Versatile permanently inhabited research institute in Low Earth Orbit The European participation in the International Space Station PROJECT : TITLE : Final Configuration DOCUMENT N°: International Space Station International Space Station (ISS) Specification The International Space Station is a versatile research institute and a large observation platform in outer space for scientific research and applications. It also serves as a test centre to facilitate introduction of new technologies. This permanently human occupied outpost in outer space should also serve as a stepping stone for further space exploration. Automated Transfer Vehicle (ATV): Resupplies and services the Space Station Payloads on Express Pallets, which house external experiments Node 3: Connects several modules European Robotic Arm (ERA): Installs equipment and supports astronauts Data Management System in Russian (DMS-R) Zvezda module Cupola: Allows observation of Space Station exterior, space and the Earth Columbus Laboratory: Houses experiment racks and external platforms Microgravity Facilities for Columbus: provides experiment capabilities Multi-Purpose Logistics Module (MPLM): Resupplies the Space Station after being installed by the Space Shuttle Node 2: Connects several modules US Space Shuttle: manned spacecraft for up to 7 astronauts and equipped with the Multi Purpose Logistics Module (MPLM), the Un-pressurized Logistics Carrier (ULC) or other space station structural parts in its cargo bay. Partners: Canada, Canadian Space Agency (CSA) Europe, European Space Agency (ESA) representing 11 of the 17 member states Japan, Japan Aerospace Exploration Agency (JAXA) Russia, Roscosmos USA, National Aeronautics and Space Administration (NASA) UIC-ESA-FSH-001 REV. 1.2 ERASMUS User Centre and Communication Office - Directorate of Human Spaceflight, Microgravity and Exploration Programmes www.spaceflight.esa.int/users Illustrations: ESA/D. Ducros Available launch vehicles: European Ariane-5 launcher Japanese H-IIA launcher Russian Proton launcher Russian Soyuz launcher United States Space Shuttle Available transport vehicles for crew and/or supplies: European Automated Transfer Vehicle (ATV): servicing and logistics vehicle Japanese HII Transfer vehicle (HTV): servicing and logistics vehicle Russian Soyuz vehicle: manned space craft that accommodates 3 cosmonauts New rescue vehicle Russian Progress vehicle: servicing and logistics vehicle
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Versatile permanently inhabited research institute in Low Earth Orbit
The European participation in the International Space Station
PROJECT :
TITLE : Final Configuration
DOCUMENT N°:
International Space Station
International Space Station (ISS)Specification
The International Space Station is a versatile research institute and a large observation platform in outer space for scientific research and applications. It also serves as a test centre to facilitate introduction of new technologies. This permanently human occupied outpost in outer space should also serve as a stepping stone for further space exploration.
Automated Transfer Vehicle (ATV):
Resupplies and services the
Space Station
Payloads on Express Pallets, which house external experiments
Node 3:Connects several
modules
European Robotic Arm (ERA):
Installs equipmentand supports
astronauts
Data Management System inRussian (DMS-R) Zvezda
module
Cupola:Allows observation of Space Station exterior, space and the Earth
Columbus Laboratory:Houses experiment racks
and external platforms
Microgravity Facilities for Columbus: provides
experiment capabilities
Multi-Purpose Logistics Module (MPLM):
Resupplies the Space Station after being
installed by the Space Shuttle
Node 2:Connects
severalmodules
US Space Shuttle: manned spacecraft for up to 7 astronauts and equipped with the Multi Purpose Logistics Module (MPLM), the Un-pressurized Logistics Carrier (ULC) or other space station structural parts in its cargo bay. Partners:
Canada, Canadian Space Agency (CSA) Europe, European Space Agency (ESA) representing 11 of the 17 member states Japan, Japan Aerospace Exploration Agency (JAXA) Russia, Roscosmos USA, National Aeronautics and Space Administration (NASA)
UIC-ESA-FSH-001
REV.
1.2
ERASMUS User Centre and Communication Office - Directorate of Human Spaceflight, Microgravity and Exploration Programmeswww.spaceflight.esa.int/users
Illus
trat
ions
: ES
A/D
. Duc
ros
Available launch vehicles:
European Ariane-5 launcher Japanese H-IIA launcher Russian Proton launcher Russian Soyuz launcher United States Space Shuttle
Available transport vehicles for crew and/or supplies:
European Automated Transfer Vehicle (ATV): servicing and logistics vehicle Japanese HII Transfer vehicle (HTV): servicing and logistics vehicle Russian Soyuz vehicle: manned space craft that accommodates 3 cosmonauts New rescue vehicle Russian Progress vehicle: servicing and logistics vehicle
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43938455611530
3296
7
4489
0 3731
8
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714
Dimensions and mass:
Width: 108 m Length: 74 m (~88 m incl. ATV or Progress) Height: 45 m Pressurized volume: 1.200 m3
Total mass at completion:~ 450.000 kg
Propulsion
Monomethyl hydrazine fuel and Nitrogen tetroxide oxidizer for orbit raise and attitude control when the Control Moment Gyros or Gyrodynes are not used or to unload them. To prevent wearout of the Stations rocket motors, attitude control and re-boost functions are also perfor- med by visiting spacecraft such as the European Automated Transfer Vehicle, the Soyuz, Progress and Space Shuttle.
Communications infrastructure
TDRS: 50 Mbps Ku-band link (up-link and down link with the same bit-rate) 192 kbps S-band down-link 72 kbps S-band up-link Environmental control
Permanent crew: 6 (after completion) Internal pressure: 958 - 1013 hPa Internal temperature: 18°C - 27°C Temperature and humidity control, Carbon dioxide removal, Trace contaminants control, Atmosphere components monitoring, Oxygen production, Waste water processing to potable water, Pre-treated urine to urine distillate processing Crew urine and fecal collection and processing
Electrical power
Maximum power output: 110 kW (Provided by large solar arrays. Power is converted to 120 V DC by the station)
Launch configuration
Launched in components on different launch vehicles, provided by 4 of the 5 participating partners and assembled in orbit. 1st launch: 20 November 1998 Assembly complete: 2010
On orbit configuration
Final assembled configuration as shown in drawings Orbital altitude: 370 - 460 km Orbital inclination: 51.6° Orbital velocity: 7.7 - 7.6 km/s (~ 27.500 km/h) Attitude: Torque equilibrium attitude control and X-vector in velocity direction
PROJECT: SCALE : 1: 750
DIMENSIONS : mm
TITLE: DOCUMENT N° :
International Space Station
Final Configuration UIC-ESA-FSH-001
REV.
1.2
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Specifications
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