. 6-4

6.2.6

Micrometeoroid and Space Debris .............................................................................. 6-4

6.3

6.3.1

Experiment Payloads for Kibo’s Pressurized Module (PM) ......................................... 6-5

6.3.2

Exposed Facility (EF) Experiment Payloads.............................................................. 6-15

6.4

ii

Experiment Payloads ......................................................................................................... 6-5

Utilization Plan ................................................................................................................. 6-21

6.4.1

Overall Schedule ....................................................................................................... 6-21

6.4.2

Utilization Fields ........................................................................................................ 6-22

6.4.3

Experiment Themes .................................................................................................. 6-23

Kibo HANDBOOK

6.4.4

Utilization Plan........................................................................................................... 6-27

7. H-II Transfer Vehicle (HTV) Overview.............................................. 7-1
7.1

Summary ........................................................................................................................... 7-2

7.1.1
7.2

HTV Components........................................................................................................ 7-3

HTV Operations ................................................................................................................. 7-7

7.2.1

Launch ........................................................................................................................ 7-8

7.2.2

Rendezvous ................................................................................................................ 7-9

7.2.3

Berthing with the ISS (Proximity Operation Phase) ................................................... 7-10

7.2.4

Operations while berthed to the ISS.......................................................................... 7-12

7.2.5

Departure from the ISS and Reentry ......................................................................... 7-14

Appendix Acronyms and Abbreviationsiii

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1. Background on Development of Kibo

1-1

1. Background on Development of Kibo

1.1

Summary

The International Space Station (ISS) is “the first borderless world“ mankind has ever had in history. The
United States of America (US), Japan, Canada, European countries and Russia are participating in this ISS
program. These partners have been collaboratively promoting the construction, assembly, and utilization of theISS. This type of collaboration, which utilizes the state-of-the-art technologies from many different countries
for constructing a single facility, has never been done before. The ISS, in many ways, is truly a symbol ofglobal cooperation and peace, as well as an important research facility to provide a major breakthrough in theworld’s space development endeavors.
The conceptual design of the space station’s drawing was initiated in 1982. The first ISS component, theZarya Module, was launched in 1998 overcoming numerous obstacles through the international cooperation of
the ISS partner countries.

The ISS construction was once suspended due to the Space Shuttle Columbia

accident in 2003. However, from 2006, the ISS construction has resumed with the target completion year set at
2010.
This chapter describes the background and the surrounding issues related to the development of Kibo fromthe perspectives of cross-border collaboration and Japan’s domestic activities.

1.2

International Space Station (ISS) Program

1.2.1 Outline
The International Space Station (ISS) is a manned research facility flying about 400 km above the earth.
While the ISS orbits the earth at a rate of 90 minutes per orbit, earth observation, astronomical observations
and scientific experiments are conducted on-board.
The primary objectives of the ISS are to provide a facility for conducting long-term experiments andresearches by using the environment unique to space, to promote science and technology by utilizing the resultsfrom these experiments and researches, and to contribute to the betterment of mankind and a means forcommercial development.
For the assembly and construction of the ISS, the US space shuttles and Russia’s Proton and Soyuz launchvehicles are used for transporting the ISS components, one segment after another, more than 40 launches
projected to assemble the ISS.

The US, Japan, Canada, Russia and 11 of the 17 member countries of theEuropean Space Agency (ESA), including Italy, Denmark, Norway, Belgium, Netherlands, France, Spain,
Germany, Swedish, Switzerland and the United Kingdom (UK), are participating in this international
collaborative program, as ISS partner countries.

Japan contributes to the ISS program through thedevelopment and utilization of Kibo.
Figure 1.2.1-1shows an overview of the ISS. Table 1.2.1-1 shows the ISS specifications.

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Kibo HANDBOOK

Figure 1.2.1-1 ISS Overview

Table 1.2.1-1 ISS Specifications
Items

Specifications

Size

108.5 m x 72.8 m (Size is equivalent to an American football field)

Mass (Weight)

420 t

Power Generation

110 kW

Number of pressurized modules

Experiment Modules: 5(includes: US 1 (Destiny), Japan 1 (Kibo), ESA 1 (Columbus), Russia 2(RM, MLM))
Habitation Modules: 1(Russia 1 (Zvezda))

External Research
Accommodations

10 on the ISS truss
10 on Kibo’s Exposed Facility (EF)
4 on Columbus

Number of crew (capacity)

6 (2 to 3 during the construction/assembly phase)

Orbit

Circular Orbit (Altitude 330 to 480 km)
Inclination 51.6 degree

Transportation system/launchvehicleAssembly flight: Space Shuttle (US), Soyuz launch vehicle / Proton
launch vehicle (Russia)
Logistics flight: Space Shuttles (US), Soyuz launch vehicle (Russia),
Ariane launch vehicle (ESA), H-IIB launch vehicle (Japan)

1-3

1. Background on Development of Kibo

1.3

Background of Kibo Development

In June 1982, the government of Japan was requested from NASA to participate in the Space Station
Program.

In response to this request, a technical study led by the National Space Development Agency ofJapan (NASDA) was initiated to establish the basic framework for Japan’s participation in the Space Station
Program.

In August 1982, the Space Station Program Task Force was formed under the auspices of the Space

Development Committee. Deliberations on Japan’s participation in the Space Station Program Framework werestarted.
In April 1985, the "Basic Framework for Participating in the Space Station Program" was established basedon the results from the studies conducted by the Space Development Committee's Space Station Taskforce.
Japan’s participation in the Space Station Program was then officially announced.

In the "Basic Frameworkfor Participating in the Space Station Program", the significance of Japan’s participation in the program wasdescribed.

The following is a summary of the framework.

(1) High Technology Acquisition
The space station is expected to actively and extensively use advanced technologies.

This will ultimately

lead to acquiring techniques for supporting manned space flight and the developing leading edge spacetechnologies while this large construction project in space is ongoing.

The space station will also lead to thepromotion and development of advanced technologies in several fields including robotics, computers, andcommunications.

In addition, significant improvements in advanced technology standards are anticipated.

(2) Promotion of Science and Technology for the Next Generation, and Expansion of Space
Activity Scope
The space station has the capability to 1) extend the amount of time that humans can spend in space, 2)
accommodate many crew members, and 3) increase power supply and crew time.

This capability would

enable extensive scientific observations or conducting larger experiments in space. It would also increase theopportunity for new scientific findings and promote the development of new technologies.

In addition, thespace station has the capability of being an outpost for on-orbit space activities, or could be a base station forsupporting manned explorations to the moon and other planets. These capabilities will lead to expanding thescope of human activities in space.
(3) International Contribution
Japan is expected to fulfill Japan’s share of international responsibility by contributing to the world’s spacedevelopment through the technologies fostered by Japan’s own independent developments or by utilizing thespace shuttles.

Through collaboration and participation in the Space Station Program, the relationshipbetween the US and Japan can be maintained or enhanced.

In addition, Japan’s technology will be enhancedby keeping pace with the world’s space development.

Specifically, Japan will be able to internationally

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Kibo HANDBOOK

contribute to the advanced technology fields, including electronics, optical communication and robotics, which
are technological strengths of Japan.
(4) Promotion of Practical Application of Space Environment Utilization
Recently, experiments using the space environment, including the development of materials and the
production of medicines, are being promoted.
significant amount of attention.

The utilization of the space environment has received a

The Space Station Program will advance space environment utilization.

Space utilization is generally targeted for commercial activities. Expansion of commercial activities in space
is a goal for many countries, including the United States.
With the aim of achieving the above objectives, Kibo has been developed as Japan’s first manned spacecraft.
Table 1.3-1 shows the background of Kibo development.
Table 1.3-1 Background of Kibo Development (1/2)
Timeline

Activities

April, 1984

In response to US President Reagan’s request, NASDA and the commissioned
companies began studies on Japan’s participation in the Space Station Program

May, 1985

The government of Japan signed a Memorandum of Understanding (MOU) with
NASA that pertained to Japan’s participation in the space station’s preliminary
design. The preliminary design was continued for two years thereafter.
Policy-related discussions with NASA were conducted under the auspices ofJapan’s Science and Technological Agency (STA). Technical andengineering-related discussions with NASA were conducted under the auspices of
NASDA.

March, 1987

Completion of the space station’s preliminary design.

March, 1989

A MOU was signed between NASA and the government of Japan.

June, 1989

Japan’s Diet (Japan’s legislature) approved the Inter-Governmental Agreement(IGA) that covered the detailed design, development, operation and utilization of aregularly manned civil space station, and included the US government, European
countries that are members of the ESA, the government of Japan and Canada’s
government. Japan officially started the full-scale development of the JapaneseExperiment Module for the Space Station Program.

January, 1990

Japan initiated basic designs of Kibo’s systems and components.

March, 1990

The “Tokyo Agreement” was executed to establish standardization requirements for
the International Standard Payload Rack (ISPR) for use with the ISS modules. The
standardizing requirements for the ISPR had been discussed amongst NASA, ESA
and NASDA, as part of their trilateral cooperation. The standardizing requirements
stipulated and defined the system interfaces, including the rack structure envelope,attachment mechanisms to the ISS modules, power, cooling, data, and videointerfaces.

March, 1994

Design of a newly reconfigured space station, also renamed as the “International
Space Station (ISS)”, was approved. During the reconfiguration and review, theinterfaces between Kibo and the ISS were revised. The control documents related
to Kibo’s launch, operations and development were also reviewed.

March, 1994

Development of the Kibo Flight Model (PFM) was initiated.

1-5

1. Background on Development of Kibo

Table 1.3-1 Background of Kibo Development (2/2)
Timeline

Activities

July, 1996

Development of Kibo’s Inter-orbit Communication System (ICS), which will be
used for communications between Kibo and the Data Relay Test Satellite (DRTS),
also known as “Kodama”, was decided, based on the consensus to utilize the
DRTS.

April, 1999

The name of the Japanese Experiment Module was domestically solicited and,
“Kibo” was selected from the numerous names that were submitted.

May, 2000

Kibo’s Experiment Logistics Module-Pressurized Section (ELM-PS) arrived at
Tsukuba Space Center (TKSC). A series of tests on the ELM-PS systems were
initiated.

November, 2000

Kibo’s Exposed Facility (EF) was shipped from the prime contractor to TKSC. A
series of tests on the EF systems were initiated.

December, 2000

Kibo’s Experiment Logistic Module-Exposed Section (ELM-ES) was shipped fromthe prime contractor to TKSC. A series of tests on the ELM-ES systems were
initiated.

September, 2001

After completing a series of system tests, Kibo’s Pressurized Module (PM) was
shipped from the prime contractor to TKSC.

October, 2001

Kibo’s total system test was conducted from October 2001 to May 2002.

April, 2003

At the NASA-NASDA PM Pre-shipment Review meeting held on April 7th, thePM was verified as satisfying the requirements for transferring to the US. On April
22nd, the PM departed on a river barge from Tsuchiura New Harbor to Yokohama
Harbor.

May, 2003

The PM departed on an ocean vessel from Yokohama Harbor to NASA’s Kennedy
Space Center (KSC). The PM arrived at Port Canaveral, which is adjacent to the
KSC on May 30th.

August, 2003

At KSC, the PM went through the Multi-Element Integrated Test-III (MEIT-III),
which is a test that verifies the system functionality and interface compatibility
between the PM and the connection module, Node 2.

September, 2003

From September 2003 to March 2004, a series of tests on the PM were conducted,
including the functionality verification tests, the Flight Crew Interface Test (FCIT),
leak tests and a series of checkouts and inspections prior to classifying the PM as,“in loading process”. One year prior to launch is set as the “functionality
maintenance period”. During this period, various tasks are scheduled that’s targetedto the loading of the PM on to the space shuttle.

January, 2007

On January 12th, Kibo’s robotic arm, Japanese Experiment Module Remote
Manipulator System (JEMRMS) was shipped via air transport, from TKSC to KSC.
On January 26th, Kibo’s ELM-PS was shipped from TKSC. The ELM-PS wasshipped via river barge from Tsuchiura New Harbor to Yokohama Harbor.

February, 2007

On February 7th, the ELM-PS departed on an ocean vessel from Yokohama Harbor
to KSC. The ELM-PS arrived at Port Canaveral, which is adjacent to KSC on
March 12th.

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Kibo HANDBOOK

2. Kibo Elements

2-1

2. Kibo Elements

2.1

Kibo Elements

The Japanese Experiment Module (JEM), also known as Kibo, consists of six components: two experiment
facilities of the Pressurized Module (PM) and the Exposed Facility (EF), a Logistics Module that is attached toeach of the PM and EF, a Remote Manipulator System(RMS), and an Inter-Orbit Communication System(ICS).
Figure 2.1-1 shows an overview of the assembled Kibo structure.
Air, electrical power, heat and communications, which are essential for Kibo’s operation, will be supplied
from the International Space Station (ISS).
Inside the space shuttle cargo bay, electrical power is provided to the Kibo’s elements from the Space Shuttle
to prevent the coolant water lines from freezing, and to maintain optimal temperatures within the criticalcomponents prior to final attachment to the ISS.

Kibo

Direction of travel

Experiment Logistics Module-Pressurized Section(ELM-PS)JEM Remote Manipulator System(JEMRMS)

Pressurized Module (PM)Exposed Facility (EF)Inter-orbit Communication System (ICS)
Experiment Logistics Module- Exposed Section (ELM-ES)

Figure 2.1-1 Kibo Structure

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Kibo HANDBOOK

2.1.1 Pressurized Module (PM)Kibo’s Pressurized Module (PM) is 11.2 meters in length and 4.4 meters in diameter. The PM’s internal airpressure is maintained at one atmosphere (1 atm), thus providing a shirt-sleeve working environment for thecrew.

ISS crew will conduct unique microgravity experiments within the PM. The PM will hold 23 racks -ten of which are International Standard Payload Rack (ISPR) for experiment payloads. The remaining 13
racks are dedicated to Kibo’s systems and storage.
Kibo also has a scientific airlock, the “JEM Airlock”, through which experiments are transferred andexposed to the external environment.
Figure 2.1.1-1 shows a picture of the PM.

Pressurized Module (PM)JEM Airlock

Figure 2.1.1-1 Pressurized Module (PM)2-3

2. Kibo Elements

2.1.2 Experiment Logistics Module - Pressurized Section (ELM-PS)
Kibo’s Experiment Logistics Module - Pressurized Section (ELM-PS) provides a storage space forexperiment payloads, samples and spare items.

The interior of the ELM-PS is controlled and maintained at

the same air pressure and temperature as that of the PM, and astronauts will be able to freely move between the
ELM-PS and the PM.

Among the ISS research facilities/modules, Kibo is the only experiment module with

its own dedicated storage facility.
Figure 2.1.2-1 shows an external view of the ELM-PS.

Figure 2.1.2-1 Experiment Logistics Module-Pressurized Section (ELM-PS)

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Kibo HANDBOOK

2.1.3 Exposed Facility (EF)Kibo’s Exposed Facility (EF) provides a multipurpose platform where science experiments can be deployed
and operated in the exposed envirnment. The experiment payloads attached on the EF will be exchanged or
retrieved by using Kibo’s robotic arm, the “JEM Remote Manipulator System (JEMRMS)”, which will be
operated by the crew from inside the PM.
Figure 2.1.3-1 shows an external view of the EF.

Figure 2.1.3-1 Exposed Facility (EF)2-5

2. Kibo Elements

2.1.4 Experiment Logistics Module - Exposed Section (ELM-ES)
Kibo’s Experiment Logistics Module-Exposed Section (ELM-ES) is attached to the end of the EF andprovides a storage space for experiment payloads and samples. Experiment payloads and samples are stored
for later use for the experiments on the EF.

Up to three experiment payloads can be stored on the ELM-ES.

In addition, the ELM-ES provides a logistics function where the ELM-ES can be detached from the EF andreturned to the ground aboard the space shuttle along with completed experiments or samples. The ELM-ES
can be re-stocked and then launched again on missions to the ISS.
Figure 2.1.4-1 is an overview of the ELM-ES.

Figure 2.1.4-1 Experiment Logistics Module-Exposed Section (ELM-ES)

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Kibo HANDBOOK

2.1.5 JEM Remote Manipulator System (JEMRMS)
Kibo’s robotic arm, JEM Remote Manipulator System (JEMRMS), serves as the human arm and hand insupporting the experiments conducted on the EF. The JEMRMS is composed of the Main Arm (MA) and the
Small Fine Arm (SFA). Each arm has six joints.

The MA is used primarily for exchanging external EF

payloads and for moving large items. The SFA, which is attached to the end of the MA, is used for moredelicate operations.

The crew will operate these robotic arms from a remote operations console, the JEMRMS

Console, located inside the PM.

The crew will watch external images, taken from the cameras that are

attached to the MA, on a television monitor at the JEMRMS Console.
Figure 2.1.5-1 shows a picture of the JEMRMS.

Main Arm（MA)EF ORU mock-up

Small Fine Arm（SFA)

Figure 2.1.5-1 JEM Remote Manipulator System (JEMRMS) -Combination Operation Test

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2. Kibo Elements

2.1.6 Inter-orbit Communication System (ICS)
Kibo’s Inter-Orbit Communication System (ICS) provides independent intercommunications between Kibo
and the Tsukuba Space Center (TKSC).

Through the JAXA’s Data Relay Test Satellite (DRTS), commands

and voice are uplinked from the ground to Kibo, and experiment data, image data or voice are downlinked from
Kibo to the ground for scientific payload operations.

The ICS consists of two subsystem components:

ICS-Pressurized Module (ICS-PM) and ICS-Exposed Facility (ICS-EF). The ICS-PM, which is installed in thePM, provides command and data handling functions. The ICS-EF has antenna and pointing mechanism thatwill be used to communicate with the DRTS.
Figure 2.1.6-1 shows pictures of the ICS subsystems.

Antenna(being stowed)

Space for PROX system
ICS-Pressurized Module(ICS-PM)ICS-Pressurized Module (ICS-PM)ICS Exposed Facility subsystem (ICS-EF)

PROX (Proximity Communication System) is a communication system which will be used for arendezvous operation of the H-II Transfer Vehicle (HTV)
Figure 2.1.6-1 Inter-orbit Communication System (ICS)

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3. Kibo Specifications

3-1

3. Kibo Specifications

3.1

Specifications of Kibo Components

Table 3.1-1 shows the specifications for Kibo’s components. Figure 3.1-1 shows Kibo’s configuration
diagrams.

For further details on Kibo’s components, please refer to Chapter 4.

Table 3.1-1 Specifications
Component

Dimension (m)Pressurized Module (PM)Outer Diameter: 4.4
Inner Diameter: 4.2
Length: 11.2

15.9

23 racks ( 11 Kibo’s System Racks
and 12 International Standard
Payload Racks (ISPR) )Experiment Logistic
Module-Pressurized
Section (ELM-PS)

Outer Diameter: 4.4
Inner Diameter: 4.2
Length: 4.2

4.2

8 racks

Remote Manipulator
System (JEMRMS)

Length:Main Arm: 10
Small Fine Arm: 2.2

1.6(Includes RMS
console)Main Arm’s maximum lifting
capacity: 7 t

Exposed Facility (EF)Width: 5.0
Height: 4.0
Length: 5.6

4.1

12 attachments for EF payloads (10for payloads and 2 for systems. In
addition, one space for temporarystorage/attachment is available)

Experiment Logistic
Module-Exposed Section(ELM-ES)

Width: 4.9
Height: 2.2
Length: 4.2

1.2

3 EF payloads

Total

27

3-2

Mass (t)Number of racks or ISPRs installedKibo HANDBOOK

φ4.4m
4.2m
（CBM
inclusive）

ELM-PSJEMRMS

8.6m

PM

φ4.4m

10m

11.2m
20.5m

8.9m

4.9m

ELM-ESEF

CBM: Common Berthing Mechanism
Figure 3.1-1 Kibo Configuration Diagram

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3. Kibo Specifications

3.2

Kibo Operation Mode

Four different operation modes are used for managing Kibo’s systems.

Kibo operation mode varies

according to the Kibo’s operations and/or the upper ISS operation modes.

Kibo operation modes and thecorresponding descriptions are shown in Table 3.2-1. The operation mode can be switched manually by crew
or by commands sent from the ground.

Figure 3.2-1 shows the Kibo operation mode transition.

Similarly, the International Space Station (ISS) has seven operation modes. All the ISS operation modes
are switched by commands sent from the ground or by the crew.

The ISS operation modes and theircorresponding descriptions are shown in Table 3.2-2.
There are situations where Kibo operation modes are constrained depending on the status of the ISS
operation mode. For example, the ISS operation mode has to be set as “External Operation Mode” whenswitching the Kibo operation mode from “Standard Operation Mode” to “Robotics Operation Mode” for
JEMRMS operation. The relation between Kibo operation modes and ISS operation modes are shown in
Table 3.2-3.

In the event of an ISS emergency, the ISS operation modes will be switched accordingly;

however if Kibo operation mode at this point is not applicable, then Kibo operation mode will be switched to“Standby Mode” automatically.

Table 3.2-1 Kibo Operation Modes
Kibo Operation Mode

Mode Description and Status

Standard Operation Mode

Kibo primary operation mode. The crew can conduct experiments.
However, the crew can not use the JEMRMS.

Robotics Operation Mode

The mode where the crew operates Kibo’s robotic arms. The other features
are the same as those of “Standard Operation Mode”.

Standby Mode

Mode for when an emergency occurs with Kibo’s systems. In emergency
cases, Kibo will be operated with minimal systems by prohibiting all theexperiment supports.

Isolation Mode

Mode for when the pressurization in the Kibo’s pressurized section cannot
be maintained. In this mode, the hatch between Kibo and ISS will beclosed and crew will not be able to enter either the PM or ELM-PS.

CommandStandard Operation Mode

Robotics Operation Mode
CommandCommandCommand or
Automatic

Command or
AutomaticStandby Mode
CommandCommand

Isolation Mode
Figure 3.2-1 Kibo Operation Mode Transitions
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Table 3.2-2 ISS Operation Modes
ISS Operation Mode

Mode Description and Status

Standard ModeISS primary operation mode.

Re-boost Mode

Mode for when the ISS changes orbital altitude (re-boost).

Microgravity Mode

Mode for operating the experiment payloads that require a
microgravity environment.

Survival Mode

Mode for ISS critical emergency situations (eg when a verified
anomaly occurs with the ISS power or attitude control systems).
This mode is used to sustain the long-term operation/survivability of
the ISS.

Proximity Operation Mode

Mode for when spacecrafts, including the space shuttles, Soyuz
spacecrafts and Progress cargo ships are in proximity operations todock or undock/depart from the ISS.

Assured Safe Crew Return (ASCR)
Mode

Mode for when the life of the ISS crew is in danger and forsupporting the swift departure (undock/separation) of the Soyuz for
returning the crew safely back to the ground.

External Operation Mode

Mode to support Extravehicular Activities (EVAs) or robotic arm
operations for external assembly or maintenance.

Table 3.2-3 Applicability of Kibo Modes to ISS Operation Modes
Standard

Re-boost

Microgravity

Survival Operation

Proximity Operation

Assured Safe Crew
Return (ASCR)

External Operatione

Standard

A

A

A

NA

A

A

A

Robotics Operation

NA

NA

NA

NA

NA

NA

A

Standby

A

A

A

A

A

A

A

Isolation

A

A

A

A

A

A

A

ISS Operation Mode

Kibo Operation Mode

A: Applicable
NA: Not Applicable

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4. Kibo System Components

4-1

4. Kibo System
ystem Components

4.1

Pressurized Module (PM)4.1.1 Brief Summary
Kibo’s Pressurized Module (PM) is a research facility
where astronauts will enter and conduct scientific experiments
or control Kibo’s systems.

The air composition inside the PM

is nearly the same as that on earth. The air pressure ismaintained at one atmospheric pressure (1atm), thus providing
a comfortable working environment for the astronauts. The
temperature and humidity inside the PM are also controlled sothat the astronauts will be able to work in a shirt-sleeve
environment.
Figure 4.1.1-1 PM location

The racks that will be installed inside the PM are basicallydivided into two categories; JEM system racks which willcontrol and maintain Kibo’s facilities, and payload racks which will be used for experiments inside the PM.
The JEM system racks includes, power supply, communications, air conditioning, thermal control andexperiment support systems. The console for Kibo’s robotic arms (JEMRMS Console) and the scientificairlock (JEM Airlock) are Kibo’s unique system.
The research payloads are for conducting experiments that have been solicited and selected fromapplications submitted from the general scientific community. The PM will hold ten International Standard
Payload Racks (ISPRs) for various types of experiments; mainly for life science and material science
experiments.
Table 4.1.1-1 shows the specifications for the PM.

Table 4.1.1-1 PM Specifications
Items
Shape
DiameterOuter diameter
Inner diameter

LengthMass
Number of Payload Racks
Electrical Power
Data management system
Environmental
control
Number of crew
Life time

4-2

Temperature
Humidity

Specifications
Cylindrical
4.4 m
4.2 m
11.2 m15.9 t23 racks
JEM system racks: 11
Scientific experiment racks: 12 (10 research/experiment
racks, one refridgerator rack, and one stowage rack)Max. 24kW, max. 120V DC
32-bit computer system
High-speed data link: max. 100 Mbps
18.3 to 26.7 degrees Celsius (°C)
25 to 70 %2 persons for normal operation (max. 4 persons)More than 10 years

Kibo HANDBOOK

4.1.2 Layout
Figure 4.1.2-1 shows an external view and structure of the PM.

JEMRMS base plate
Window
Hand Rails for
Extravehicular Activity

JEM Airlock

Debris Shield

Exposed Facility Berthing Mechanism (EFBM)

Hand Rails for Extravehicular Activity
to Node 2
Debris Shieldto ELM-PS

φ4.4m

Hatch
Common Berthing
Mechanism (CBM)
Window

JEMRMS base plate

11.2m
JEM Airlock

Exposed Facility Berthing Mechanism (EFBM)
Figure 4.1.2-1 Kibo’s PM

4-3

4. Kibo System Components

Inside the PM, the inner walls will hold racks that are composed of either JEM system or scientific research
payloads. The work space inside the PM is almost square in shape and is 2.2 m in height and width.

Aninternal view of the PM is shown in Figure 4.1.2-2.
The PM can hold a total of 23 racks.

The racks are built into the inner four walls of the PM.

Of the four

inner walls, six racks will be built into three of the walls, and five racks will be built in the remaining wall.
Of these racks, 11 racks are for JEM system, and 12 are for payloads.

The racks can be attached or detachedon orbit. Figure 4.1.2-3 shows the locations of the JEM system racks. Figure 4.1.2-4 shows the locations of
the payload racks.

A schematic of how to attach and/or detach the racks is shown in Figure 4.1.2-5.

The payloads racks are designed according to the standardized specifications for hardware interface powerand data interface. These racks built in accordance with the required standardized specifications are called“International Standard Payload Rack (ISPR)”. Of the 12 payload racks inside of the PM, 11 racks are ISPRs
and one rack is for storing experiment materials.

DMS: Data Management System
EPS: Electric Power System
ECLSS: Environmental Control and Life Support System
TCS: Thermal Control System
LIFE: Life Science Payload Rack
MTL: Material Science Payload Rack
Figure 4.1.2-2 Internal Image of PM (view as may be seen from the Harmony Module)
4-4

Kibo HANDBOOK

Aft
Port
Starboard
Forward (direction of travel)
Data Management System (DMS) Rack 1
Inter-orbit Communication System RackJEMRMS Rack

Stowage Rack 1
DMS Rack 2

JEM Airlock

to Node 2
ECLSS/TCS Rack 2
ECLSS/TCS Rack 1

Electric Power System Rack 2

Electric Power System Rack 1
Workstation Rack

Stowage Rack 2

Figure 4.1.2-3 JEM System Racks inside PM

Aft
Port

ELM-PS

Starboard
Forward (direction of travel)
Material Science
Payload Racks(ISPR)
Life Science
Payload Racks(ISPR)JEM Airlock

Stowage Rack

to Node 2
Material Science Payload Racks (ISPR)
Refrigerator Rack
Material Science Payload Racks (ISPR)
Life Science Payload Racks (ISPR)

Figure 4.1.2-4 Experiment racks (ISPRs) inside PM
4-5

4. Kibo System
ystem Components

Rack

Figure 4.1.2-5 Schematic of how to attach or detach the racks: Each rack can individually be attached anddetached for relocation, exchange, or maintenance.

4.1.3 System Components of PM
The PM is composed of the following subsystems.
•

Command and Data Handling (C&DH)•

Electrical Power System (EPS)•

Communication and Tracking (C&T)•

Thermal Control System (TCS)•

Environmental Control and Life Support System (ECLSS)•

Experiment Support System (ESS)•

Structure•

Mechanical System•

Crew Support System (CSS)The Command and Data Handling (C&DH), the Electric Power System (EPS), the Communication andTracking (C&T), the Thermal Control System (TCS) and the Environmental Control and Life Support System(ECLSS) are in particular critical systems, and thus, have redundant structures composed of primary andsecondary strings. If a system’s primary string fails, the secondary string will takeover the primary’s function
and capability, and will fully or partially maintain the system. When the PM is in an operational status,

4-6

Kibo HANDBOOK

basically, both primary and secondary strings of the above listed systems will be activated.

The followings

are details of the systems/subsystems.
(1) Command and Data Handling (C&DH)
The Command and Data Handling (C&DH) system includes the JEM Control Processor (JCP), which is
Kibo’s central subsystem that controls and monitors the status of Kibo’s system and experiment payloads.
The JCP also controls the setting of Kibo Operation Mode in concert with the ISS Operation Modes.

Forfurther information on Kibo’s and ISS operation modes, please refer to Chapter 3, Section 3.2.
This subsystem also has data processing functions, including collecting and compiling Kibo’s system status
data and experiment data for downlink to the ground, relaying data files to each of Kibo’s systems through theCommunication and Tracking (C&T) system, or relaying the actual time data provided from the ISS to eachpayload or system onboard Kibo. Kibo is equipped with two JCP units for redundant purposes. If one of the
JCP units fails, the second JCP unit will automatically take over the control and fully maintain the functions
and capabilities that the JCP is responsible for.
(2) Electrical Power System (EPS)The Electric Power System (EPS) converts and distributes the electrical power (two electrical powerchannels, 120V DC each) that is supplied from the Node 2 of the ISS. The EPS consists of various units
including, Power Distribution Boxes (PDBs) and Power Distribution Units (PDUs) that distributes power topayloads and system equipments.
(3) Communication and Tracking (C&T)
The Communication and Tracking (C&T) consists of Low /Medium/High Data Rate Systems, Video System
and Audio System.
The Low Rate (max. 1Mbps), Medium Rate (max. 10Mbps) and High Rate (max. 100 Mbps) Data Systems
relays the data sent from the C&DH system to each subsystem, and collects data from the JEM system or
payloads to be relayed to the C&DH system.
The Video System is composed of Television Cameras (TVCs) which are installed inside and outside of Kibo,
Television Monitors and Camera Control Panels (CCPs).

The Video System will transmit visual images takenby the TVCs.
The Audio System is composed of Audio Terminal Units (ATUs) installed in the Work Station Rack (WSRack) and JEMRMS rack.

The ATU is a unit common to the ISS.

ATUs are installed in several locations

within the ISS. The crew can use the ATUs as an interphone for communicating with another crew in adifferent segment of the ISS.
(4) Thermal Control System (TCS)The Thermal Control System (TCS) consists of the following two systems: An Active Thermal Control
4-7

4. Kibo System Components

System (ATCS) which transfers the heat generated in the Kibo’s equipments by means of circulating coolant
water in the coolant loops, and a Passive Thermal Control System (PTCS) which controls and maintains thetemperature of Kibo’s equipment through the use of insulating materials or heaters.

Two water coolant loops,

the Low Temperature Loop (LTL) and Moderate Temperature Loop (MTL) are included in the PM.

The heat

generated in Kibo is collected and discharged through two external ammonia coolant loops (medium and low
temperature), known as the Interface Heat Exchanger (IFHX), which is located on the Node 2 exterior.

Amaximum of 25kW of heat can be discharged through the medium temperature IFHX, and a maximum of 9 kW
can be discharged through the low temperature IFHX.
(5) Environmental Control and Life Support System (ECLSS)
The Environmental Control and Life Support System (ECLSS) controls and maintains the temperature insideof the PM within a range of 18.3 to 26.7 degree Celsius (°C) and humidity within a range of 25 to 70 %. The
astronauts will be able to conduct experiments in a shirt-sleeve environment.

This system provides acomfortable and safe intra-vehicular environment.
The pressurized air is adjusted by a mixture of oxygen and nitrogen supplied from the US segment of the ISS.
The air is circulated inside Kibo by fans for inter-module ventilations, and then returned to the ISS US
segment.
Kibo has fire detection and suppression function. Smoke sensors will detect any fire. The fire’s location
will be isolated by power shut down. Fire extinguishers (carbon dioxide) will be used to suppress the fire.
(6) Experiment Support System (ESS)The Experiment Support System (ESS) supplies argon (Ar), helium (He), nitrogen (N2) and carbon dioxide(CO2) to the payload racks located in the PM. The ESS also conducts vacuum ventilation and evacuates thegasses from the payload racks. The Common Gas Supply Equipment (CGSE) is a unique special element of
Kibo. The CGSE contains gas bottles of Ar, He and CO2, and supplies these gases to each experiment rack.
Nitrogen gas that will be supplied to the experiment racks is provided from NASA’s Environment Control andLife Support System (ECLSS).
(7) Structure
The structural body of the PM is designed to bear loads imposed during the space shuttle’s launch, ascent,ISS attitude control and maneuver.

At the same time, the system will maintain a pressurized environment

inside the PM through a shielding of aluminum alloy panels. The Debris Shield covers the PM’s outer shellstructure to protect the body from debris impacts.

The PM is equipped with two windows located on the sideof the EF docking port. Astronauts will be able to look outside through these windows.
Passive Common Berthing Mechanism hatch is part of the PM’s structure.

4-8

The Node 2 side’s

Kibo HANDBOOK(8) Mechanical System
The Mechanical System consists of the following three mechanisms: 1) the Common Berthing Mechanism(CBM) which will be used as the berthing port for the Node 2 or the ELM-PS, 2) the JEM Airlock and 3) the
Exposed Facility Berthing Mechanism (EFBM).
Airlock.

The following are further details on the CBM and the JEM

For details of the EFBM, please refer to Section 4.3.3 in this chapter.

(a) Common Berthing Mechanism (CBM)
The Common Berthing Mechanism (CBM) is an ISS common mechanism designed to connect different ISS
modules (except Russian modules).

The CBM ensures that the modules berthed by the CBM maintain apressurized environment where astronauts and materials can move freely between different ISS modules.
The CBM is paired and composed of active and passive parts: the Active CBM (ACBM) that uses electricmotors for berthing and the Passive CBM (PCBM). The PM has both the PCBM and the ACBM.

ThePCBM is located on the Node 2 berthing port, and the ACBM is located on the berthing port for the
Experiment Logistics Module's Pressurized Section (ELM-PS).

Figure 4.1.3-1 shows an outline andconfiguration of the CBM.

Capture latch
Bolt

φ2.0m

φ2.0m
Structure
Ring

Alignment Guide
CBM controller

Alignment Guide
PCBM

ACBM

ELM-PS
ACBM

ACBM

PCBM

JEMRMS
Node2

PM
EF

Figure 4.1.3-1 Common Berthing Mechanism (CBM)

4-9

4. Kibo System
ystem Components(b) JEM Airlock
An airlock is basically a passage or small area where air pressure can be adjusted for differences between
two docked neighboring compartments so as to allow astronauts or equipments to move between the twocompartments.
The JEM Airlock is designed for transferring experiments and supplies; humans cannot enter this airlock.
The JEM Airlock inside is pressurized with air at one atmospheric pressure and the EF which is exposed to thevacuum space environment.

The JEM Airlock is used for transferring experiment payloads or samples

between PM and EF.
The JEM Airlock is cylindrical and equipped with the Inner Hatch which is located inside of the PM side and“Outer Hatch” which is located outside of the EF side. Experiments and supplies that will be transferredthrough the airlock are first fastened on a slide table, and then, transferred by extending the slide table.

The“Inner Hatch” is equipped with a small window so that astronauts can visually check the inside of the airlock.
Pressurized
section (PM)Exposed section(Vacuum)
Small window

Inner Hatch
Outer Hatch

Slide Table

Figure 4.1.3-2 JEM Airlock

Table 4.1.3-1 JEM Airlock Specifications
Item
Outer
Diameter

4-10

Specifications

Outer side

1.7 m

Inner side (inside the PM)

1.4 m

Length

2.0 m

Pressure proof performance

1047 hPa

Allowable size for transfer

0.64×0.83×0.80 m

Allowable weigh for transfer

300 kgPower ConsumptionLess than 600 W

Kibo HANDBOOK(9) Crew Support System (CSS)The Crew Support System (CSS) is composed of support equipment which will be used by astronauts during
inter-vehicular activities.

The CSS includes in-board lightings, emergency lightings, handrails, and footrestraints.

4-11

4. Kibo System Components

4.2

Experiment Logistics Module- Pressurized Section (ELM-PS)

4.2.1 Brief Summary
The Experiment Logistics Module – Pressurized Section, or
ELM-PS will initially be used as a logistics container for
carrying payload racks and system racks from the ground to theISS. Once the ELM-PS is on orbit, the ELM-PS will be used
as a stowage facility.

Maintenance tools for the system andpayloads, samples and spare items will be stored inside the
ELM-PS.

The ELM-PS volume is less than that of the PM.

A total of eight racks can be stored inside the ELM-PS
Table 4.2.1-1 shows the ELM-PS specifications.
Figure 4.2.1-1 ELM-PS location

Table 4.2.1-1 ELM-PS Specifications
Items
Structural Type
Diameter

4-12

Specifications
Cylindrical

Outer Diameter

4.4 m

Inner Diameter

4.2 m

Length

4.2 m

Mass

4.2 t

Number of Racks

8 racks

Power provided

3kW 120V DC

Environment

Temperature: 18.3 to 29.4 degree Celsius (°C)
Humidity: 25 to 70 %Life Time

More than 10 years

Kibo HANDBOOK

4.2.2 Layout
Figure 4.2.2-1 shows the ELM-PS structure.

Figure 4.2.2-2 shows the rack locations inside the ELM-PS.

ELM-PS Exposed Facility Unit

Common Berthing
Mechanism (CBM)

φ4.4m

4.2m
CBM Hatch (for PM)

Figure 4.2.2-1 ELM-PS Structure
Forward (direction of travel)

Aft
StarboardPort
Forward(Direction of travel)

Port

Starboard

Image of right side is internalview of ELM-PS which is seenfrom PM

Aft
Figure 4.2.2-2 Rack Locations inside ELM-PS

4-13

4. Kibo System Components

4.2.3 System Components of ELM-PS
The ELM-PS consists of the following subsystems.
•

Electrical Power System (EPS)•

Communication and Tracking (C&T)•

Thermal Control System (TCS)•

Environmental Control and Life Support System (ECLSS)•

Structure•

Mechanical System•

Crew Support System (CSS)

Each ELM-PS subsystem is driven with one-string system, whereas the PM’s subsystems have a redundantfunctionality. The followings are details of the ELM-PS subsystems.
(1) Electrical Power System (EPS)The Electrical Power System (EPS) distributes electrical power provided by the PM’s EPS to each ELM-PS
subsystem. In the event that the PM EPS fails, a second PM EPS channel is available as backup; however thecrew will need to change the wiring. When the ELM-PS is attached temporarily to the Node 2 awaiting arrivalof the PM (Please refer to Chapter 5, Section 5.2.1), the electrical power will be supplied to the ELM-PS fromthe Node 2.
(2) Communication and Tracking (C&T)
The Communication and Tracking (C&T) consists of a Medium (max. 10 Mbps) Data System, Video System
and Audio System.

The C&T relays the data from the ELM-PS subsystems or images inside of the ELM-PS

to the PM’s Communication and Tracking (C&T) system.
(3) Thermal Control System (TCS)The Thermal Control System (TCS) maintains the temperature inside the ELM-PS, within a required range,
by means of a Passive Thermal Control System (PTCS) that controls the thermal environment through the useof thermal insulating materials and heating devices.
(4) Environmental Control and Life Support System (ECLSS)
The Environmental Control and Life Support System (ECLSS) controls the atmospheric pressure,temperature and humidity inside the ELM-PS so as to provide a shirt-sleeve working environment.
subsystem provides a comfortable inner vehicular environment similar to that of the PS.
is circulated by fans and supplied from the PM.

4-14

This

In the ELM-PS, airKibo HANDBOOKIn addition, this subsystem has fire detection and suppression functions.
The fire will be isolated by power shut down.

Smoke sensors will detect any fire.

The fire will be suppressed by fire extinguishers (carbon

dioxide).
(5) Structure
Similar to the PM, the ELM-PS structural body is designed to bear loads imposed during the space shuttle’s
launch, ascent, ISS attitude control and maneuver. The ELM-PS is also designed to maintain a pressurizedenvironment inside the ELM-PS through shielding by aluminum alloy panels. Debris Shield covers the
ELM-PS’s outer shell structure so as to protect the body from debris hit. The berthing hatch for the PM is partof the ELM-PS’s structure.
(6) Mechanical System
The Mechanical System consists of a Common Berthing Mechanism (CBM), which will be used as theberthing port for the Node 2 or the PM, and the ELM-PS Unit Replacement Mechanism (Note: A Passive CBM(PCBM) is attached to the body of the ELM-PS).
Unit (EFU).

The followings are details of the ELM-PS Exposed Facility

For details on the CBM, please refer to Section 4.1.3 in this chapter.

(a) ELM-PS Exposed Facility Unit (EFU)
While the H-II Transfer Vehicle (HTV) is berthed to the ISS, payloads or cargo on the Exposed Pallet (EP)carried by the HTV will be unloaded. The Exposed Pallets carried by the HTV needs to be attached to the
ELM-ES.

For this purpose, the ELM-ES is temporary attached to the ELM-PS whenever the HTV arrives.

At this stage, the ELM-ES is attached to the ELM-PS EFU.

While the ELM-ES is berthed to the ELM-PS

EFU, the ELM-ES is provided electrical power and enables data-exchange. Figure 4.2.3-1 shows an image of
the ELM-ES being berthed to the ELM-PS EFU. For information on the HTV, please refer to Chapter 8.

4-15

4. Kibo System Components

ELM-ES
ELM-PS EFU

ELM-PSJEMRMSEF

Figure 4.2.3-1 ELM-ES berthed to ELM-PS EFU (image)(7) Crew Support System (CSS)The Crew Support System (CSS) provides in-board lightings and emergency lightings inside the ELM-PS.

4-16

Kibo HANDBOOK

4.3

Exposed Facility

4.3.1 Brief Summary
Kibo’s Exposed Facility (EF) is a multipurpose experimentplatform where various scientific activities, including scientificexperiments, earth observation, communication, scientific andengineering experiments or material experiments can be
conducted by utilizing the microgravity and vacuum spaceenvironment. The EF can be used when the EF is berthed to
the PM.

The Equipment Exchange Unit (EEU) willaccommodate a maximum of 12 payloads, including the
Exposed Facility (EF) payloads, ELM-ES and the Inter-orbit

Figure 4.3.1-1 EF location

Communication System (ICS). Since the EF payloads can beexchanged on orbit, it is expected that several different types ofscientific experiments can be conducted on the EF.

In order to support the space-exposed experiments on the EF, the EF will provide the necessary electrical
power to each payload, will circulate coolant so as to keep the payloads within a required temperature and willcollect experiment data.
Table 4.3.1-1 shows the EF specifications.

Table 4.3.1-1 EF Specifications
Items

Specifications

Shape

Box shapedSize

5.0 m (width) x 5.6 m (length) x 4.0 m (height)

Mass

4.1t

Number of attached payload

12 (including 2 for JEM system and 1 for temporary storage)

Electrical power provided

Max. 11 kW (max. 1 kW for system, 10 kW for EF payloads) 120 V DC

Data management system

16-bit computer system
High-speed data link: max. 100 Mbps

Environment control

NoneLife timeMore than 10 years

4-17

4. Kibo System
ystem Components

The EF Equipment Exchange Units (EF-EEUs) are used to attach the EF payloads to the EF. Figure
4.3.2-1(2/2) shows the configuration of the EF with eight EF payloads and the ICS Exposed Facility subsystem(ICS-EF) attached on the EF. The standard EF payload envelope is assumed to be less than 1.85m x 1.0m x0.8m, with a weight of 500kg. Figure 4.3.1-2 shows a standard EF payload configuration.

0.8m
1.85m

1.0m
Grapple Fixture
JEMRMS will grapple here

Payload Interface Unit (PIU)
For details, refer toParagraph 4.3.3 (5) (b)Launch Restraint Trunnion

Figure 4.3.1-2 Standard EF Payload

4-18

Kibo HANDBOOK

4.3.2 Layout
EF Configuration diagram is shown in Figure 4.3.2-1.

Trunnion (x 5)This is a fixture forfastening the EF to thespace shuttle’s cargo bay,when the EF is launched.

Grapple Fixtures (x 2)
SSRMS or SRMS grapple
here

Small Fine Arm (SFA)
Stowage Equipment(SSE)
For details, refer toParagraph 4.5.3

EF Berthing
Mechanism(EFBM)

5.0m

PM

Exposed Facility Unit (EFU) (12 units)
This mechanism is used to attach EF payloads to the EF.
Robot essential Orbital Replacement Unit (R-ORU) (8 units)

PM
4.0m

Extravehicular Activity Orbital Replacement Unit (E-ORU)（4 units）

5.6m

Figure 4.3.2-1（1/2） EF Structure

4-19

4. Kibo System
ystem Components

EF Berthing Mechanism (EFBM)

Grapple Fixtures (x 2)PM
Small Fine Arm (SFA)
Stowage Equipment(SSE)
Trunnion (x 5)

Robot essential
OrbitalReplacement Unit
(R-ORU) (4units)EF Payloads

ICS-EFrefer to section 4.6

EF Equipment Exchange Unit (EEU)（12 units）

Figure 4.3.2-1（2/2） EF Structure

4-20

Kibo HANDBOOK

4.3.3 System Components of EF
The EF consists of the following subsystems;•

Electrical Power System (EPS)•

Communication and Tracking (C&T)•

Thermal Control System (TCS)•

Structure•

Mechanical System

The Electrical Power System (EPS), Communication and Tracking (C&T) and Thermal Control System(TCS) have redundant functionality.

If the primary strings of these subsystems fail, the secondary strings willtake over and maintain their system functions. The following are details of the subsystems.
(1) Electrical Power System (EPS)The Electrical Power System (EPS) receives electrical power from the PM and distributes power to the EF
equipment, Exposed Pallet (ELM-ES), and EF payloads attached to the EF respectively.
(2) Communication and Tracking (C&T)
The Communication and Tracking (C&T) includes the Exposed Facility System Controller (ESC), which isinstalled on the EF and controls the EF equipment or system devices by communicating with the JEM Control
Processor (JCP).

The ESC also relays data between the PM and the EF payloads, such as experiment data,

image, temperature and pressure data.
(3) Thermal Control System (TCS)The Thermal Control System (TCS) is composed of the following two systems.

The Active Thermal

Control System (ATCS) which transfers heat generated in the equipment and payloads by circulating thecoolant, FluorinertTM, and the Passive Thermal Control System (PTCS) which maintains the temperature of the
EF system equipments or payloads through the use of thermal insulators or heaters.

The TCS manages thetemperature environment for the EF system and payloads operation by protecting the EF from the extreme
space thermal environment.

The heat collected by the ATCS will be transferred to the Heat Exchanger

installed on the PM structure. Coolant loops pipes have no redundancy; however other components, such as
pumps, have redundancy.
(4) Structure
The Structure of the EF is composed of box shaped units, which consist of aluminum alloy frames, panels,
and trunnions that are used to attach the EF to the space shuttle’s cargo bay.

4-21

4. Kibo System Components(5) Mechanical System
The Mechanical System is composed of Exposed Facility Berthing Mechanism (EFBM) that is used toconnect the EF with the PM, and Exposed Facility Equipment Exchange Unit (EEU) that attaches EF payloads
to the EF.
(a) Kibo’s Exposed Facility Berthing Mechanism (EFBM)
The EF Berthing Mechanism (EFBM) is a mechanism to connect the EF to the PM.

It is paired andcomposed of an Active EFBM and a Passive EFBM. The Active EFBM, which has a pull-in torque structureand fastens bolts by motor drive, is located on the PM.

The Passive EFBM is located on the EF. Once both

Active and Passive EFBMs are connected, the electrical power system, communication and tracking, andthermal control system will be simultaneously connected. Data and power transfer between the PM and EF will
be initiated.

The external view of the EFBM is shown in Figure 4.3.3-1.

Pull-in torque structure

Active EFBM

Passive EFBM

Figure 4.3.3-1 Exposed Facility Berthing Mechanism （EFBM）

4-22

Kibo HANDBOOK(b) Kibo’s Exposed Facility’s Equipment Exchange Unit (EF-EEU)
The EF Equipment Exchange Unit (EEU) is a mechanism that attaches the EF payloads to the EF.

Once apayload is attached to the EF by the EEU, the electrical power system (EPS), communication and tracking(C&T) and thermal control system (TCS) will be simultaneously connected and power supplies to the payloads,
data transactions, and thermal control become operable.
The EEU is composed of an active EEU known as the Exposed Facility Unit (EFU) and is located on theside of the EF. The passive EEU, known as the Payload Interface Unit (PIU), is located on the EF payloads.
Figure 4.3.3-2 shows the EEU (EFU and PIU) structures.
The EEU accommodates the EF payloads to be exchanged on orbit, thus several different types ofexperiments can be conducted compared to existing spacecrafts, and thus will flexibly meet the demands for
future technology development.
Kibo’s Robotic arm(JEMRMS Main Arm)

Grapple FixtureEF
Capture Latch

Power / fluid connectors
EF payload

EFU
PIU

Figure 4.3.3-2 EEU (EFU and PIU) Structures(c) Exposed Facility’s Orbital Replacement Units (ORUs) – Extravehicular Activity ORU(E-ORU) and Robot essential ORU (R-ORU)
Electrical Power System (EPS), Communications and Tracking (C&T) or Thermal Control System (TCS) are
critical systems for operating the EF, thus these system units are designed as ORUs.

In case of failure, theseunits can be exchanged on orbit. There are two types of ORUs on the EF. The first type of ORU is theExtravehicular Activity ORU (E-ORU), which is attached to the nadir side of the EF, and will be exchanged byextravehicular activities.

The second ORU type is Robot essential ORU (R-ORU) which is attached to thezenith side, and will be exchanged by JEMRMS, Kibo’s robotic arm.

4-23

4. Kibo System
ystem Components

4.4

Experiment Logistic Module-Exposed Section (ELM-ES)

4.4.1 Brief summary
Kibo’s Experiment Logistics Module-Exposed Section(ELM-ES) is a Kibo’s component, which carries Exposed
Facility (EF) payloads and EF system ORUs. The ELM-ES
will supply and transfer the system ORUs and the EF payloads
to the Kibo’s Exposed Facility (EF), as well as, store completed
EF payloads exchanged from the EF.

The ELM-ES will bedelivered to the ISS by space shuttles and attached to the EF.
After the ELM-ES is attached to the EF, the EF payloads on the
ELM-ES will be removed and transferred to the EF by using
Figure 4.4.1-1 ELM-ES location

the JEMRMS.
The used payloads will be retrieved from the EF using the
JEMRMS and stored on the ELM-ES.

Then, the ELM-ES will return to the ground aboard the space shuttles.

Figure 4.4.1-2 shows the ELM-ES operations concept. Table 4.4.1-1 shows the ELM-ES specifications.

Space shuttle
docked to the ISS

ELM-ES installed on /removed from EF

ISSSpace shuttle undockedfrom the ISS

Kibo
LaunchEF payloads exchanged
by JEMRMSEF
ELM-ES loaded in
the space shuttle’s
cargo bay

EF payloads installedon / removed from
ELM-ES

ELM-ES

Landing
ELM-ES prepared andchecked out

ELM-ES retrieved from thespace shuttle’s cargo bay
to ground overhaul facility
Exchange ofEF payloads

Figure 4.4.1-2 ELM-ES operation concept

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Kibo HANDBOOK

Table 4.4.1-1 ELM-ES Specifications
Specifications

Items
Structure type

Frame

Width

4.9 m

Height

2.2 m (including the height of the payloads)

Length

4.2 m

Mass (Dry weight)

1.2 t (excluding payloads)

Number of Payloads(loading style variable)

Three EF payloads
Two EF payloads + three R-ORUs
Two EF payloads + two E-ORUs

Electrical power supply

Max. 1.0 kW 120 V DC

Thermal control

Heater and thermal insulator

Life timeMore than 10 years

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4. Kibo System Components

4.4.2 Layout
ELM-ES configuration is shown in Figure 4.4.2-1.

Grapple Fixture

Payload Attachment Mechanism (PAM)

Payload Interface Unit
(PIU)
Trunnion

Grapple Fixture (x 2)
SSRMS or SRMS will grapple
here

Payload Interface Unit (PIU)
This mechanism isused to attach the
ELM-ES to the EF
or ELM-PS

4.9m
2.2m

Trunnions

EF payloads
This illustrates
when three EF
payloads areattached

4.2m

Payload Attachment Mechanism (PAM)
Trunnions (x 5)This mechanism is used to fasten the
ELM-ES to the space shuttle’s cargo bay

Figure 4.4.2-1 ELM-ES Configuration

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Kibo HANDBOOK

4.4.3 System Components of ELM-ES
The Experiment Logistics Module-Exposed Section (ELM-ES) is composed of the following subsystems.
•

Electrical Power System (EPS)•

Communication and Tracking (C&T)•

Thermal Control System (TCS)•

Structure•

Mechanical System

Details of the subsystems are as follows.
(1) Electrical Power System (EPS)The Electrical Power System (EPS) receives power from the space shuttles during the period from launch to
docking with the ISS, and distributes the power to ELM-ES system and Exposed Facility (EF) payloads.
Power will be supplied from the EF while the ELM-ES is operated on orbit.
(2) Communication and Tracking (C&T)
The Communication and Tracking (C&T) includes the Electronic Control Unit (ECU) that is installed on the
ELM-ES.

The ECU monitors the status of the ELM-ES, temperature of the EF payloads attached on the

ELM-ES, and the status of the Payload Attachment Mechanisms (PAMs) by communicating with the JEM
Control Processor (JCP) on the PM.

The ECU also controls the PAMs or temperature of the attached EF

payloads.
(3) Thermal Control System (TCS)The ELM-ES is entirely covered with thermal insulating materials in order to prevent the temperature of the
ELM-ES system from exceeding the operating temperature. In addition, to maintain the ELM-ES thermal
environment, heating devices are installed in the areas where thermal insulating material are not sufficient andthe temperature may exceed tolerable temperature ranges.

In addition, heating devices are installed in the EF

system ORU and EF payloads which are attached on the ELM-ES.
(4) Structure
The ELM-ES structure is designed to bear loads imposed during the space shuttle’s launch, ascent, ISS
attitude control and maneuver. The main sections of the ELM-ES are composed of aluminum alloy panels ina reticular pattern.

A mechanism called “Trunnion” fastens the ELM-ES to the space shuttle’s cargo bay.

The ELM-ES has five Trunnions.

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4. Kibo System Components(5) Mechanical System
The Mechanical System consists of Payload Attachment Mechanisms (PAMs), which locks the EF payloads
on to the ELM-ES, and a Payload Interface Unit (PIU), which connects the ELM-ES to the EF or the ELMPS.
For information on the PIU, please refer to Section 4.3.3 (5) (b).
(a) Payload Attachment Mechanism (PAM)
The Payload Attachment Mechanism (PAM) fastens the EF payloads to the ELM-ES while the ELM-ES isbeing launched to the ISS or returned to the ground aboard the space shuttle. In addition, this mechanism isused to install and remove EF payloads; for instances when these payloads need to be moved on orbit by using
the robotic arms.

In addition, the PAM has electrical connectors that provide heater power for keeping the EF

payloads temperature. Figure 4.4.3-1 shows an overview of the PAM.
Trunnion for the EF payload
This structure connects theEF payloads to the ELM-ES
Umbilical Connector Mechanism (UCM)
This mechanism enables power to besupplied to the EF payloads from the
ELM-ES

EF payload

Alignment Guide

Structure Latch Mechanism (SLM)
An EF payload will be grappled with four SLMs
Figure 4.4.3-1 Payload Attachment Mechanism (PAM)

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Kibo HANDBOOK

4.5

Japanese Experiment Module Remote Manipulator System(JEMRMS)

4.5.1 Brief Summary
Japanese Experiment Module Remote Manipulator System(JEMRMS), Kibo’s robotic arm, is a robotic manipulator
system intended for supporting experiments being conducted
on Kibo and/or for supporting Kibo’s maintenance tasks inspace. The JEMRMS will be the third remote manipulator
robotic arm system designed for space operations that Japan
will have flown into space. The JEMRMS follows Japan’s
Manipulator Flight Demonstration (MFD)* 1 in August 1997
and the Engineering Test Satellite VII (ETS-VII)* 2 , also
known as “KIKU No.7”, in November 1997. The JEMRMS

Figure 4.5.1-1 JEMRMS Locationis composed of two arms, the Main Arm (MA) and the Small
Fine Arm (SFA). The robotic control workstation, known as the JEMRMS Console, is used to operate the
JEMRMS.
Both the Main Arm (MA) and Small Fine Arm (SFA) have six joints and allow for similar movements withthe human arm. Inside the PM, the crew will control the JEMRMS, while watching images on the TV
monitor, located on the JEMRMS Console, which are taken from the cameras attached to the arm.
With these arms, the crew can conduct several tasks including exchanging EF payloads or EF system ORUs
that are located on the EF and ELM-ES.

The ten-meter-long Main Arm transfers (grapple and move) large

objects, and the two-meter-long Small Fine Arm is used for precise, delicate and fine-tuned operations.
The JEMRMS will be operated for more than ten years on orbit.
repairable design in case of failure.

Thus, the JEMRMS has exchangeable or

These arms can be repaired by intra-vehicular or extravehicular activities.

(Repair of the Main Arm will be conducted only by extravehicular activity.)
Table 4.5.1-1 shows the specifications for the JEMRMS (Main Arm and Small Fine Arm).

*1 The Manipulator Flight Demonstration (MFD) test, conducted on STS-85 in August 1997, used a test model(equivalent to the JEMRMS), that verified some of the JEMRMS functions.
*2 The Engineering Test Satellite VII (ETS-VII), "KIKU No.7", launched in November 1997, evaluated theremote-manipulation system and studied the basic techniques for using robotics in space.
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4. Kibo System
ystem Components

Table 4.5.1-1 JEMRMS (Main Arm and Small Fine Arm) Specifications
Specifications

Items
Main Arm (MA)

Small Fine Arm (SFA)

Structure type

Main Arm with attached Small Arm.

Degrees of freedom

6

6Both arms have 6 joints

Lengthm

102.2

Mass (weight)

kg

780

190

Handling Capacitykg

Max. 7,000

Max. 300

mm

Translation 50(+/-)

Translation 10(+/-)

degreeRotation 1(+/-)

Rotation 1(+/-)

60 (P/L: less than 600kg)

50 (P/L: less than 80kg)

30 (P/L: less than 3,000kg)

25 (P/L: less than300kg)

20 (P/L: less than 7,000kg)-

More than 30

More than 30

Positioning accuracy

Translation / rotation speed

Maximum tip force
Life time

4-30

mm/s

N

More than 10 years

Kibo HANDBOOK

4.5.2 Layout
Compositions of the Main Arm, Small Fine Arm and the JEMRMS Console are shown in Figure 4.5.2-1.

MA Joint 2

MA Joint 1
MA Boom 1

MA Joint 3
Rotary Motion
関節の動作

MA Elbow Vision
Equipment

4m
MA Boom 2
MA BaseMain Arm (MA)MA Joint 44m

MA Joint 6
MA Joint 5
SFA Grapple Fixture
SFA Electronics
2.2m
Fully
Deployed

SFA Shoulder Joint (Roll)
SFA Shoulder Joint (Pitch)
Boom 1SFA Elbow Joint (Pitch)
Boom 2
SFA Wrist Joint(Pitch)Boom1

MA Wrist Vision
Equipment

MA Boom 32m

MA End Effector

SFA TV Camera
Electronics
SFA Wrist Joint (Roll)
SFA Force / Torque Sensor
SFA Wrist TV Camera HeadSFA Tool
SFA Wrist
Joint (Yaw)

Small Fine Arm (SFA)
JEMRMS Console

Hold/Release Electronics (HREL)
Remote Interface Panel (RIP)
Translational Hand Controller (THC)

Caution and Warning (C&W) Panel
Audio Terminal Unit (ATU)
Television Monitor 1 (Display)
Camera Control Panel (CCP)

Robotics Laptop Terminal (RLT)

Television Monitor 2 (Display)

Avionics Air Assembly (AAA)

Rotational Hand Controller (RHC)

Power Distribution Box (PDB)

Management Data Processor (MDP)

Interface Panel

Arm Control Unit (ACU)

Figure 4.5.2-1 Main Arm (MA), Small Fine Arm (SFA) and JEMRMS Console
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4. Kibo System Components

4.5.3 System Components of JEMRMSThe JEMRMS is composed of the following subsystems.
•

Main Arm•

Small Fine Arm•

JEMRMS Console•

SFA Stowage Equipment•

JEMRMS Visual Equipment•

Hold and Release Mechanism

The following are details of the subsystems.

(1) Main Arm (MA)The Main Arm (MA) consists of MA Booms, MA Joints, MA Television Cameras (TV Cameras), MA
Camera Pan Tilt Unit (PTU), a light and the MA End Effector (grapple fixture) that grapples EF payloads.
There are three MA Booms, known as MA Boom 1, 2 and 3. Vision equipments (TV Cameras, PTU andlight) are attached to the MA Boom 2 and MA Boom 3.

The crew will control the JEMRMS while watching

the images, which are taken with the visual equipment, on the TV monitor located on the JEMRMS Console.
The Main Arm is primarily used for exchanging EF payloads (Standard payload envelope is planned to be
1.85m x 1.0m x 0.8m and weighing less than 500kg). The EF payload is grappled and moved by the
JEMRMS Main Arm End-Effector.
(2) Small Fine Arm (SFA)The Small Fine Arm (SFA) consists of SFA Electronics, SFA Booms, SFA Joints, end effectors called “Tool”,
and SFA TV Cameras.

The SFA is used when the SFA is grappled by the MA End Effector.

The SFA is primarily used for precise, delicate and fine-tuned tasks, which include exchanging the Orbital
Replacement Units (ORU) on the EF.

(ORU size is planned to be 0.62 x 0.42 x 0.41 m, and weighing 80 kg

max)
The SFA is designed with a compliance function that was validated on the Manipulator Flight Demonstration(MFD) during the STS-85 mission.

This feature allows the crew to easily operate the arm.

The SFA

compliance function utilizes the Force/Torque Sensor on the arm to sense when a target is touched, after which
the attitude of the arm is automatically controlled.

(3) JEMRMS Console
The JEMRMS Console is installed in the PM.

4-32

Crew will control the JEMRMS while watching the images,

Kibo HANDBOOK

which are taken with TV cameras, on the TV monitor located on the JEMRMS Console. The JEMRMS
Console is composed of a Management Data Processor (MDP), Laptop Computer, Hand Controllers, TV
Monitors and Hold/Release Electronics (HREL).

The MDP controls the JEMRMS systems bycommunicating with the JCP and the ISS Command and Control Multiplexer/Demultiplexer (C&C MDM) that
controls the ISS. The Laptop Computer and Hand Controllers (RHC and THC) are used to manipulate the
JEMRMS. The TV monitor displays images taken from the external cameras. The Hold/Release Electronics(HREL) is used to operate the Hold and Release Mechanism (please refer to (5)).
(4) Small Fine Arm (SFA) Stowage Equipment (SSE)The Small Fine Arm (SFA) Stowage Equipment (SSE) is a device to stow the SFA when the SFA is notin-use.

The SSE is installed on the EF.

The location of the SSE is shown in Figure 4.3.2-1.

(5) Hold and Release Mechanism (HRM)
While the Main Arm (MA) is launched to the ISS, the Hold and Release Mechanism (HRM) locks the Main
Arm to the PM.

After the PM is docked with the ISS, the crew will manipulate the HREL on the JEMRMS

Console to release the locked Main Arm from the HRM.

Afterward, the Main Arm will be deployed. The

HRM holds the Main Arm’s elbow, wrist and Boom3.

Figure 4.5.3-1 shows the position of the JEMRMS

locked to the PM. (Launch configuration).

Hold and Release
Mechanism (HRM)（Hidden below the arm）

HRM

JEMRMS base plate

Main Arm

Pressurized
Module (PM)HRM

Figure 4.5.3-1 JEMRMS locked to PM (Launch configuration)

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4. Kibo System Components

4.6Inter orbit Communication System (ICS)

4.6.1 Brief Summary
The Inter-orbit Communication System (ICS) is Japan’s
unique system for uplink/downlink data, images and voice data
between Kibo and the Mission Control Room at the TsukubaSpace Center (TKSC).

The ICS uses the 80-centimeter

diameter antenna that is installed on the EF and JAXA’s data
relay satellite, the Data Relay Test Satellite (DRTS), also known
as Kodama.
The ICS consists of the following two subsystems. The ICS
Pressurized Module (ICS-PM) subsystem located in the PMprovides the data communication functions. The ICS Exposed

Figure 4.6.1-1 ICS Location

Facility (ICS-EF) subsystem composed of an antenna installedon the EF.
Table 4.6.1-1 shows the ICS specifications.

Table 4.6.1-1 ICS Specifications
Specifications

Items
ICS-PM

ICS-EF

Size (m)2.0 x 1.0 x 0.9

1.1 x 0.8 x 2.0 (antenna retracted)
2.2 x 0.8 x 2.0 (antenna deployed)

Mass (weight) (kg)

330

310

Data rate /frequency /modulation
methodDownlink

50 Mbps / About 26 GHz / QPSK

Uplink

3 Mbps / About 23 GHz / BPSKDRTS Visible Window*

Total of 7.8 hours per day (DRTS currently consists of only one satellite)
Max. 40 min. per orbit*: The actual amount of time available for the DRTS communication may be shorter than the data in the abovetable since the above time is based on calculated estimations. In addition, DRTS communication time may
occasionally be allocated for other satellites.
QPSK (Quadrature Phase Shift Keying)
BPSK (Binary Phase Shift Keying)

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Kibo HANDBOOK

4.6.2 Layout
The ICS configuration is shown in Figure 4.6.2-1.

Grapple Fixture
JEMRMS willgrapples here
Stowagespace

Antenna（Retracted state）

ICS ORU(seven nits)

Earth sensor

Sun sensor
Space for HTV - Proximity
Communication System (PROX)ICS Pressurized Module (ICS-PM) subsystem

ICS Exposed Facility (ICS-EF) subsystem

Figure 4.6.2-1 Inter-orbit Communication System (ICS)

4-35

4. Kibo System Components

4.6.3 System Components of ICS
The following are details of the ICS subsystems, ICS-PM and ICS-EF components.
(1) ICS Pressurized Module (ICS-PM) subsystem
The ICS Pressurized Module (ICS-PM) subsystem is comprised of seven Orbital Replacement Units (ORUs).
Equipment or devices, such as the Base Band Data Processing Unit, are included in those ORUs.

These

ORUs are installed in the ICS rack and manages the ICS.
Primarily, the ICS-PM multiplexes the data of the Kibo’s system and experiment payloads for downlink from
Kibo to the ground, demultiplexes the data uplinked from the ground, and modulates the data before sending or
demodulates the data after receipt.
In addition, the ICS-PM has an automatic operation scheduling function where, commands are uplinked
from the ground in advance while the DRTS is in a communication window. The commands uplinked from theground are stored in the ICS-PM.

Each command is executed at the scheduled time.

This provides ICS

scheduled automatic operations. In addition, the ICS-PM has data recording function for later downloading to
the ground, whenever real time communication is not available.

(2) ICS Exposed Facility (ICS-EF) subsystems
The ICS Exposed Facility (ICS-EF) subsystem is comprised of several components, including Pointing
Mechanism, frequency converters, High-Power Amplifier, as well as, various sensors, including the Earthsensor, Sun sensor and Inertial Reference Unit.
Data downlinked from Kibo to the ground are relayed to the ICS-EF by the ICS-PM. The data is passed
through the frequency converter and power amplifier, and then, sent to the DRTS. Data uplinked from theground will pass through the frequency converter, converted to a low frequency, and then, relayed to the
ICS-PM.
In addition, the ICS antenna can automatically track the DRTS.

The ICS-EF determines the antenna’s

attitude based on data from the Earth sensor, Sun sensor and Inertial Reference Unit, while at the same time,
calculating the antenna’s directions based on the ISS and DRTS orbital positions The ICS-EF moves theantenna using the Antenna Pointing Mechanism by estimating the variability of the ICS attitude, and tracks the
DRTS automatically.

Further, while communicating with the DRTS, the ICS can calibrate the direction of the

DRTS by detecting any pointing error based on the high-frequency signals that the antenna receives.

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Kibo HANDBOOK

5. Kibo Operations

5-1

5. Kibo Operations

5.1

Launch and Flight Plan

Kibo’s components will be launched to the International Space Station (ISS) in three assembly flights asshown in Table 5.1-1 below.

Table 5.1-1 Kibo Launch Plan
ISS Assembly Flight*1

Kibo Component

Launch Target

1J/A

Experiment Logistics Module -Pressurized
Section (ELM-PS)

No earlier than February 14,
2008

1J

Pressurized Module (PM) with JEMRMS

No earlier than April 24, 2008

2J/A

Exposed Facility (EF) and Experiment
Logistics Module –Exposed Section (ELM-ES)

Japanese Fiscal Year (JFY)2008

After being attached to the ISS, every ISS component including Kibo’s component is and will be operated
according to the operations overview as shown in Table 5.1-2. Each country or organization that develops an
ISS component is responsible for operating their own components. Kibo operations are controlled from theMission Control Room in the Space Station Integration and Promotion Center (SSIPC) at the Tsukuba Space
Center (TKSC).

For details on the ground facilities and Kibo’s mission operations, please refer to Section 5.3.

Table 5.1-2 Operations of ISS Components after launch
Operations

Overview

Assembly Activation andCheckout

Assemble and activate, and verify whether the components areoperational

System Operations

Control and monitor the component’s operational status

Utilization(For Kibo) Conduct experiments in space using experiment payloads
onboard Kibo

MaintenanceExchange or repair failed or failing equipment

Supplies, which are necessary for maintaining or exchanging experiment payloads on-orbit, are delivered to
the ISS by the space shuttle, the H-II Transfer Vehicle (HTV) that is currently under development by Japan, theRussian Progress spacecraft, and the Automated Transfer Vehicle (ATV) developed by the European Space
agency (ESA). For information on the HTV, please refer to Chapter 8.

*1
For the ISS Assembly Flight Numbers, the letter "J" represents the mission relating to Japan's element, and"A" represents the mission relating to US elements. For example, "2J/A" is the second assembly flight which
delivers elements of Japan and US.

5-2

Kibo HANDBOOK

5.2

Kibo Assembly Sequence

5.2.1 1J/A Flight
During the 1 J/A Flight, the Experiment Logistics Module – Pressurized Section (ELM-PS) will be delivered
to the ISS.

The ELM-PS will be carrying Kibo’s system racks (JEM system racks) and payload racks.

Figure 5.2.1-1 shows the expected external view of the ISS after completion of the 1J/A Flight Mission.

Theplanned cargo bay layout during launch of the 1J/A Flight is shown in Figure 5.2.1-2.
After the docking of the space shuttle to the ISS, the following procedures will be used to attach the ELM-PS
to the ISS.

Figure 5.2.1-3 shows the procedures for attaching the ELM-PS to the ISS.

1.

Space shuttle docks to ISS

2.

Canadarm2 (ISS robotic arm) grapples the Orbiter Boom Sensor System (OBSS) and removes the
OBSS from the space shuttle’s cargo bay. (This will provide sufficient clearance for the safe removalof the ELM-PS from the space shuttle’s cargo bay.) (Figure 5.2.1-3 (1))

3.

The Shuttle Remote Manipulator System (SRMS) removes the ELM-PS from the space shuttle’s cargobay. (Figure 5.2.1-3 (1) to Figure 5.2.1-3 (3))

4.

The ELM-PS is attached, by the SRMS, to the Common Berthing Mechanism (CBM) at the zenith sideof Node 2. (Figure 5.2.1-3 (4))

5.

The CBM vestibule is pressurized. The crew connects the electrical power cables and air ducts
between the ELM-PS and Node 2.

6.

The ELM-PS is powered up and activated. The operational status of the ELM-PS is checked.

7.

The crew enters the ELM-PS from Node 2.

Eventually, the ELM-PS will be attached to the PM. However, since the ELM-PS will be launched before
the PM, the ELM-PS will temporarily be attached to the Node 2 until the PM is delivered to the ISS.

Note: The above procedures are based on NASA/JAXA coordination as of March 2007.

The aboveprocedures are subject to change dependent on possible changes.

5-3

5. Kibo Operations

Experiment Logistics Module –Pressurized Section (ELM-PS)

Node 2

Direction of travel
Direction towards earth
Figure 5.2.1-1 ISS after completion of 1J/A FlightExperiment Logistics Module –Pressurized Section (ELM-PS)

Orbiter Docking System (ODS)

SRMS
Canadian element

to space shuttle’s Middeck

Figure 5.2.1-2 Cargo bay layout during launch of 1J/A Flight (Image)

5-4

Kibo HANDBOOK

Canadarm2 (SSRMS)
Node 2OBSS
ELM-PS
SRMS(1)
Node 2

ELM-PS
SRMS
(2)

(3)

(4)
Figure 5.2.1-3 Procedures for connecting ELM-PS to ISS

5-5

5. Kibo Operations

5.2.2 1J Flight
During the 1J Flight, the Pressurized Module (PM) and Kibo’s Remote Manipulation System (JEMRMS)
will be delivered to the ISS.

Figure 5.2.2-1 shows the expected external view of the ISS after completion of

the 1J Flight. The Planned cargo bay layout during launch of 1J Flight is shown in Figure 5.2.2-2.

The

JEMRMS will be securely locked to the PM when the JEMRMS is launched to the ISS.
Following the space shuttle’s docking to the ISS, the PM will be berthed to the ISS according to thefollowing procedure.

Figure 5.2.2-3 shows the procedures for berthing of the PM to the ISS. Figure 5.2.2-3

shows the procedures for relocating the ELM-PS from the Node 2 to the PM.
1.

Space shuttle docks to ISS

2.

Canadarm2 removes the PM from the space shuttle’s cargo bay (Figure 5.2.2-3 (1) to Figure 5.2.2-3
(2))

3.
4.

The PM is berthed to the CBM on the port side of Node 2. (Figure 5.2.2-3 (3) to Figure 5.2.2-3 (4))
The CBM vestibule is pressurized. The crew connect electrical power cables and other cables orlines.

5.

The PM is powered up. The operational status of the PM system is checked through the activation of
one (B string) of the two strings (A & B strings) of the PM system.

6.

The air conditioning and air ventilations are activated.

7.

Three JEM system racks and JEMRMS Console, which were launched during the 1J/A Flight while

The crew enters the PM.

being stored in the ELM-PS, are transferred to the PM through the Node 2.
8.

The “A” string (second string) of the PM system is activated. The system’s operational status (twostrings activated) is checked.

9.

The JEMRMS Console is activated.

The JEMRMS is deployed.

10.

The other racks are transferred from the ELM-PS to the PM.

11.

After closing the ELM-PS hatches, the ELM-PS is deactivated. And the Canadarm2 removes the
ELM-PS from the Node 2 CBM and relocate to the PM CBM. (Figure 5.2.2-4 (1) to Figure 5.2.2-4 (4))

12.

The ELM-PS system is reactivated, and the crew enters the module.

Note: The above procedures are based on NASA/JAXA coordination as of March 2007.
procedures are subject to change dependent on possible changes.

5-6

The above

Kibo HANDBOOK

ELM-PSJEMRMS
PM

Node 2

Direction of travel

Direction towards earth
Figure 5.2.2-1 ISS after 1J Flight is completed

PM

JEMRMS
Main Arm

Orbiter Docking System
(ODS)

PM
SRMS
to space shuttle’s Middeck
Configuration of the
JEMRMS during launch
Figure 5.2.2-2 Cargo bay layout during launch of 1J Flight (Image)

5-7

5. Kibo Operations

ELM-PS
Node 2

Canadarm2 (SSRMS)
PM

(1)

PM

(2)

JEMRMS(3)

JEMRMS(4)
Figure 5.2.2-3 Procedures for attaching PM to ISS

5-8

Kibo HANDBOOK

Canadarm2 (SSRMS)
ELM-PSJEMRMS

Node 2(1)

PM

ELM-PS

(2)

(3)

(4)
Figure 5.2.2-4 Procedures for relocating ELM-PS (space shuttle is not included)

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5. Kibo Operations

5.2.3 2J/A Flight
During the 2J/A Flight, the Exposed Facility (EF) and the Experiment Logistics Module – Exposed Section(ELM-ES) will be launched to the ISS. Figure 5.2.3-1 shows the expected external view of the ISS after
completion of the 2J/A Flight. The Planned cargo bay layout during launch of the 2J/A Flight is shown in
Figure 5.2.3-2.
After the docking of the space shuttle to the ISS, the EF and ELM-ES will be attached to the ISS according
to the following procedures.

The procedures for attaching the EF and ELM-ES to the ISS are shown in Figure

5.2.3-3.
1.

Space shuttle docks to the ISS

2.

Canadarm2 removes the EF from the space shuttle’s cargo bay (Figure 5.2.3-3 (1) to Figure 5.2.3-3
(2))

3.

The EF is attached to the Exposed Facility Berthing Mechanism (EFBM) on the PM by the Canadarm2

4.

The EF is powered up and activated The EF’s operational status is checked.

5.

The SRMS removes the ELM-ES from the space shuttle’s cargo bay (Figure 5.2.3-3)

6.

The ELM-ES is handed over from the SRMS to the Canadarm2 (Figure 5.2.3-3 (6))

7.

The ELM-ES is attached to the EF by the Canadarm2 (Figure 5.2.3-3 (7) to Figure 5.2.3-3 (8))

8.

The ELM-ES is powered up and activated The ELM-ES’s operational status is checked.

9.

The payloads carried on the ELM-ES during launch are relocated to the EF by the JEMRMS(Figure 5.2.3-3 (3) to Figure 5.2.3-3 (4))

Note: The above procedures are based on NASA/JAXA coordination as of March 2007. The above procedures
are subject to change dependent on possible changes.

5-10Kibo HANDBOOK

ELM-PSJEMRMSPM
ELM-ESEF

Direction of travel
Direction towards earth

Figure 5.2.3-1 ISS after completion of 2J/A Flight (Illustration provided by NASA)

ELM-ESEF
Orbiter Docking System (ODS)
US cargo

SRMS

to the space shuttle’s Middeck

Figure 5.2.3-2 2J/A Cargo bay layout during launch of 2J/A Flight (Image)

5-11

5. Kibo Operations

Canadarm2 (SSRMS)
PM
EF

SRMS
ELM-ES(5)(1)

Canadarm2 (SSRMS)
EF

SRMS
ELM-ES

(2)

(6)

(3)

(7)

(4)

(8)
Figure 5.2.3-3 Procedures for connecting EF and ELM-ES to ISS

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Kibo HANDBOOK

5.3

Kibo Operations Control

The International Space Station (ISS) program, which includes the construction, assembly, and utilization of
the ISS, has been promoted by the United States (US), Japan, Canada, 11 European countries that belong to theEuropean Space Agency (ESA), and Russia.

Overall operations of the ISS are coordinated by the US.

Each

International Partner is responsible for operating each country’s own ISS component including ISS
components/modules/segments, ISS payloads or equipment.
Communications between the ISS and the International Partners are conducted through the Tracking andData Relay Satellite (TDRS) by way of NASA Johnson Space Center (JSC) and White Sands Ground Station.
Japan will alternatively use JAXA’s Data Relay Test Satellite (DRTS), known as Kodama, for communicatingwith Kibo.

Russia communicates with the ISS only when direct communications with the ISS are permitted,

and uses the TDRS as a backup communication method.
Figure 5.3-1 shows the conceptual diagram for the ISS operations.

Tracking andData Relay
Satellite

JAXA Data
Relay Test
Satellite
Space Shuttle
Automated
Transfer
Vehicle (ATV)

NASA White Sands
Ground Station

Soyuz /
Progress

H-II Transfer
Vehicle (HTV)

Russian Space
Agency: Baikonur
Cosmodrome
NASA KSC:
Kennedy Space
Center
Payload Operations
Integration Center

Tanegashima
Space Center(TNSC)

ESA: Kourou, French
Guiana

JAXA: Tsukuba Space
Center (TSKC),
Tsukuba Japan
NASA JSC: Mission
Control Center

Canadian Space Agency
Saint-Hubert, Quebec

ESA:
Columbus Control Centre

Russian Space Agency: Mission
Control Center-Moscow

Each organization operate their own components / modules / segments from their own Control Centers

Figure 5.3-1 ISS Operations Conceptual Diagram

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5. Kibo Operations

After all of the Kibo components are assembled and attached to the ISS, Japan’s full-scale experiments inspace will commence.
Experiments, which will be performed in or on Kibo, are operated and controlled from the Space Station
Operations Facility (SSOF) in the Space Station Integration and Promotion Center (SSIPC) at Tsukuba Space
Center (TKSC) in collaboration with the Space Station Control Center (SSCC) at NASA’s Johnson Space
Center (JSC), where the overall operations of the International Space Station (ISS) are controlled and managed.
Overview of the SSIPC that consists of several related ground facilities is shown in Figure 5.3-1.
The SSOF is responsible for Kibo’s operations control, including (1) controlling and monitoring Kibo’s
ongoing systems, (2) operating Japan’s experiment payloads onboard Kibo, (3) implementing operations plans,and (4) supporting launch site processing.
Kibo’s operations systems are categorized by the following systems: (a) Operations and Utilization Planning
System, (b) Operations Control System, (c) Crew Operations Training System, (d) Engineering Support System,(e) Logistics and Maintenance Operations Management System and (f) Operations Data Network System.
Overview of the Operations Control System (OCS), which is the most critical system for Kibo operations, isshown in Figure 5.3-2.

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Kibo HANDBOOK

ESA
Columbus Control Center(Col-CC)

NASA

This center is responsible forthe operations of Columbus
laboratory.

Payload Operations andIntegration Center(POIC)FSA
Mission Control Center –Moscow (MCC-M)
This center controls andoperates the Russian segmentof the ISS.

This center is located at the
MSFC and integrates thescientific payload operations
aboard the ISS

NASA
Space Station Control
Center (SSCC)
This center is located at the JSC
and controls and operates theoverall ISS systems. This centeris responsible for the safety of the
ISS and the ISS flight crew.
Space Station Test Building

Communication Interface for payload operations
Communication Interface for system operations
JAXASpace Station Integration
and Promotion Center(SSIPC)This operations control complex is located at the TKSC. The SSIPC
controls and manages Kibo operations.

Tests on Kibo’s integrated systems are conducted
here. Operational status of the systems, interfaces,
and applicability of the payloads are tested here.
Engineering supports for Kibo’s on-orbit operations
will be provided.

Space Station Operations Facility (SSOF)
Responsible for controlling Kibo
operations in cooperation with SSCC
and POIC. At the SSOF, operations of
Kibo’s system and payload are
conducted and Kibo operations plans areprepared. The operability and launch
feasibility are studied here.

Space Experiment Laboratory (SEL)

Responsible for 1) development of technologies forexperiments in space, 2) supporting users
developed the Kibo experiments, 3) preparing Kibo
experiment operations program, and 4) supporting
the experiment data analysis.
Astronaut Training Facility (ATF)

Responsible for crew selection, training, and healthcare. Research for developing technologies or
methods for the crew selection, training and healthcare are conducted.
Weightless Environment Test Building (WET)

Weightless environment simulator provides anartificial microgravity environment by waterbuoyancy,. Design verification tests on Kibo’s
components are conducted here. Kibo maintenanceor Kibo’s ORU replacement procedures are prepared
and aastronaut’s basic training is conducted here.

Mission Control Room Responsible for real-time Kibo operation
on a 24-hour basis. Ongoing Kibo
(MCR)

systems, monitoring health and status of
Kibo’s payloads, sending commands, andreal-time operational planning aremanaged here.

User Operations
Area (UOA)

Operations Planning
Room

Distributs status of Japan’s experiments
and experiment data to the respective
users. Users who are responsible for theexperiment’s operations, can monitor,
control, and analyze the experiment’s data.
The users can support and conduct
on-orbit experiments from the ground.
Plans on-orbit and ground operations
based on the power distribution, crew’
resources, and data transmission capacity.
If the operation plands need to bechanged, adjustments will be conductedin tandem with the Mission Control
Room, the User Operations Area andNASA.
Functions are similar to the MCR’s. The

Operations Rehearsal ORR provides trainings for flightRoom(ORR)
controllers, conducts integrated rehearsals,and conducts joint integrated simulations
with NASA.

Figure 5.3-1 Space Station Integration and Promotion Center (SSIPC) Ground facilities
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5. Kibo Operations

Operations Control System (OCS)

Along with the SSCC operations control, the Operations Control
System (OCS), which is a core component of the SSIPC, controls
and monitors Kibo’s systems and the status of Japan’s andinternational partners experiment payloads aboard Kibo. The OCS
also conducts data management and provides user support.
In addition, the OCS prepares and manages the operations plans for
Kibo’s systems and payload operations within the available
resources that are allotted to Kibo in cooperation with the
SSCC/POIC that is responsible for integrating the overall ISS
system and payload operations.

Monitoring Control subsystem

Experiment Operations
Support subsystem

Strategic and Tactical Planningsubsystem

Operations Data Management
subsystem

Operations Data Network
subsystem

Common Equipment subsystem

The Monitoring Control subsystem is responsible for: (1) theprocessing and display of telemetry data required for the realtime monitoring and control of Kibo’s onboard payloads(Japan’s and international partners’), (2) control andverification of commands that are transmitted, (3) operations
history data archive, (4) transmission, control and/or
verification of on-orbit operations files, and (4) fault
detection, isolation, and recovery.
This subsystem provides several types of supports for users
who operate their experiments on or in Kibo including: (1)distribution and display of experiment data and ancillarydata that is downlinked from Kibo to the users, (2) input andtransmission of commands from the users, and (3)interfacing the uses’ provided equipment for standard
interfacing.
This planning subsystem manages: (1) planning andpreparation of Kibo’s systems or payloads, (2) ground
operations planning for Kibo on-orbit operations, and (3)revising or modifying ground operations plans, and (4) data
management for operations planning.
This data management subsystem manages: (1) operations
data of Kibo’s system and Kibo’s on-board payloads (bothJapan’s and international partners’), (2) experiment data forJapan’s experiment payloads, (3) accumulation of ancillarydata and statistical processing, (4) data processing,long-term storage management and distribution of data, and(5) data search management.
This network subsystem manages: (1) the equipment forinterfacing between NASA and Kibo’s ICS and (2) OCS
network operations.
This subsystem provides equipment and information that arecommon to either the Kibo’s flight controllers or Kibo’s
operations staff. This subsystem is composed of: (1) audio
and video communication equipment, (2) large displays, (3)standard time provision equipment, and (4) consoles at the
MCR.

Figure 5.3-2 Kibo Operations Control System

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Kibo HANDBOOK

5.3.1 Orbital Interface (between the ground to/from Kibo)
There are two types of communication links between Tsukuba Space Center (TKSC) and Kibo for data
uplink/downlink.

In general, Kibo operations are conducted by using NASA’s communication link.

(1) NASA Data Communication Link
This link provides the data communication interface between Kibo and TKSC through NASA’s Tracking andData Relay Satellite System (TDRSS).

Commands or data from the TKSC are first received at NASA JSC

and White Sands Ground Station and forwarded to Kibo through the TDRSS and the ISS. This link utilizes
two types of communication bands. Each band relays different types of data.
(a) S band
The S band relays commands (power-on and power-off commands to Kibo), telemetry data (Kibo’s healthstatus data) and voice.
(b) Ku band
The Ku band relays larger bandwidth data that is acquired at Kibo to the ground, including, experiment dataor video images.
(2) JAXA Data Communication Link
This link provides a direct interface between the TKSC and Kibo through JAXA’s Data and Relay Test
Satellite (DRTS).

The data sent from TKSC are relayed through the DRTS and received by the Inter-orbit

Communication System (ICS) installed on Kibo.

This link uses the Ka band. The types of the data to be

uplink/downlink are nearly the same as the types of data for NASA’s communication link, including,commands, telemetry, voice, video images, experiment data and experiment images.

JAXA’s Data

Communication Link is also known as the “ICS link”.

5-175. Kibo Operations

5.3.2 Ground Interface (between TKSC and NASA Mission Control Centers)
There are two types of ground links between JAXA and NASA.

Both links between the two control centers

are via leased lines/channels.
(1) Link between the Tsukuba Space Center (TKSC) and NASA’s Johnson Space Center (JSC)
This link interfaces the Tsukuba Space Center (TKSC) with NASA’s Johnson Space Center (JSC).
Commands (power-on and power-off commands to Kibo), telemetry data (Kibo’s health status data), voice andvideo images are sent and received.
(2) Link between Tsukuba Space Center (TKSC) and NASA’s Marshall Space Flight Center(MSFC)
This link interfaces Kibo with the TKSC through the Huntsville Operations Support Center (HOSC) at
NASA’s Marshall Space Flight Center (MSFC).

Experiment data downlinked from Kibo is sent to the TKSC.

Figure 5.3-3 shows a conceptual diagram of the orbital/ground interfaces for Kibo operations.

5-18

S-bandKa-bandKu-band

TDRS

DRTS
NASA Data
Communication Link

UnitedStatesJAXA Data
Communication Link

S-band• •Downlink: ISS/Kibo telemetry data, voice• •Uplink: ISS/Kibo commands, voice

Ku-band
NASA
White
Sands
GroundStation• •Downlink (50Mbps): Experiment data, video

Ka-band• Downlink (50Mbps): Kibo telemetry data,
voice, video images, experiment data
• Uplink (3Mbps): Kibo command, voice,data file for payloads

Tsukuba

images

DRTS
GroundStation
SSIPC

NASA Johnson Space Center (JSC)
Mission Control Center

experiment data

Operations
Control System
（OCS）

5-19

Figure 5.3-3 Conceptual Diagram of orbital/ground communication interfaces for Kibo Operations

Kibo HANDBOOK

NASA Marshall Space Flight Center(MSFC)
Huntsville Operations Support
Center (HOSC)

Kibo telemetry data / commands,
voice, video images(Space Station Integration andPromotion Center）

5. Kibo Operations

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Kibo HANDBOOK

6. Kibo Utilization

6-1

6. Kibo Utilization

6.1

Summary

400 km above the earth, construction and assembly of the International Space Station (ISS) is ongoing.
Aboard the ISS, various scientific experiments are currently or will be conducted by utilizing an environment
unique to space. The space environment is characterized by microgravity, space radiation, vast views, very
high vacuum and an abundant source of solar energy. These environmental conditions are completely different
and difficult to fully duplicate from what is available on earth.

The results from these experiments are

expected to enhance the capabilities of our 21st century industry and will also be used for the betterment ofmankind.

On Kibo, several types of scientific experiments that will use Kibo’s pressurized and exposed

facilities are planned.

This chapter describes Kibo’s space experiment environment and the experiment

payloads planned to be used inside or outside of Kibo, and introduces Kibo’s utilization plans during Kibo’s
initial utilization phase.

6.2

Environment

6.2.1 Microgravity
Every object orbiting the earth, like the ISS, is in a state of continuous free-fall towards the center of theearth.

Under these conditions, these orbiting objects are under the influence of microgravity or near zerogravity conditions.

On-board the ISS, several factors including atmospheric drag, gravity gradient (tidal

force), crew activities, and the station’s solar array rotations may affect the ISS gravitational environment.
However, microgravity is still only about 10-6 to 10-4 g of that on earth, and thus can be utilized for long-term
research on-board the ISS.

(Note: 1 g is a measurement expressed as an object’s nominal acceleration at

2

9.80665 m/s due to gravity on Earth at sea level and known as G-force or G-load).

Utilizing thismicrogravity environment, several types of experiments or studies on the effects of gravity on life are underconsideration for Kibo’s future experiments.

6.2.2 Line of Sight and field of view from the ISS
The line of sight from certain sites of the ISS can be blocked by the ISS structural components, including thepressurized modules or rotating solar arrays.

The field of view or what can be seen depends on location andthe direction of the line of sight.
Since Kibo will be located at the front of the ISS (ISS’s direction of travel), a relatively wider field of view
can be seen from the Exposed Facility (EF) experiment payloads site attached to the front (ISS’s direction of
travel) of the Kibo’s Exposed Facility (EF).
The field of view from the EF experiment payload #1, that will be attached to the EF, was estimated by afield of view analysis.

Figure 6.2.2-1 shows an estimated field of view from the EF experiment payload #1.

Mission planning for an experiment, which will be conducted using an EF experiment payload on the EF and aview is of importance, will need to factor in the results of the field of view analysis.

6-2

Kibo HANDBOOK

to Node 2

EF

Direction of travel

Zenith direction
EF experiment
payload #1
Direction of earth center Direction of travelEF
SFA Storage Equipment
PMEF payload
JEMRMSTV camera,
lights, PTU

Radiator

ELM-PS
Solar Array

Solar Array

Earth

Solar Array

Solar Array

ICS

30

30

Radiator

Radiator
60 Soyuz spacecraft

60

Node 390

90

Direction of travel

Note: The rotation envelopes for the station’s solar arrays and radiators areindicated. Both figures illustrate a hemispheric view.
SFA: Small Fine Arm
PTU: Pan Tilt Unit

Figure 6.2.2-1 Estimated field of view for EF experiment payload #1 site on EF

6.2.3 Background Atmosphere
The degree of vacuum at the ISS orbit (at an altitude of 400 km) is approximately 10-5 Pa.

Water dumps

from the ISS or water dumps from the space shuttle being docked to the ISS could affect this vacuum
environment.

In addition, the atmospheric density of the environment surrounding the ISS may varydepending on solar and geomagnetic activities.
At the altitude where the ISS orbits, a significant amount of atomic oxygen exists.
formed from dissociated oxygen molecules exposed to ultraviolet (UV) radiation.

The atomic oxygen is

Atomic oxygen is known tooxidize, erode and contaminate spacecraft materials on orbit.
Excluding water dumps from the ISS, there are many contamination sources in Kibo’s surrounding
environment, including out-gassing from the ISS components (gasses emitted from organic materials) or
thruster burns by the space shuttles or other spacecrafts.

When planning experiments for the EF, atmosphericfactors will need to be taken into consideration.

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6. Kibo Utilization

6.2.4 Space Radiation
The environment where the ISS orbits are comprised of cosmic radiations, including a radiation belt (Van
Allen belts) consisting of particles captured by the earth's magnetic field, solar flare particles (solar protons)
generated by solar activities, and galactic cosmic rays that originates from outside the solar system.

The

environment outside and inside the ISS can be affected by cosmic radiations impacted with the ISS structuralcomponents or the atmosphere, which in turns generates secondary radiations.

The cosmic radiation may

cause malfunctions with the ISS equipment, which is known as a “single event effect”. Additionally, thecosmic radiation may adversely affect the health of the ISS crew. Therefore, observations and researches on
cosmic radiation have become increasingly important.

6.2.5 Thermal Environment
The ISS and Kibo’s thermal environments are complex and composed of direct solar exposure, sun lightreflected from the earth (albedo), infrared radiation and cosmic background radiation.

The temperaturesurrounding the ISS and Kibo ranges from -150 °C to +120 °C (degree Celsius), depending on the shaded or
un-shaded area of the ISS or Kibo. The thermal environment can also vary depending on the relative position of
the sun and the ISS orbital plane.
Before designing an EF experiment payload, as well as Kibo’s components, verification that EF experiment
payload itself is strong enough to endure the severe thermal conditions of space including interruptions orreflections attributed to ISS’s surrounding components should be done.

6.2.6 Micrometeoroid and Space Debris
In space, micrometeoroids which are believed to originate from comets or asteroids and space debris, which
originate from artificial satellites, spacecraft components, old launch vehicles or orbit burns of solid rocket fuel,are orbiting the earth.

These orbiting micrometeoroids and space debris may possibly impact the ISS or Kibo.

Under an altitude of 2,000 km above the earth, more than 10,000 pieces of space debris, the size of 10 cm or
greater, have been confirmed.

If a piece of debris that may impact the ISS is predicted or confirmed, a debris

avoidance maneuver that alters the ISS orbital altitude will be implemented.

In addition, debris shields ordebris bumpers are installed around the outside surface of the PM and ELM-PS for protecting thesecomponents’ structural bodies from possible space debris impacts.

Moreover, these components are designed

not to break apart even if a hole is made in the component’s surfaces from debris impacts. The safety of the ISS
crew can be ensured by evacuating the crew to a different ISS module, and then, closing and securing thehatches of the affected module.

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Kibo HANDBOOK

6.3

Experiment Payloads

6.3.1 Experiment Payloads for Kibo’s Pressurized Module (PM)(1) Cell Biology Experiment Facility (CBEF)
The Cell Biology Experiment Facility (CBEF) is equipped with an incubation environment where thetemperature, humidity and carbon dioxide (CO2) concentration can be controlled. The basic phenomena of lifein space can be studied through the use of cells from animals, plants, microorganisms, etc. A centrifuge will be
used to generate an artificial gravity environment, thus experiments in both a microgravity and artificial gravity
environment can be conducted in Kibo.
The culture chamber will be set in a “canister” and installed within the CBEF. Through a utility connector
inside the CBEF, the canister can receive power, command input, sensor output, video output. These utilities
will provide support for an efficient experimental environment. In addition, by placing the canister in the
Clean Bench (CB), the ISS crew can, by using the Clean Bench’s glove box, directly handle the samples inside
the canister.
Figure 6.3.1-1 shows an overview of the CBEF. Table 6.3.1-1 shows the CBEF specifications.
The CBEF will be installed in the “SAIBO” experiment payload rack in Kibo’s Pressurized Module (PM).
The Clean Bench (CB) will also be installed in the “SAIBO” rack.

The CBEF will be operated at the location

as shown in Figure 6.3.1-2.

Microgravity Compartment(μG incubator unit)

Centrifuge
1G Compartment(1 G incubator unit)

Figure 6.3.1-1 CBEF

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6. Kibo Utilization

Table 6.3.1-1 CBEF Specifications
Items

Specifications

Temperature setting

15 to 40 °C

Humidity setting

Max. 80 ± 10 % RH

CO2 concentration setting

0 to 10 % (0.1 % step)

Gravity setting

0.05 to 2 G (at 112.5 mm radius point)

Utility

Power: DC+5V, +12V, ±15V
Sensor output: 0 to 5 V
Command: 1 bit
Video output

SAIBO Rack
（Location Code: A2 in PM）

Figure 6.3.1-2 Location of SAIBO Rack in Pressurized Module (PM)6-6

Kibo HANDBOOK(2) Clean Bench (CB)The Clean Bench (CB) will provide an aseptic glove-box operating compartment called “Operation Chamber(OC)” where germfree operations can be conducted. Life Science and biotechnological experiments can be
performed on-board Kibo through the use of the CB. The CB has a Disinfection Chamber (DC), which isseparated from the OC. This separation prevents the OC from becoming contaminated by microorganisms
while transferring samples or equipment.

In addition, the OC is equipped with ultraviolet lamps forsterilization and High Efficiency Particle Air (HEPA) Filters.
suspended in the air.

These filters eliminate particles that areConsequently, germfree experiments can be conducted by the Clean Bench.

The frontof the OC is comprised of transparent materials so as to provide good views of the inside of the OC. The ISS
crew will be able to conduct germfree experiments by directly monitoring the insides of the OC. In addition,
to support the experiments, a phase-contrast/fluorescent microscope and a monitor camera are installed in the
CB.
Figure 6.3.1-3 shows an overview of the CB. Table 6.3.1-2 shows the CB’s specifications.
The CB will be installed in the “SAIBO” experiment payload rack in the PM together with the CBEF, andwill be operated at the location as shown in Figure 6.3.1-2.

Power Unit
Liquid Crystal Display(LCD) Monitor

Operation
Chamber
Astronaut Furukawa using the OC

Joystick

Glove

Control Unit
Microscope
Disinfection
Chamber (DC)

Figure 6.3.1-3 CB

6-7

6. Kibo Utilization

Table 6.3.1-2 CB Specifications
Items

6-8

Specifications

Cubic Volume

Operation Chamber: 52 L
Disinfection Chamber: 14 L

Environment Control

Air duct filtering system: particle are eliminated by HEPA filters (two)Sterilization method: UV-germicidal lamp
Temperature setting: 20 to 38 °C

Equipment installed

Phase-contrast/fluorescent microscope (objective lens: x4, x10, x20, x40
magnification)

Utility

Power: DC+5V, +12V, ±15V
Video output

Kibo HANDBOOK(3) Fluid Physics Experiment Facility (FPEF)
The Fluid Physics Experiment Facility (FPEF) is an experiment facility for conducting fluid physics
experiments at ambient temperature and in a microgravity environment.

In space or in a microgravity

environment, the effects from thermal convection are lower than that on earth. Thus, Marangoni convection(convection attributed to differences between surface tensions) is significant. The primal objective of the
FPEF is to investigate the Marangoni convection in a space environment which affects such as thesemiconductor single crystal growth experiment.

The results from investigating the Marangoni convection

are expected to facilitate control of convections that are currently hampering industrial applications. The
results, by deepening our understanding of the Marangoni convection, may be applied to methodologies foreliminating foam or bubbles in fluids.
As part of the FPEF standard functions, the FPEF has the following features for observing, measuring ormonitoring: (1) two-dimensional (2D) and three-dimensional (3D) flow field observation for observing flow
distributions, (2) surface temperature measurement, (3) velocity profile measurement using ultrasound, and (4)surface flow velocity monitoring.

Currently, the “Liquid Bridge” application is being planned for the FPEF

for investigating the Marangoni convection. In addition, several Experiment Cells are being developed to meetseveral diverse experiment purposes. Figure 6.3.1-4 shows an overview of the FPEF. Table 6.3.1-3 shows the
FPEF specifications.
The FPEF will be installed in the “RYUTAI” experiment payload rack inside the PM. The FPEF will be
operated at the location as shown in Figure 6.3.1-5.

Figure 6.3.1-4 FPEF

6-9

6. Kibo Utilization

Table 6.3.1-3 FPEF Specifications
Items

Specifications

Liquid Bridge Formation

Sample: Silicone Oil
Diameter: 30 mm, 50 mm
Length: 65 mm maximum

Temperature Control

Heating Disk: 90 ℃ (degrees Celsius) maximum
Cooling Disk: 5 ℃ (degrees Celsius) minimum

3D Flow Field Observation

CCD camera (effective pixel: 768 (H) x 494 (V))

Liquid Bridge Overview
Observation

CCD camera (effective pixel: 768 (H) x 494 (V))

Surface Temperature
Distribution Measurement

Infrared Imager*spectral response: 8 to 14 μm*measurement range: 0 to 100 °C

Surface Flow Velocity
Measurement

Photochromic dye actuation with nitrogen gas laser(two points irradiation)

Utility

Power source: 12 ± 2V, 4A (Max), 1ch
24 ± 2V, 3.5A (Max), 3ch± 15V ± 0.5V, 0.8A (Max)/ch, 1ch
Analog Input: 0 to 10V, 8ch
Digital Input: 8ch
Digital Output: 8ch
Gas supply: Argon (Ar) gas

RYUTAI Rack
（Location Code: A3 in PM）

Figure 6.3.1-5 Location of RYUTAI Rack

6-10

Kibo HANDBOOK(4) Solution/Protein Crystal Growth Facility (SPCF)
The Solution/Protein Crystal Growth Facility (SPCF) is an experiment facility for conducting basic
researches related to crystal growth in various solutions or proteins in a space environment. The SPCF
consists of the Solution Crystallization Observation Facility (SCOF) and the Protein Crystallization Research
Facility (PCRF). The SCOF uses cell cartridges for growing solution crystals. In-situ observations can be
performed while the crystals are growing by controlling the temperature and pressure in the cell cartridge.

A

Mach-Zehnder (MZ) Interference Microscope and a Dynamic Light Scattering unit are mounted in the SCOF
for crystal growth observation, crystal surface observation, liquid-phase temperature/concentration distribution
measurements, and/or particle size distribution measurements.

The second SPCF facility, the PCRF, is a

facility for growing large and high-quality protein crystals for ground structural analyses.
The SCOF and PCRF can be operated separately as independent facilities.
PCRF are shown in Figure 6.3.1-6 and Figure 6.3.1-7, respectively.

The overviews of the SCOF and

The specifications for the SCOF and

PCRF are shown in Table 6.3.1-4 and Table 6.3.1-5, respectively.
The SPCF will be installed in the “RYUTAI Rack” in the PM together with the FPEF, and will be operated at
the location as shown in Figure 6.3.1-5.
Mach-Zehnder (MZ)
Interference MicroscopeElectronics Controller

Amplitude-Modulation
Microscope
Polarizing Microscope
Bright-Field Microscope

Laser Light

Test specimen(cell cartridge)

Optical Window

Cell Driving System
Gas Port(SCOF Inside)(SCOF Front)
Figure 6.3.1-6 SCOF

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6. Kibo
bo Utilization

CCD Camera

Cell Tray
Cell Cartridge

Figure 6.3.1-7 PCRF

Table 6.3.1-4 SCOF Specifications
Items

Specifications

Mach-Zehnder (MZ)
Interference Microscope

Magnification: x2, x4
Light source: LD and solid-state laser diode (λ = 532 nm, 780 nm)
Phase resolution: More than 0.2 λAmplitude-Modulation
Microscope

Magnification: x2, x4
Light source: LED (λ = 600 nm)
Phase resolution: More than 0.2 λUser Interface

Temperature Control: Peltier element
Temperature Measurement: Thermister (standard or high precision
measurement), Thermocouple (K, J type)

Options

Dynamic Light Scattering
Fluorescence Decay
Reflecting Spectrophotometer
Absorption Photometer

Table 6.3.1-5 PCRF Specifications
Items

Specifications

Cell Cartridge

Number of cartridges: 6
Temperature control: 0 to 35 °C
Harvesting method: Vapor Diffusion, Batch, Membrane, Liquid-liquid diffusion

Observation systems

Camera: 1/2 CCD camera
Light source: LED
Resolution: More than 40 μm

6-12

Kibo HANDBOOK(5) Gradient Heating Furnace (GHF)
The Gradient Heating Furnace (GHF) is a multipurpose electrical furnace for conducting experiments related
to vapor deposition and crystal growth of semiconductor materials.

The GHF is comprised of a furnace, aControl Equipment, and a Sample Cartridge Automatic Exchange Mechanism (SCAM) with a controller.
Samples will be heated or cooled in the Furnace Section. The Control Equipment will receive commands
from the ground to control the experiments while relaying data to the data communication system of Kibo.
The SCAM can accommodate up to 15 samples and can automatically exchange the samples.
heating units in the Furnace Section.

There are three

Each heating unit can independently be controlled or maneuvered. Thus,

different temperature profiles can be set for conducting various experiments. When running the experimentsin the GHF, fusion and unidirectional solidification of the samples can be conducted. The GHF overview isshown in Figure 6.3.1-8.

The GHF specifications are shown in Table 6.3.1-6.

The GHF will be installed in the “KOBAIRO” experiment payload rack, with power or coolant water being
supplied from the PM.

Data can be sent to or received from the ground.

Vacuum Chamber

Heating Unite

Motor（GHF installed in the KOBAIRO Rack）
GHF Material Processing Unit (Furnace)

Figure 6.3.1-8 GHF

6-13

6. Kibo
bo Utilization

Table 6.3.1-6 GHF Specifications
Items

Specifications

Heating Temperature Range

500 to 1600 °C

Temperature Stability

Within ±0.2 °C

Temperature Gradient

150 °C / cm or higher at temperature 1450 °C

Speed

0.1 to 200 mm / hTemperature Monitoring

Five points (max. 10 points)

KOBAIRO Rack (Installed at Location
Code F3 in PM)

Figure 6.3.1-9 Location of KOBAIRO Rack in PM

6-14

Kibo HANDBOOK

6.3.2 Exposed Facility (EF) Experiment Payloads(1) Monitor of All-sky X-ray Image (MAXI)The Monitor of All-sky X-ray Image (MAXI) will monitor X-ray variations from more than 1,000 X-ray
sources.

The observations will encompass the entire sky during a time period ranging from a day to a few

months.

The MAXI will conduct monitoring once per orbit.

The MAXI is equipped with two types of slit cameras. The first camera is a Gas Slit Camera (GSC) with agas proportional counter. The GSC is equipped with 12 counters.
5000 cm2.

The GSC has a total effective area of

The second camera is a Solid-state Slit Camera (SSC) with peltier-cooled X-ray sensitive CCD.

The MAXI is equipped with two SSCs that provide a total effective area of 200 cm2.

By combining thesecameras, an x-ray in a low to high-energy range can be captured over a wide range of wavelengths.

Color

image data can be obtained using an X-ray.
An overview of the MAXI is shown in Figure 6.3.2-1. The specifications for the slit cameras mounted on the
MAXI are shown in Table 6.3.2-1.

Payload Interface Unit

Radiation plate

Grapple Fixture

Power unit
Ring laser
gyroscope
Visual Star Camera Head

Signal processing
Mission Data Processor
Gas Slit Camera
Solid-state Slit Camera

Loop Heat Pipe

Figure 6.3.2-1 MAXI

6-15

6. Kibo Utilization

Table 6.3.2-1 Specifications of Slit Cameras mounted in MAXI
Items

Specifications

Sky coverage

FOV: 160 degree (L) x 1.5 degree (FWHM), 2 directions
Scope of instant observation: 2 % of the entire sky
Scanning: 90 to 98 % of the entire sky (per orbit)

Imaging capability

Point spread function (PSF): 1.5 degree (FWHM)
Pointing Accuracy: Less than 6 arc min.

Spectroscopy

X-ray photons of 2 to 30 keVResolution

18 % at 5.9 keVTiming accuracy

120 μ sec. with respect to GPS timeSensitivity

10 m Crab (1 orbit), 1 m crab (1 week)

Sky coverage

FOV: 90 degree (L) x 1.5 degree (FWHM), 2 directions
Scope of instant observation: 1.3 % of the entire sky
Scanning: 70 % of the entire sky (per orbit)

Imaging capability

Point spread function (PSF): 1.5 degree (FWHM)
Pointing Accuracy: Less than 6 arc min.

Spectroscopy

X-ray photons of 0.5 to 10 keVResolution

150 eV at 5.9 keVTiming accuracy

3 to 16 sec. (Dependent on CCD read-out methods)

Sensitivity

20 m Crab (1 orbit), 2 m crab (1 week)

GSC

SSC

Note: mCrab = unit, 1/1000 of the X-ray intensity of the Crab Nebula

6-16

Kibo HANDBOOK(2) Superconducting Submillimeter-Wave Limb-Emission Sounder (SMILES)The Superconducting Submillimeter-Wave Limb-Emission Sounder (SMILES) will observe submillimeter
wavelengths that are emitted from trace gases in the stratosphere. These observations will be conducted bypointing the SMILES antenna (Submillimeter Antenna (ANT)) at the upper reaches of the atmosphere. The
SMILES can determine the amount of trace gases that exist in the ozone layer. The SMILES measures the
distribution and changes in the trace gases in the stratosphere, globally, with a high degree of accuracy.
The Submillimeter-wave Receiver installed in SMILES is comprised of a superconductive sensor andamplifiers (low noise).

The SMILES uses a highly sensitive superconductive sensor and a 4-Kelvinmechanical cooler that are world leading edge components.
An overview of the SMILES is shown in Figure 6.3.2-2. The specifications of SMILES sensors andmeasuring instruments are shown in Table 6.3.2-2.

Crycooler Drive Electronics

Antenna Drive Electronics
Electrical Power System

Ambient Temperature Optics

Acousto-Optic
Spectrometer

Beam Transfer UnitStar Tracker

Submilimeter-wave emitted from trace gases

Antenna Reflector

Figure 6.3.2-2 SMILES

6-17

6. Kibo Utilization

Table 6.3.2-2 SMILES / Equipment Specifications
Items

Main bodySensor &measuring
instruments

6-18

Specifications

Mass (weight)

Less than 500 kg

Electrical powerLess than 900 W (tentative)

Observation band

640 GHz Band

Target gases

O3, HCI, CIO, HO2, H2O2, HOCI, BrO, HNO3, SO2, etc.

Latitude range

65N to 38S

Altitude range

10 to 60 km

Sensitivity

1 K (rms) in a single scan

Submillimeter Antenna (ANT)

Structure type: Offset Cassegrain reflector
Size: 400 mm x 200 mm
HPBW: 0.09 degree (El) x 0.18 degree (Az)

Submillimeter-wave Receiver

RF: 624.32 to 626.32 GHz (LSB)
648.32 to 650.32 GHz (USB)LO frequency: 637.32 GHzIntermediate frequency: 11.0 to 13.0 GHz

Mechanical 4-K Cooler

Joule - Thomson Cryocooler: 4.5 K
Stirling Cryocooler (x2): 20 K, 100 K

Acousto-optical Spectrometer(AOS)

Band: 1.2 GHz
Channel: 1500 per unit
Resolution: 1.8 MHz

Kibo HANDBOOK(3) Space Environment Data Acquisition equipment-Attached Payload (SEDA-AP)
The Space Environment Data Acquisition equipment-Attached Payload (SEDA-AP) will measure the spaceenvironment (neutrons, plasma, heavy ions, high-energy light particles, atomic oxygen, and cosmic dust) at theISS orbit.

Using the SEDA-AP, the space environmental effects on materials and electronic devices will be

investigated.
A number of sensors and equipment are mounted in the SEDA-AP, including the Neutron Monitor (NEM)
and the Plasma Monitor (PLAM).

Space environment data obtained by the SEDA-AP will be applied to thedevelopment of future spacecraft designs. The data will also be utilized for ISS operations and relatedscientific researches, and space weather forecast (prediction of solar activity trends).
The SEDA-AP will conduct measurement and monitoring by extending a mast, on which the Neutron
Monitor (NEM) - Sensor and the Plasma Monitor (PLAM) are attached.

The mast extends to over 1 m fromthe SEDA-AP structural body. The experiments using the SEDA-AP sensors and electronic devices willmeasure, monitor, and collect data, simultaneously, for three consecutive years.
An overview of the SEDA-AP is shown in Figure 6.3.2-3.

The specifications for the SEDA-AP sensors andmeasuring instruments are shown in Table 6.3.2-3.

Heater Control Equipment
Extension Mechanism
Drive circuit

Heavy Ion Telescope (HIT)
Neutron Monitor (NEM) - Sensor

Kibo Exposed Facility
Standard
Dose Monitor(SDOM)

PDU

Attached Payload Remote Terminal
Atomic Oxygen Monitor(AOM)

Plasma Monitor (PLAM)
Micro-Particles Capturer(MPAC) and Space Environment
Exposure Device (SEED)Electronic Device Evaluation
Equipment (EDEE)

Neutron Monitor (NEM) - Electronic device

Figure 6.3.2-3 SEDA-AP

6-19

6. Kibo Utilization

Table 6.3.2-3 SEDA-AP / Equipment Specifications
Items

Main body

Dimension

Mast stowed : W800 x H1000 x L1850 mm
Mast extended : W800 x H1000 x L2853 mm

Mass (weight)

Approx. 450 kg

Power Consumption

Approx. 220 W (Nominal operation)

Extension Capacity

NEM Sensor extends to over 1 m from the SEDA-AP structural
body

Neutron Monitor(NEM)

Bonner Ball Neutron Detector (BBND)
Measuring energy range : 0.025 eV (thermal neutron) to 15 MeV
Maximum number of measurable particles : 1 x 104 count/sec
Scintillation Fiber Detector (FIB)
Measuring energy range : 15 MeV to 100 MeV
Maximum number of measurable particles : 50 event/sec

Heavy Ion Telescope(HIT)

Li: 10 to 43 MeV/nuc
C: 16 to 68 MeV/nuc
O: 18 to 81 MeV/nuc
Si: 25 to 111 MeV/nuc
Fe: 34 to 152 MeV/nuc

Plasma Monitor (PLAM)

Langmuir probe mode :High Gain -0.2 µA to +2 µA
Low Gain -0.04 mA to +0.4 mA
Floating probe mode :High Gain ±5 V
Low Gain ±100 V

Standard Dose Monitor(SDOM)

Electron : 0.5-21 MeV (7 ch)
Proton : 1.0-200 MeV (15 ch)
Alpha : 7.0-200 MeV (6 ch)
Heavy Ion : ID only (1 ch)

Atomic Oxygen Monitor(AOM)

Measuring range : 3 x 1017 to 3 x 1021 atoms/ cm2
Resolution : 3 x 1017 atoms/ cm2

Electronic Device
Evaluation Equipment(EDEE)

Memory (1MSRAM)
Micro-Processor Unit (V70-MPU)
Power MOSFET

Micro-Particles Capturer(MPAC) and Space
Environment Exposure
Device (SEED)

Micro-particle capture :Silica-aerogel (34 mm x 34 mm x 9 pcs)
Golden plate (119 mm x 60 mm x 2 pcs
76 mm x 25.5 mm x 1 pcs)
SEED onboard sample : Scheduled to be selected prior to launch

Sensor andElectronic
Device6-20

Specifications

Kibo HANDBOOK

6.4

Utilization Plan

6.4.1 Overall ScheduleWith the exception of the GHF, all of the experiment payloads, as shown in section 6.3.1, will be installed in
the SAIBO Rack or the RYUTAI Rack.

The SAIBO Rack and RYUTAI Rack will be stored in Kibo’s

Experiment Logistics Module-Pressurized Section (ELM-PS). The ELM-PS is scheduled for launch during
Japan Fiscal Year 2007.
Both racks will be transferred from the ELM-PS to Kibo’s Pressurized Module (PM), and will be installed at
the locations as shown in Figure 6.3.1-2 and Figure 6.3.1-5, respectively.

After functions of the two racks areverified on orbit, experiments using these two racks will commence, based on the schedule as shown in Figure
6.4.1-1.

Transfer method of the GHF in the KOBAIRO Rack is currently under consideration. The

KOBAIRO Rack may be launched on-board the HTV toward the ISS.
The SEDA-AP and MAXI will be launched aboard the space shuttle, and will be attached onto Kibo’s
Exposed Facility (EF) on orbit.
The SMILES is currently planned for launch on-board the HTV.

FY2007
February, 2008
JEM ELM-PS

FY2008
April, 2008
JEM-PM

In the ELM-PS

FY2009FY2008JEM-Exposed Facility& ELM-ESOn the ELM-ES

FY 2009
HTV#1 launch

On the Unpressurized
Logistics Carrier (ULC)of HTV.

FY2010FY 2010
HTV#2 launch

In Pressurized Logistics
Carrier (PLC) of HTV

KOBIRO Rack

SAIBO Rack
RYUTAI Rack
Both rack will be install in
ELM-PS at NASA Kennedy
Space Center.

Development is completed

MAXI
SEDA-AP
SEDA-AP
Development has completed.
Preparing for launch and onboard operation

SMILES
Assembling flight hardware

MAXI
Assembling flight hardware(July 2007 updated)
Figure 6.4.1-1 Major Milestone (tentative) for Experiment Payload Launches

6-21

6. Kibo Utilization

6.4.2 Utilization Fields
The period of two-and-half years starting after Kibo launch until the completion of the ISS construction,scheduled for the middle of 2010, is defined as the First Utilization Phase (Initial Utilization Phase). Toward
the First Utilization Phase, the following preparation tasks for Kibo utilization are in progress.
Scientific Research•Preparations of the 16 experiment themes related to Life Science and Material Science, which wereselected from domestic or international applications, and will be conducted in the PM, are progressing.

•

Development of the three Exposed Facility (EF) experiment payloads (SEDA-AP, SMILES and MAXI)
to be conducted on Kibo’s EF are progressing.

•

Preparations of the three Life Science and space-medicine experiment themes, which were selectedfrom international applications, and will be using ISS facilities (non Kibo facilities), are progressing.

Applied Research•

Research activities related to protein crystallization and nano application study are under consideration
at the Application Research Center.

Space Medicine and Human Space Technology•

Researches focusing on medical risk mitigation for long-duration manned space exploration areprogressing. (Telemedicine, reducing bone and muscle atrophy, etc.)

Diversified Utilization, including Education and Culture•

Educational missions targeted for students and on-orbit scientific educational experiments are being
planned.

•Ten experiments have been selected as pilot studies for the Art field with preparations currently inprocess.

Utilization by the Asia Pacific Region•

Utilization of Kibo facilities is being proposed at the Asia-Pacific Regional Space Agency Forum(APRSAF). Feasibility assessment of Kibo experiments after 2010 is in process.

Commercial Utilization (fee base)•Supporting the Private sector businesses through commercializing the results from application
researches or Space Open Lab Program.

•

6-22

Using Kibo facilities for a fee are currently under consideration.

Kibo HANDBOOK

6.4.3 Experiment Themes
The scientific experiment themes, which will be conducted in Kibo’s Pressurized Module (PM), weredomestically solicited in 1992. The preliminary selections of the domestic experiments were conducted inAugust 1993. Life Science and microgravity-science experiment themes that will be conducted in Kibo’s
Pressurized Module (PM), were also solicited internationally.

Preparations of the selected experiment themes

from domestic and international applications have been in progress as part of the collaborative activities
between the themes’ principal investigators and Japan Aerospace Exploration Agency (JAXA).

The

preparations include preparations of the experiment plans (protocols), refinement of the specifications for the
payloads, evaluations on the experiment operational tasks, and pilot studies on experiments using the space
shuttles. Through these activities, the required techniques and methods for conducting experiments utilizing
Kibo facilities have been accumulated.
Table 6.4.3-1 shows the experiment themes of Kibo (Material Science and Life Science) that will utilize
Kibo’s Pressurized Module (PM) during the First Utilization Phase. Table 6.4.3-2 shows the experiment
themes that will utilize Kibo’s Exposed Facility (EF) or other ISS facilities (non-Kibo facilities).
Table 6.4.3-3 shows the utilization themes currently under consideration from such diverse fields as,
application research, space medicine, manned space exploration, culture and education.

6-23

6. Kibo Utilization

Table 6.4.3-1 Scientific Experiment Themes (Material Science & Life Science)
Kibo’s Pressurized Module (PM)Fields

Title
•
•
•
•

Material
Science•••••

Pressurized
Module

•
•
•
•
Life
Science
•
•
•
•

6-24

Spatio-temporal Flow Structure in Marangoni Convection (Marangoni1;
Yasushi Takeda, Hokkaido University)
Chaos, Turbulence and its Transition Process in Marangoni Convection(Marangoni2; Hiroshi kawamura, Science University of Tokyo)
Investigation on Mechanism of Faceted Cellular Array Growth (Facet; Yuko
Inatomi, JAXA)
Study on micro-gravity effect for pattern formation of dendritic crystal by amethod of in-situ observation (Ice Crystal; Yoshinori Furukawa, Hokkaido
University)
Experimental Assessment of Dynamic Surface Deformation Effects inTransition to Oscillatory Thermo capillary Flow in Liquid Bridge of HighPrandtl Number Fluid (Marangoni3; Satoshi Matsumoto, JAXA)Interfacial Stability under Microgravity (Succinonitrile; Yasunori Miyata,
Nagaoka University of Technology)
Role of the short range order on the self-and impurity diffusion of group
14(IVB) elements with a different degree of complexity* (Diffusion; Toshio
Itami, Hokkaido University/JAXA)
Growth of Homogeneous In0.3Ga0.7As Single Crystals in Microgravity*(Hicari; Kyoichi Kinoshita, JAXA)
Control of cell differentiation and morphogenesis of amphibian culture cells(Dome Gene; Makoto Asashima, Tokyo University)
Biological effects of space radiation and microgravity on mammalian cells(Neuro Rad; Hideyuki Majima, Kagoshima University)
Detection of Changes in LOH Profile of TK mutants of Human Cultured
Cells (LOH; Fumio Yatagai, RIKEN)
Gene expression of p53-regulated Genes in Mammalian Cultured Cells after
Exposure to Space Environment(Rad Gene; Takeo Ohnishi, Nara
Medical University)
Cbl-Mediated Protein Ubiquitination Downregulates the Response of Skeletal
Muscle Cells to Growth Factors in Space (Myo Lab; Takeshi Nikawa, T
University of Tokushima)
Regulation by Gravity of Ferulate Formation in Cell Walls of Wheat
Seedlings (Ferulate; Kazuyuki Wakabayashi, Osaka City University)
Integrated assessment of long-term cosmic radiation through biologicalresponses of the silkworm, Bombyx mori, in space (Rad Silk; Toshiharu
Furusawa, Kyoto Institute of Technology)
Life Cycle of Higher Plants under Microgravity Conditions (Space Seed;
Seiichiro Kamisaka, Toyama University)
RNA interference and protein phosphorylation in space environment using
the nematode Caenorhabditis elegans (CERISE; Atsushi Higashitani,
Tohoku University)

Kibo HANDBOOK

Table 6.4.3-2 Scientific Experiment Themes
Kibo’s Exposed Facility (EF) or other ISS facilities
Fields

Title•

Exposed Facility•••

Material
Science

•
•
•

Other
ModuleLife
Science

•
•
•

Space
Medicine•

Monitoring the Space Environment and Research on Its Effects on Parts &Materials (SEDA; Tateo Goka, JAXA)
Experimental Observation of Atmosphere Using ”SMILES” (SMILES;
Masato Shiotani, Kyoto University)
Research on Long-and Short-Term Variations of ALL Sky A-ray Sources(MAXI; Masaru Matsuoka, JAXA)
Effect of Material Properties on Wire Flammability in a Weak Ventilation ofSpacecraft (Osamu Fujita, Hokkaido University)
Containerless Crystallization of Silicon in Microgravity (CCSM; Kazuhiko
Kuribayashi, JAXA)
Role of Microtubule-Membrane-Cell Wall Continuum in Gravity Resistancein Plants (Cell-Wall; Takayuki Hoson, Osaka City University )Reverse genetic approach to exploring genes responsible for cell-wall
dynamics in supporting tissues of Arabidopsis under gravity conditions.
(Resist-Wall; Kazuhiko Nishitani, Tohoku University)
Effects of Microgravity and Neuromuscular Activity on Skeletal Muscle
Fibers (Akihiko Ishihara, Kyoto University)
The Effect of Microgravity on Vestibular Neurotransmission (Shinichi Usami,
Shinshu University)
Hydrotropism and auxin-inducible gene expression in roots grown inmicrogravity conditions (Hydro Tropi; Hideyuki Takahashi, Tohoku
University)
Preflight zoledronate infusion as an effective countermeasure forspaceflight-induced bone loss and renal stone formation (Bisphosphonates;
Toshio Matsumoto, University of Tokushima)

6-25

6. Kibo Utilization

Table 6.4.3-3 Utilization Themes other than scientific experiments (tentative)
Fields•••Protein Crystallization (Osaka University)
Nano-material (Nagoya Institute of Technology)
Dynamics of Interfaces (Tokyo University of Science)•••

Physiological Countermeasure; Prevention of bone loss and urinary stone,
Countermeasure for muscle atrophy
Psychological Support; Psychological monitoring for adaptation of isolationand human interaction, Cross-cultural Issue
Radiation; Bio-dosimetry, Personal dosimetry (advanced type)
Medical System; Small and Portable Medical data monitoring equipment(Tele-medicine), Autonomous Diagnostic Medical equipment
Environment; Gas monitoring and analyzing system (advanced type)
Habitation Technology(Japanese Space Foods, e.t.c.)JEMutilization
by Asia
Pacific
region••Research collaboration with Asia Pacific region
Educational program using ISS/JEM

Commercial
utilization•••

Protein Crystallization
3 Dimensional Photonic Crystallization
High Definition Video filing

Appliedresearch

Pressurized
Module

6-26

Title

Space
Medicine
Human
Space
Technology•••

Kibo HANDBOOK

6.4.4 Utilization Plan
For the First Phase Utilization, which will continue for three years from the beginning of the Kibo operations
until 2010, the detailed operations plans have been deliberated at the ISS/Kibo Utilization Promotion
Committee, which is an external advisory committee to JAXA.

The allocation of the utilization resources per

study field or the experiment payloads that will be loaded on Kibo, or the experiment themes that are targeted
for international coordination in 2008, were arranged in 2005.
For international coordination, the allocation of the ISS utilization resources and optimization of the ISS
overall resources are currently being evaluated based on the ISS overall logistics plan and the ISS overall
operations plan.
Figure 6.4.4-1 shows the tentative schedule for the First Utilization Phase

FY

FY2007

Inc. 15

FY2008

Inc. 16
Inc. 17△1J/A△1J

FY2009Inc. 18

Inc. 19△2J/A

JEM Pressurized Module

FY2010Inc. 20

Inc. 21RYUTAI Rack

FPEF

Inc. 22

Inc. 23

HTV
Marangoni1

Marangoni2
Marangoni13
Facet

SCOF

Ice Crystal
Succinonitrile

PCRF
Rad Gene
LOH
Dome Gene
Rad Silk
CERISE

CBEF
CB

SAIBO Rack

Neuro RadSpace Seed
Myo Lab

GHF

Ferulate

KOBAIRO Rack
HicariDiffusion
HD CamHD Cam/Small devices
Education/Culture

Other Module (IAO)

US LabHD CamCell Wall / Resist Wall
Bisphosphonates (Pre/Post flight)

RussianModuleJEM Exposed Facility

Matryoshka/ARTCLISS/Space ICCHIBAN
3DPC #2
Protein #2
Protein #3

SEDA
MAXI
SMILES(July 2007 updated)
Figure 6.4.4-1 Schedule for the First Utilization Phase (tentative)

6-27

6. Kibo Utilization

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6-28

Kibo HANDBOOK

7. H-II Transfer Vehicle (HTV) Overview

7-1

7. H-II Transfer Vehicle (HTV) Overview

7.1

Summary

The H-II Transfer Vehicle (HTV), designed and being built in Japan, is an unmanned cargo transfer
spacecraft that will deliver supplies to the International Space Station (ISS).
The HTV will be launched from the Tanegashima Space Center in Japan aboard an H-IIB Launch Vehicle(currently under development). When the HTV approaches close proximity to the ISS, the Space Station
Remote Manipulator System (SSRMS), also known as "Canadarm2," will grapple the HTV and berth it to theISS.

The HTV will deliver up to 6,000 kg of supplies, including food, clothing and several types ofexperiment payloads to the ISS.

After the supplies are unloaded, the HTV will then be loaded with wastematerials, including used payloads or used clothing. Afterward, the HTV will undock and depart from the ISS,
and will de-orbit and reenter the atmosphere. While the HTV is berthed to the ISS, the ISS crew members
will be able to enter and remove supplies from the HTV Pressurized Logistics Carrier (PLC).
Figure 7.1-1 shows an image of the HTV on-orbit.

Figure 7.1-1 Image of HTV during Flight
The HTV will be utilized for delivering supplies to the ISS as with the Russian Progress cargo spacecraft, theU.S. space shuttle, and the Automated Transfer Vehicle (ATV) developed and built by the European Space
Agency (ESA),. The HTV can carry both pressurized (for inside use) and un-pressurized (for outside use)
cargo, and this is a unique special feature of the HTV.
The launch of the HTV "Technical Demonstration Vehicle" (initial flight vehicle) is scheduled during Japan’s
fiscal year 2009 (JFY 2009).

7-2

Thereafter, one or two HTVs per year are planned for launch.

Kibo HANDBOOK

7.1.1 HTV Components
The H-II Transfer Vehicle (HTV) consists of two logistic carriers: Pressurized Logistics Carrier (PLC) andUn-pressurized Logistics Carrier (UPLC) which carries an Exposed Pallets (EP), and an Avionics Module and a
Propulsion Module.
Proximity

Communication System(PROX),

antennas andreflectors which enable inter-orbit

communications between Kibo and the HTV, are installed on Kibo, and will be utilized when the HTV
approaches the ISS.

Table 7.1.1-1 shows the HTV specifications.
Avionics Module
Avionics Module contains navigation,communication and electrical equipment

Un-pressurized Logistics
Carrier (UPLC)
Pressurized Logistics Carrier (PLC) UPLC will carry an Exposed Pallet
PLC will carry supplies that will be
used aboard ISS. ISS crew will beable to enter and work inside PLC

Propulsion Module
Exposed Pallet（EP）
Exposed Pallet will carry
un-pressurized payloads

Common Berthing
Mechanism（CBM）

Propellants, necessary to generate
propulsion for rendezvous,
attitude control and de-orbit, arestored in Propulsion Module’s
propellant tanks

Figure 7.1.1-1 HTV Configuration Diagram

Table 7.1.1-1 HTV Specifications
Items

Specifications

Length10 m (including thrusters)

Diameter

4.4 m

Mass (weight)

10,500 kg (exclude cargo mass)

Cargo capacity (supplies)

6,000 kg-Pressurized cargo: 4,500 kg-Un-pressurized cargo: 1,500 kg

Cargo capacity (waste)

6,000 kg

Target orbit to ISS

Altitude: 350 km to 460 km
Inclination: 51.6 degrees

Maximum duration of a mission

Solo flight: 100 hours
Stand-by (on-orbit): More than a week
Berthed with the ISS: Maximum 30 days

7-3

7. H-II Transfer Vehicle
ehicle (HTV) Overview(1) Pressurized Logistic Carrier (PLC)The Pressurized Logistics Carrier (PLC) will carry cargo, including International Standard Payload Racks(ISPR), drinking water, and clothes that will be used aboard the ISS.
maintained at one atmospheric pressure (1atm).
to the ISS.

The PLC's internal air pressure isTemperature inside the HTV is controlled until it is berthed

After the HTV is berthed to the ISS, the PLC’s and the ISS’s internal air will be circulated

throughout the ISS using fans.

While the HTV is berthed to the ISS, the ISS crew will be able to enter the

PLC to unload the supplies.

After the supplies are unloaded, the HTV will de-orbit and reenter theatmosphere carrying the waste materials.

The HTV's berthing port is equipped with a Common Berthing

Mechanism (CBM).
(2) Un-pressurized Logistic Carrier (UPLC)The Un-pressurized Logistic Carrier (UPLC) will carry an Exposed Pallet (EP) (Please refer to (3))(3) Exposed Pallet (EP)The Exposed Pallets (EPs) will carry EF payloads, as well as, the ISS battery Orbital Replacement Units(ORU).

There are two different types of Exposed Pallets, Type I and Type III. To meet different andspecialized purposes, development of other types of Exposed Pallets, in addition to Type I and Type III, areunder consideration. An outline of the Exposed Pallets is shown in Figure 7.1.1-2.
Type I:This type of pallet carries the Exposed Facility (EF) payloads that will be used on Kibo's Exposed
Facility (EF). Two or three EF payloads per flight can be delivered. This pallet will be attachedto the EF.

Type III: This type of pallet carries the US ORUs, such as the battery ORU. This pallet will be attached tothe station's Mobile Base System (MBS).

Up to six battery ORUs can be delivered.

FRGF
EF payload

A Battery ORU can be
temporarily attached

Battery ORU

PIU
FRGF

Exposed Pallet
Type I

PVGF
Type IIIFRGF: Flight Releasable Grapple Fixture. JEMRMS grapples here.
PVGF: Power Video Grapple Fixture. Canadarm2 grapples here.
PIU: Payload Interface Unit (Passive part of EEU). For detail, please refer to Chapter 4 Section 4.3
Figure 7.1.1-2 Exposed Pallets (EP) (left: Type I, right: Type III)

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Kibo HANDBOOK(4) Avionics Module
The Avionics Module contains guidance navigation & control, communication and electrical power systems.
The Avionics Module controls and navigates the HTV’s remote-controlled flight by receiving commands fromthe ground or by HTV autonomous flight.

In addition, the Avionics Module distributes power to eachcomponent of the HTV.
(5) Propulsion Module
The Propulsion Module has four propellant tanks. These tanks supply propellant to the HTV thrusters.

The

propulsion for orbital adjustment or attitude control will be produced by commands sent from the Avionics
Module.

The HTV has 32 thrusters installed. Specifications of the HTV thrusters are shown in Table 7.1.1-2.

Locations of the thrusters are shown in Figure 7.1.1-3

Table 7.1.1-2 HTV thruster specifications
Specifications
Items
Main thruster

Attitude Control Thruster

Number of units

4 units

14 units x 2 string (redundant structure)*Of 28 units, 12 units are installed on thePressurized Logistics Carrier (PLC)

Thrust (per unit)

490N

110N

Attitude Control Thruster

Main Thruster

Attitude Control Thruster

Figure 7.1.1-3 Location of HTV thrusters

7-5

7. H-II Transfer Vehicle
ehicle (HTV) Overview(6) Proximity Communication System (PROX)
The Proximity Communication System (PROX), which is installed in Kibo, consists of PROX antennas,
PROX-GPS antennas, PROX communication equipment, and a Hardware Command Panel (HCP). With thetheexception of the PROX antennas, the PROX-GPS antennas and the HCP, the PROX related equipments are
installed in the Inter-orbit Communication System (ICS) rack, which is one of the JEM system racks installedin the JEM Pressurized Module (PM).
When the HTV approaches in close proximity to the ISS, the PROX antenna will initiate communications
with the HTV. This antenna contains GPS receivers.
be relayed to the HTV through the PROX.

The ISS's orbital location and speed will immediately

At the same time, data from the HTV will be relayed to the ISS.

In addition, the antenna will relay commands sent from the ground to the HTV.
(7) Reflector
The reflectors are installed on the nadir (bottom) side of Kibo. The reflectors will reflect the lasers that arearebeamed from the HTV's Rendezvous Sensor (RVS) when the HTV is in ISS Proximity Operations and as ththee
HTV approaches the ISS from the nadir side (direction of earth). For locations of the reflectors, please refer
to Figure 7.1.1-4

PROX GPS AntennaCommunications & Data
Handling/Electrical Power/GPS
equipment(Installed in the ICS rack in the PM)
Reflector

PROX antenna (Installedon the outside of the PM)
Figure 7.1.1-4 PROX and Reflectors

7-6

Hardware Command
Panel (HCP)Kibo HANDBOOK

7.2

HTV Operations

The HTV will be operated in the following sequence. An outline of the HTV operations is shown in Figure
7.2-1
1.

Launch2.

Rendezvous with the International Space Station (ISS)3.

Berthing with the ISS

4.

Operations while berthed with the ISS

5.

Undock/Departure from the ISS/Reentry

Max. 30 days

TDRSS

TDRSS

ISS Proximity
Operations Phase

4 min. after
launchH-IIB/HTV
Separation

Rendezvous
Phase
Approx. 3 days

ISS DeparturePhase
De-orbit
Phase
Reentry

H-IIA/B-CC

HTV-CC
Tanegashima
Space Center

Tsukuba Space Center (TKSC)

Control
Center

SSCC
NASA Johnson
Space Center (JSC)

NASA White Sands
Ground Station

US

Japan

Figure 7.2-1 HTV Operations

7-7

7. H-II Transfer Vehicle
ehicle (HTV) Overview

7.2.1 Launch
The HTV will be launched from the Tanegashima Space Center aboard an H-IIB launch vehicle (Figure
7.2.1-1 above). The HTV’s launch opportunity will be once a day, since the HTV’s launch time has to be
adjusted and scheduled for when the ISS’s orbital plane is passing over the Tanegashima Space Center launch
site.

HTV mounted
insideH-IIB Launch Vehicle(Second Stage)

HTV

Figure 7.2.1-1 HTV Launch Image (above) and HTV/H-IIB Separation Image (below)
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Kibo HANDBOOK

Following the launch phase, the HTV will be inserted into an elliptical orbit with an altitude of 200 km(perigee) x 300 km (apogee) and a inclination of 51.6 degree.
After separating from the H-IIB launch vehicle, 1) the HTV will automatically activate the HTV subsystems,2) maintain its attitude,3) perform a self-check on the HTV’s components, and 4) initiate communications with
the HTV Control Center (HTV-CC) at Tsukuba Space Center (TKSC).

7.2.2 Rendezvous
After separating from the H-IIB launch vehicle, the HTV will approach the ISS in the following sequence as
described below.

Figure 7.2.2-1 shows the HTV Rendezvous Flight profile that depicts how the HTV willapproach the ISS, by boosting (adjusting) the HTV’s orbital altitude.
1.

After separating from the H-IIB launch vehicle, the HTV will automatically activate HTV’s
communication system and initiate communications with NASA's Tracking and Data Relay Satellite(TDRS).

2.

The HTV status will be monitored from the ground. Next, the HTV will then start orbital flighttowards the ISS.

3.

After three days of orbital flight, the HTV will reach close proximity to the ISS.

4.

The HTV will reach the proximity "Communication Zone" (23 km from the ISS), at which point the
HTV can directly communicate with the ISS

5.

The HTV will establish communications with the Proximity Communication System (PROX).

6.

While communicating with PROX, the HTV will approach the ISS, guided by GPS signals (Relative
GPS Navigation), until the HTV reaches the “Approach Initiation (AI) Point, 7 km behind the ISS .
At this point, the HTV will maintain this distance from the ISS.

AltitudeTime
Reentry

Proximity
Departure operations

Rendezvous

LaunchISS
Adjusting orbital
altitude and phase
ApogeePerigeeFigure 7.2.2-1 HTV Rendezvous Flight Profile

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7. H-II Transfer Vehicle (HTV) Overview

7.2.3 Berthing with the ISS (Proximity Operation Phase)
The HTV will slowly approach the ISS from the nadir (bottom) side of the ISS (from the direction of Earth).
The HTV will then be grappled by the Canadarm2 and berthed to the ISS.

ISS Proximity Scale
Drawing

Direction of travel

7 km behind the ISS

AI Point

Parking Point
Departure
Operations

R-bar approach
Rendezvous Sensor Navigation

Separation
ManeuverApproach
Initiation

500 m fromthe ISSRGPS Navigation

Final Approach

RGPS Navigation: Relative GPS navigation
R-bar Approach: Approach from the direction of earth

Figure 7.2.3-1 HTV Proximity Operations

The HTV's approach to the ISS during the Proximity Operation Phase is as follows.
1.

The HTV will move from the Approach Initiation (AI) Point to a point 500 meters below the ISS, asguided by Relative GPS Navigation

2.

Using a laser radar called “Rendezvous Sensor (RVS)”, the HTV will approach closer to the ISS. Laser
reflectors are installed on Kibo (This is called “RVS Navigation”)

3.

The HTV will slowly and gradually approach the ISS.

The HTV will hold its approach twice, whenreaching the following points: HTV will stop 300 m below the ISS (hold point), and will stop 30 m
below the ISS (Parking Point).
4.

Eventually, the HTV will approach a proximity area called “Berthing Point”.

This point is set 10 m

below the ISS, and is in a predetermined area which is called ”Berthing Box”. Next, while at theBerthing Point, the HTV will maintain its distance from the ISS
The HTV’s approach speed during the RVS Navigation phase is 1 to 10 meters per minute. During theapproach, the ISS crew can send commands including "HOLD," "RETREAT" or "ABORT" to the HTV.

In

addition, if an emergency occurs and further approach can not be permitted, the HTV will be controlled todepart from the ISS orbit.

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Kibo HANDBOOK

Canadarm2
HTV

HTV

Canadarm2

Figure 7.2.3-2 Images of HTV approaching the ISS (above) and HTV Berthing to the ISS (below)

Once the HTV Control Center (HTV-CC) at the TKSC confirms that the HTV’s approach and distance fromthe ISS is within the Berthing Box, the ISS crew will inhibit the HTV thrusters (Figure 7.2.3-2 above). Next,
the Canadarm2 will grapple the HTV and berth the HTV to the CBM located at the nadir side (earth side) of theNode 2.

The HTV will then be berthed to the ISS (Figure 7.2.3-2 below).

7-11

7. H-II Transfer Vehicle (HTV) Overview

7.2.4 Operations while berthed to the ISS
Once the HTV is berthed to the ISS, the lights in the PLC will be powered up and the air pressure in the PLC
will be adjusted by ISS crew or the HTV-CC for ingress preparation.
tasks, both the HTV and ISS hatches will be opened.

After completing these preparatory

The temperature inside of the PLC will be maintained at

15.6 °C (degrees Celsius) before the ISS crew enters the PLC. This is a preemptive measure to hinder the
possible formation of dew upon the crew entering the PLC. While the HTV is berthed to the ISS, power will be
supplied from the ISS to the HTV.
After the hatches between the ISS and HTV opened, the ISS crew will start transferring the supplies (ISPRs,
drinking water, clothes, etc.) from the PLC to the ISS.

After the supplies are transferred, the HTV will be

loaded with waste from the ISS.
In addition, in order to unload the supplies from the Exposed Pallet (EP), the EP will be removed from the
HTV’s Unpressurized Logistics Carrier (UPLC) and will be attached to the ISS Mobile Base System (MBS) or
Kibo's Exposed Facility (EF). An example of the EP Type I transfer procedure is as follows.
1.

The Canadarm2 will grapple the EP, and remove the EP from the UPLC (Figure 7.2.4-1)

2.

The EP will be handed from the Canadarm2 to the JEMRMS, Kibo’s robotic arm (Figure 7.2.4-2 (2))

3.

The EP will be attached to Kibo’s Exposed Facility (EF) by the JEMRMS (Figure 7.2.4-2 (4))

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Kibo HANDBOOK

Canadarm2

HTV

Exposed Pallet

Figure 7.2.4-1 Image of EP being removed from UPLC

Canadarm2

Exposed Pallet

( )

( )

JEMRMS

( )

HTV

EF

( )
Figure 7.2.4-2 Image of EP attached to EF

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7. H-II Transfer Vehicle (HTV) Overview

7.2.5 Departure from the ISS and Reentry
After being loaded with waste, the HTV will undock and depart from the ISS. The HTV will be destroyed
while reentring the atmosphere. The procedures for the HTV’s undocking and departure from the ISS are as
follows.
1.

The hatch of the HTV will be closed and the power supply will be switched to the HTV’s internal
power supply by the ISS crew

2.

The Canadarm2 will grapple the HTV

3.

The Common Berthing Mechanism will be disengaged

4.

The Canadarm2 will move the HTV to the release point

5.

The Canadarm2 will release the HTV

6.

The HTV thrusters will be activated by the ISS crew.

7.

The HTV will depart from the ISS

Figure 7.2.5-1 Image of HTV reentering the atmosphere

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Kibo HANDBOOK

Visible window

Debris Falling
Permissible /Expected Areas

Visible window

Debris Falling
Permissible /Expected Areas

Figure 7.2.5-2 HTV Debris Falling Permissible (Allowed or Expected) Areas and HTV’s Orbit (Red lines)

7-15

7. H-II Transfer Vehicle (HTV) Overview

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7-16

Kibo HANDBOOK

Appendix

Acronyms and AbbreviationsiAppendix

Acronyms and Abbreviations

Acronym/Abbreviation

ii

Name

ACBM

Active Common Berthing Mechanism

AEFBM

Active Exposed Facility Berthing Mechanism

AI

Approach Initiation

AOM

Atomic Oxygen Monitor

AOS

Acousto-optical Spectrometer

APRSAF

Asia-Pacific Regional Space Agency Forum

ASCR

Assured Safe Crew Return

ATCS

Active Thermal Control System

ATF

Astronaut Training Facility (TKSC)

ATU

Audio Terminal Unit

ATV

Automated Transfer Vehicle

BBND

Bonner Ball Neutron Detector

C&C MDM

Command and Control Multiplexer/Demultiplexer

C&DH

Command and Data Handling

C&T

Communication and Tracking

CB

Clean Bench

CBEF

Cell Biology Experiment Facility

CBM

Common Berthing Mechanism

CDR

Critical Design Review

CGSE

Common Gas Supply Equipment

CMG

Control Moment Gyro

Col-CC

Columbus Control Center

CSA

Canadian Space Agency

CSS

Crew Support System

DC

Docking Compartment

DMS

Data Management System

DRTS

Data Relay Test Satellite

ECLSS

Environmental Control and Life Support System

ECU

Electronic Control UnitEDEEElectronic Device Evaluation Equipment

EEU

Equipment Exchange Unit

EF

Exposed Facility

EFBM

Exposed Facility Berthing Mechanism

EFU

Exposed Facility Unit

ELM-ES

Experiment Logistics Module-Exposed Section

ELM-PS

Experiment Logistics Module-Pressurized Section

Kibo HANDBOOK

Acronym/Abbreviation

Name

E-ORU

Extravehicular activity Orbital Replacement Unit

EPSElectrical Power System

ERA

European Robotic Arm

ESS

Experiment Support System

EVA

Extravehicular Activity

FCIT

Flight Crew Interface Test

FIB

Scintillation Fiber Detector

FSA

Federal Space Agency

FPEF

Fluid Physics Experiment Facility

FRGF

Flight Releasable Grapple Fixture

GHF

Gradient Heating Furnace

GPS

Global Positioning System

GSC

Gas Slit Camera

HCP

Hardware Command Panel

HEPAHigh Efficiency Particulate Air

HIT

Heavy Ion Telescope

HOSC

Huntsville Operations Support Center

HREL

Hold and Release Electronics UnitHTV

H-II Transfer Vehicle

HTV-CCHTV Control Center

ICS

Inter-orbit Communication System

ICS-EFICS Exposed Facility Subsystem

ICS-PM

ICS Pressurized Module Subsystem

IFHX

Interface Heat Exchanger

ISPR

International Standard Payload Rack

ISS

International Space Station

JAXA

Japan Aerospace Exploration Agency

JCP

JEM Control Processor

JEM

Japanese Experiment Module

JEMRMS

Japanese Experiment Module Remote Manipulator System

JFY

Japan’s fiscal year

JSC

Johnson Space Center

LCD

Liquid Crystal Display

LTL

Low Temperature Loop

LVLH

Local Vertical Local Horizontal

MA

Main Arm (JEMRMS)

iii

Appendix

Acronyms and Abbreviations

Acronym/Abbreviation

iv

Name

MAXI

Monitor of All-sky X-ray Image

MBS

Mobile Base System or MRS(Mobile Remote System) Base System

MCC

Mission Control Center

MCC-M

Mission Control Center - Moscow

MCR

Mission Control Room (TKSC)

MEIT

Multi-Element Integration Test

MLM

Multi-Purpose Laboratory Module

MOU

Memorandum of Understanding

MPAC&SEED

Micro-Particles Capturer and Space Environment Exposure Device

MSFC

Marshall Space Flight Center

MTL

Moderate Temperature LoopNASA

National Aeronautics and Space Administration

NASDA

National Space Development Agency of JapanNEM

Neutron Monitor

OBSS

Orbiter Boom Sensor System

OCS

Operation Control System (TKSC)

ODS

Orbiter Docking System

OPR

Operations Planning Room (TKSC)

ORR

Operations Rehearsal Room (TKSC)

PAM

Payload Attach Mechanism

PCBM

Passive Common Berthing Mechanism

PCRF

Protein Crystallization Research Facility

PDB

Power Distribution Box

PDRPreliminary Design Review

PDU

Power Distribution Unit

PEFBM

Passive Exposed Facility Berthing Mechanism

PIU

Payload Interface Unit

PLAM

Plasma Monitor

PLC

Pressurized Logistics Carrier (HTV)PM

Pressurized Module

PMA

Pressurized Mating Adapter

POIC

Payload Operations and Integration Center

PROX

Proximity Communication System

PTCS

Passive Thermal Control System

PVGF

Power & Video Grapple Fixture

RM

Research Module

Kibo HANDBOOK

Acronym/Abbreviation

Name

R-ORU

Robot essential Orbital Replacement Unit

RUR

Reference Update Review

RVS

Rendezvous Sensor

SCOF

Solution Crystallization Observation Facility

SDOMStandard Dose Monitor

SEDA-APSpace Environment Data Acquisition equipment – Attached Payload

SEL

Space Experiment Laboratory (TKSC)

SFA

Small Fine Arm (JEMRMS)SFUSpace Flyer Unit

SLM

Structure Latch Mechanism

SLT

System Laptop Terminal

SMILES

Superconducting Submilimeter-Wave Limb-Emission Sounder

SPCF

Solution/Protein Crystal Growth Facility

SRMS

Shuttle Remote Manipulator System

SSC

Solid-state Slit Camera

SSCC

Space Station Control Center

SSE

Small Fine Arm Storage Equipment

SSIPC

Space Station Integration and Promotion Center

SSOF

Space Station Operations Facility (TKSC)

SSRMSSpace Station Remote Manipulator System

TCS

Thermal Control System

TDRS

Tracking and Data Relay Satellite

TKSC

Tsukuba Space Center

UCM

Umbilical Connector Mechanism

UOA

User Operations Area (TKSC)

UPLC

Un-pressurized Logistics Carrier

URM

Unit Replacement Mechanism

WET

Weightless Environment Test Building (TKSC)

v