The International Space Station’s Modules
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The ISS comprises:
Zarya Functional Cargo Block
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Zarya Functional Cargo Block (FGB) was the first
component of the International Space Station. This module was designed
and built at M.V. Khrunichev enterprise (Russia) within the frame of the
contract, concluded with Boeing Company, the ISS general contractor of
the USA. The ISS in-orbit assembly began with this module. Initially the
FGB provided mated module configuration flight control, electric power
supply, communication, and also fuel receiving, storage, and transfer.
It was launched on the Russian Proton-K rocket
on the 20th of November, 1998.
Main technical characteristics
| Parameters |
Value |
| Orbital mass, kg |
20040 |
| Body length, mm |
12990 |
| Maximal diameter, mm |
4100 |
| Pressurized modules volume,
m3 |
71.5 |
| Solar arrays span, mm |
24400 |
| Photocells area, m2 |
28 |
| Power supply average capacity,
kW per day |
3 |
| Propellant mass, kg |
3800 |
| Estimated lifetime in-orbit,
years |
15 |
Zarya Layout
| Zarya FGB comprises a cargo instrumentation module
(PGO) and pressurized adapter (GA), which accommodates onboard systems,
used for mechanical docking with the other ISS elements and spacecraft
arrived. The pressurized adapter is separated from the cargo instrumentation
module by a pressurized spherical bulkhead with a hatch 800 mm in diameter.
Pressurized volume of PGO is 64.5 m3 and the same of GA is 7.0 m3. The
whole inside of PGO and GA is divided into instrumentation and habitable
zones. In the instrumentation zone there are onboard system units. The
habitable zone is intended for crew performance. There are elements of
onboard complex control and monitor systems and also elements of caution
and warning system in it. PGO has three functional blocks: PGO-2 is a conical
section of Zarya FGB, PGO-3 is a cylindrical section adjacent to GA, PGO-1
is also a cylindrical section between PGO-2 and PGO-3. |
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The Unity Node was the first major US-built
module of ISS American Segment. Unity Node was delivered by Space Shuttle
Endeavour during STS-88 in December, 1998. It was docked with Zarya FGB
already orbiting.
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Main dimensions:
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length – 5490 mm
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length (across adaptors) – 10980 mm
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diameter (max) – 4580 mm
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launching mass – 11500 kg
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Unity Module represents a cylindrical through
passage module. It has six berthing ports, one on each facet, to which
future modules can be attached. The Pressurized Mating Adapter I is attached
to its aft port.
Except that the Unity is attached to the Zarya,
it attached to the American Destiny laboratory module and the Quest airlock,
which is also a component of ISS AS. The module has the shape of a cylinder,
the bottoms of which have square hatches. These hatches are provided with
ÑÂÌ (Common Berthing Mechanism)-type docking nodes.
Unity Module is built by the Boeing Company at
a manufacturing facility of Marshall Space Flight Center in Huntsville.
It is the first of three such connecting modules that will be built for
the station. This module is 4.6 m (15 feet) in diameter and 5.5 m (18 feet)
long.
Zvezda Service Module (SM),
launched on July 12, 2000, provides the crew activities and control of
routinely changing configuration of the station. At the early stage of
ISS deployment this module was a core one.
SM’s habitable area is equipped with crew life
support means. There are personal rest rooms, medical equipment, exercise
machines, a food galley, a dining table, personal hygiene means in it.
Also there is a station control post with monitoring equipment in the module.
The Service Module consists of three pressurized
compartments (working compartment, transfer compartment, and transfer chamber)
and unpressurized assembly compartment.
Main technical characteristics
| Parameters |
Value |
| Module
mass, kg: |
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| Insertion
Module Mass |
22776 |
| Orbit
Module Mass |
20320 |
| Module
dimensions, m: |
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| Length
(with fairing and intermediate section) |
15.95 |
| Length
(without fairing and intermediate section) |
12.62 |
| Width
(with deployed solar array panels) |
29.73 |
| Volume,
m3: |
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| Internal
volume (including equipment) |
75.0 |
| Crew
habitation volume |
46.7 |
| Power
supply system: |
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| Operational
voltage, V |
28 |
| Solar
arrays capacity, kW |
10 |
| Propulsion
system: |
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| Main
Engines, kgf |
2x312 |
| Attitude
Engines, kgf |
32x13.3 |
| Oxidizer
Mass (nitrogen tetroxide), kg |
558 |
| Fuel
Mass (unsymmetrical dimethylhydrazine), kg |
302 |
Main functions:
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support of working and living conditions;
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control of main complex elements;
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power supply of the complex;
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providing two-way radio communication of a crew with
Ground-based Control Complex (GCC);
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television reception and transmission;
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transmission of telemetry information on crew and
onboard system status to GCC;
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receiving of control information;
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complex cog orientation;
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complex orbit correction;
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rendezvous and docking of other station elements;
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maintenance of temperature and humidity conditions
of habitable volume, constructional elements, and equipment;
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spacewalks, station maintenance, and repair of the
station external surface;
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scientific and applied research and experiments using
delivered equipment;
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support of two-way communication between complex
modules.
Zvezda Service Module comprises:
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onboard control complex, which incorporates:
- motion control system;
- onboard computer system;
- onboard radio system;
- flight measurement system;
- onboard complex control system;
- remote operator control mode equipment;
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electrical power supply;
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integrated propulsion system;
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thermal conditioning system;
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life support system;
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medical support means.
Destiny Laboratory Module
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Destiny Laboratory was delivered by Space
Shuttle Atlantis during STS-98 on February 10, 2001. It is the major module
for arrangement of American scientific equipment. It supports experiments
in microgravity research, human life science, fundamental biology and ecology,
space sciences, earth observations, and commercial applications.
Main technical characteristics:
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length over ends of docking nodes – 8788 mm,
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pressurized hull length – 8534 mm,
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maximal diameter – 4445 mm,
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pressurized volume – 117 m3,
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launching mass – 14056 kg.
Destiny Laboratory Module is the centerpiece of extensive
scientific research and experiment program aboard the International Space
Station that may contribute to studies toward cures for diseases like cancer
and diabetes, as well as material science, etc.
The Boeing Company began construction of the
16-ton, state-of-the-art research laboratory in1995 at Marshall Space Flight
Center in Huntsville, Alabama. In 1998 the Destiny was shipped to Kennedy
Space Center in Florida and in August, 2000 it was turned over to NASA
for pre-launch preparations.
Destiny Module Structure
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The module comprises three pressurized cylindrical
sections and two end cones. The “honeycomb” profile of the module walls
provides maximal strength with minimal mass. The pressurized hull
mass (without systems and assemblies) is 2.72 tons. Module bottoms
have hatches, where through astronauts can come in and out of it.
Destiny Module is docked to the forward port
of Unity Module.
Destiny Module is provided with ÑÂÌ (Common Berthing
Mechanism)-type docking nodes.
There are racks, rack standoffs, and vestibule
jumpers inside the laboratory. |
Quest Joint Airlock, one of the element
of ISS American Segment, was delivered during ISS-7À/STS-104 and was attached
to the right hand docking port of Unity Node on July 15, 2001.
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Quest Joint Airlock Specifications:
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length – 5491 mm (across mated CBM node – 5636 mm)
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maximal diameter – 4445 mm
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mass – 6064 kg
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pressurized volume – 34.0 m3
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Quest Joint Airlock is designed to provide Extravehicular
Activity (EVA) of ISS crews using either US Extravehicular Mobility Unit
(EMU) or Russian Orlan EVA suits.
| Quest Joint Airlock is a pressurized
module consisting of two main components, which are attached end-to-end
by a connecting bulkhead and hatch: a crew airlock, from which astronauts
exit into outer space, and an equipment bay for storing EVA assemblies
and suits and so-called overnight “campouts”, wherein Nitrogen is purged
from astronaut’s bodies overnight as pressure is dropped in preparation
for spacewalks the following day. This alleviates the bends of cosmonauts
after coming-back and compartment pressurization. |
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Pirs Docking Compartment (DC), which is an element
of ISS Russian Segment, was launched aboard Progress M-SO1 dedicated cargo
vehicle-logistics module on September 15, 2001. Progress M-SO1 was docked
to ISS on September 17.
The double-purpose Docking Compartment was designed
and built by RSC-Energia.
Firstly, it can be used as an airlock for exits
of two crewmembers in outer space.
Secondly, it serves as an additional port for
docking of both manned Soyuz transport vehicle and Progress M-type automatic
cargo vehicle.
Besides, it enables refilling of RS’s tanks with
propellant components, delivered aboard cargo vehicles. |
Main technical characteristics
| Parameters |
Value |
| Launching
mass, kg |
4,350 |
| In-orbit
mass, kg |
3,580 |
| Reserve
mass for delivered cargoes, kg |
800 |
| Orbit
altitude when assembling, km |
350-410 |
| Operational
orbit altitude, km |
410-460 |
| Length
with Docking Assembly extended, m |
4.91 |
| Maximal
diameter, m |
2.55 |
| Pressurized
compartment volume, m3 |
13 |
The active (pin) hybrid docking node SSVP-M
G8000 is intended for pressurized docking to Zvezda SM.
The passive (cone) docking node SSVP G4000
at the opposite side is intended for tight connection with Soyuz TM transport
vehicles and Progress M cargo vehicles.
Four Kurs-A motion control antennas
used for Pirs attachment to ISS and Kurs-P equipping facilities that ensure
rendezvous and docking of cargo vehicles are installed on the DC exterior.
Pirs has two frames with hatches for exit in
outer space. Each hatch, the bore diameter of which is 1000 mm, is closed
by a cover with a 228-mm window. Both hatches are designed for the same
purpose and are used depending on which side of Pirs DC it is more convenient
to exit in outer space. Hatch covers can be opened 120 times each. Pirs
DC exterior is equipped with hand rails. |
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There are thermal conditioning, communications, and
control systems, television and telemetry systems, end-to-end communication
cables and thermal conditioning piping inside Pirs Docking Compartment.
It also includes remote control panels of electric
power systems, lighting switches, electric outlets. Two coupling blocks
of the onboard docking system are used for locking of two Orlan-suited
crewmembers.
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Harmony Node-2 is the connection element between
two research laboratories: European “Columbus” and Japanese “Kibo” labs.
It provides electric power supply of said labs
and data exchange. For the purpose of ISS crew number increase an additional
life support system was installed in the module.
Besides, it is equipped with three additional
sleep stations.
Harmony Node technical characteristics:
- length – 7.3 m,
- mass – 14.3 tons.
Harmony node was delivered by Space Shuttle “Discovery”
during STS-120 on October 26, 2007. ISS-16 crew put Harmony node on the
permanent location – the forward docking node of Destiny Module on November
14, 2007. |
Columbus Orbital Facility
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| Columbus Module of ESA represents a research
laboratory for conduction of physical, bio-medical, material science and
other experiments under weightless conditions. The module hull is a cylinder
of 4.5 m in diameter, its length is 6.9 m, mass is 12.2 tons.
There are 10 standardized stowage bays for containers
with scientific facilities and equipment inside the module.
On the exterior of the module there are four places
for attachment of scientific equipment, which is intended for operation
under outer space conditions (investigation of solar-terrestrial relationship,
analysis of long-term space effects on equipment and materials, experiments
on germ surviving under extreme conditions, etc.)
The module is controlled by the European Center
in Oberpfaffenhofen, 60 km from Munich, Germany. Node-2 was delivered by
Space Shuttle “Atlantis” during STS-122 and on February 11, 2008 it was
docked to Harmony Module. Estimated in-orbit lifetime of the Node is 10
years. |
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Kibo (“Hope” in English) Experiment Module is
the first orbital research module of Japan. It is the biggest ISS module.
International abbreviation is JEM (Japanese Experiment
Module).
Kibo Module was designed by Japanese Aerospace
Exploration Agency (JAXA).
Kibo Module is intended for experiments and extensive
studies of the phenomena that occur on the Earth and in near-Earth space
(ozone layer status, global warming, crystallogenesis, microgravity and
radiation effects on plants, animals, and men, astronomical research, etc.).
Japanese Kibo Experimental Module comprises four
primary elements, they are:
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Research Laboratory (Pressurized Module (ÐÌ));
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Experiment Logistics Module (ELM), which includes:
ELM - Pressurized Section (ELM-PS) and
ELM - Exposed Section (ELM-ES);
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JEM Remote Manipulator System (JEMRMS);
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Exposed Facility (EF).
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Research Laboratory of the Kibo
represents pressurized cylindrical module (ÐÌ) 11.2 m in length and 4.4
m in diameter, where experiments are prepared and performed. Four astronauts
can work in the lab simultaneously.
Pressurized Section of the Experiment Logistics
Module (ELM-PS) is 4.2 m in length and 4.4 m in diameter; it is docked
to the upper hatch of the PM and is intended for storing equipment and
spare tools, and also experimental results.
Exposed Section of the Experiment Logistics
Module (ELM-ES), docked to the end face of the Exposed Facility (EF),
is used as a storage of experimental facilities and samples for future
experiments on EF.
Up to three different experimental facilities
can be stored in an unpressurized section (ELM - ES).
ELM – ES with experimental results and samples
in it can be undocked from EF and returned to earth aboard Space Shuttle.
Remote Manipulator System (JEMRMS) is attached
to the end face of the research laboratory and intended for equipment transfer
between ELM-ES and EF. The main part of the “arm” is used for transfer
of the hard objects and the small removable “arm” is used for finer work.
The “arm” is equipped with a camcorder, which helps to control its movements
accurately.
Exposed Facility (EF) is placed just next
to the lab module and used for accommodation of equipment, intended for
scientific and technical experiments under microgravity and outer space
conditions, as well as the Earth exploration, communication. Experimental
facilities, installed on EF, may be replaced or removed by means of the
Remote Manipulator System.
Poisk Small Research Module (MIM2)
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Poisk Small Research Module (MIM2) is
an element of ISS Russian Segment. It was designed and built by S.P.Korolev
RSC-Energy.
Purpose
Poisk Small Research Module is purposed for the
following:
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conduction of scientific-applied research and experiments
inside and outside of the module;
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use as an airlock compartment for spacewalks of two
Orlan-suited crew members;
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creation of an additional port for docking of manned
Soyuz transport vehicles and automatic Progress cargo vehicles to ISS.
Technical characteristics of the Module:
- internal volume – 12.5 m3;
- length – 4.05 m;
- diamenter – 2.55 m,
- number of EVA hatches – 2.
Poisk Module has two (active and passive) docking
nodes aligned along its longitudinal axis. Exit hatches are located on
the starboard and portside of the module. For convenience there are hand
rails inside and outside. Hatch covers are opened inward of the module.
Propellant refilling transit lines are laid through the module.
Poisk Research Module was delivered on ISS as
a part of automatic Progress-M /MIM2 cargo vehicle-module, designed on
the basis of Progress-M vehicle, and attached to the zenith (upper) docking
node of Zvezda Service Module’s transfer compartment. |
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Tranquility Module was delivered on ISS on February
10, 2010.
Inside Tranquility habitation module there is
a life support system, which reworks waster liquids into water for residential
use and also produces breathing oxygen. Besides, Tranquility Module has
a lavatory and air purification system, which purifies and monitors air
make-up inside the module.
Technical characteristics of the Module:
- mass – 15.5 tons;
- length – 6.7 m;
- diameter – 4.4 m.
Tranquility Module has six docking nodes. It is docked
to Unity Node using one of the axial docking nodes. Cupola all-round view
module is docked to the lower docking node of Tranquility Module. There
are eight 2-meter racks inside the module: two racks are used for installation
of the module control equipment, the rest – for installation of ISS status
monitoring system and parts of ISS life support control system (air-circulating
system, oxygen production system, waste utilization system, water reprocessing
system, ect.). |
Cupola Module is designed for observation
of the Earth, cosmic space, men, performing EVA, and technical facilities
in outer space. It represents all-round view cupola, which has seven transparent
quartz glass windows 10 centimeter thick. Windows are arranged as follows:
one round window is amidmost; six trapezoidal windows are arranged about
it. Covers protect them from micrometeorites and space debris impacts.
Audiovisual control systems, ISS temperature condition control system,
and Canadarm-2 robotic manipulator control working stations are installed
inside the module. The whole construction is two meters in diameter and
1.5 meters high. Its mass is 1.8 tons.
Cupola and Tranquility Modules were delivered
on ISS by Space Shuttle “Endeavour” on February 10, 2010. |
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ITS was deployed in the course of many
missions. It is the element of ISS American Segment, which provides the
attachment of modules, payloads, and system equipment. Connectors, radiators,
external payloads, and batteries are installed on the truss. The truss
sections are marked according to their location at port side or starboard
Assembled ITS truss comprises:
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central section - S0;
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five starboard section - S1, S3,
S4,
S5, S6;
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five port side section - Ð1, Ð3,
Ð4,
Ð5, Ð6.
Producer – Boeing Company.
During the truss deployment Z1 zenith segment
will be used.
ITS sections were delivered and positioned on
ISS in the following order.
SO Central Section
This section was delivered on orbit on April 10,
2002 during STS-100 and installed on ISS on April 11, 2002 by Atlantis
Space Shuttle crew. It is designed to provide a rigid connection between
ITS truss and laboratory module and an interface between ITS and a whole
station as well.
S1 Starboard Section
This section was delivered on orbit on October 9,
2002 during STS-112 and installed on ISS on October 10, 2002 by Atlantis
Space Shuttle crew. It is designed to provide electrical power and data
transmission from other sections, accommodate radiators and pipelines of
the external active thermal control system.
S1 Starboard Section is attached to S0 Central
Section.
Z1 Zenith Segment
This segment was delivered on orbit on October11
9, 2000 during STS-92 and installed on ISS on October 14, 2000 by Discovery
Space Shuttle crew. It is designed to provide operation of communication
and telemetry system, motion control system, electrical power supply, thermal
control, EVAs. â îòêðûòîì êîñìîñå.
Z1 Zenith Segment is installed on the zenith
docking unit of Unity Node.
P1 Port Side Section
This section was delivered on orbit on November 24,
2002 during STS-113 and installed on ISS on November 26, 2002 by Endeavour
Space Shuttle crew. It is designed to provide electrical power and data
transmission from other sections, accommodate radiators and pipelines of
the external active thermal control system.
P1 Portside Section is attached to S0 Central
Section.
P6 Port Side Section
This section was delivered on orbit on December 1,
2000 during STS-97 and installed on ISS on December 3, 2000 by Endeavour
Space Shuttle crew. It is designed to generate electrical power up to 64
kW.
P6 Portside Section is attached to Ð5 Section.
Ð3/Ð4 Portside Assembly
This assembly was delivered on orbit during STS-115
and installed on ISS on September 11, 2006.
It is designed to generate electrical power.
P3/P4 Portside Assembly is attached to Ð1 Section.
Ð5 Starboard Section
This section was delivered on orbit during STS-116
and installed on ISS in December, 2006. It is designed to generate electrical
power.
P5 Starboard Section is attached to Ð4 Section.
S3/S4 Portside Assembly
This assembly was delivered on orbit during STS-117
and installed on ISS on June 11, 2007. It is designed to generate electrical
power.
S3/S4 Portside Assembly is attached to S1 Section.
S5 Starboard Section
This section was delivered on orbit during STS-118
and installed on ISS on August 11, 2007. It is designed to generate electrical
power.
S5 Starboard Section is attached to S4 Section.
S6 Starboard Section
This section was delivered on orbit during STS-119
and installed on ISS on March 18, 2009. It is designed to generate electrical
power.
S6 Starboard Section is attached to S5 Section.
Assembly process of ITS was finished after S6
Section had been delivered and installed on ISS.
