Feature

The Crew Return Vehicle is a higly automated reusable spacecraft that serves as a space ambulance, life boat and alternate return vehicle for the crew on the International Space Station. The Crew Return Vehicle provides space for up to 7 astronauts.

NOTE: Since data for the real CRV is not yet available this fact sheet is largely based on the X-38, the CRV's prototype.
 

Dimensions   Crew Return Vehicle length 9144 mm Crew Return Vehicle width 4420 mm de-orbit-propulsion stage length 1829 mm Cabin internal volume 11.8 m3 Mass budget   Crew Return Vehicle mass 11 340 kg De-orbit propulsion stage mass 2722 kg

 
 

Propulsion   De-orbit propellant Mono-propellant Hydrazine Attitude control system Pressure regulated Nitrogen cold gas thrusters 922 x 111 N each)

 
 

Communications infrastructure     S-band   Ku band TDRS satellite

 
 

Environmental control   Max. number of crew members 7 Cabin temperature 18° - 27° C (Attached to ISS) up to 28° C after landing Air pressure 958 - 1013 hPa CO2 and CO removal Lithium Hydroxide cartridge H2O vapor removal Charcoal cartridge Medical facilities Ambulance style first aid can be administered

 
 

Electrical power     Launch phase Power provided by Space Shuttle atttached to ISS: Dormant mode (monthly low power maintenance checks from ISS) De-orbit and descent Power provided by 4 rechargeable Lithium batteries

 
 

Main construction material   Pressure shell Internal structure Various composite materials Thermal protection Ceramic Matrix Composite (CMC), Thermal tiles and Thermal blankets

 
 

Main European contractor   MAN Technology (Bremen, Germany) and Alenia (Turin, Italy) Leading 22 industrial companies in eight countries

 
 

Launch configuration   Launch Vehicle Space Shuttle   Launched inside the orbiter's cargo bay and berthed to ISS with the Space Station Remote Manipulator Launch site Kennedy Spce Center (Florida, USA) First flight mid 2007 Flight rate 1 per 3 years

 
 

On orbit configuration     Attached in stand-by mode to Node 3   Port-port for a period of 3 years Maximum mission duration for emergency departure 9 hours Maximum mission duration for medical return 3 hours (because this allows time for optimum sequencing between ISS departure and re-entry burn) Maximum tumbling rate of ISS still to allow separation 2°/s

 
 

Landing configuration     Control during flight and landing Autonomous with manual interference   Attitude control Cold gas and Air surfaces (which take over in denser regions of the atmosphere) Parafoil area 685 m3 Drogue chute deployment at 8 km. altitude     Main chute deployment at 7 km. altitude in 5 steps Landing gear 3 skis   Landing accuracy < 9 km radius   Horizontal landing speed < 4.6 m/s   Flight hardware (European built) Fin structure, Fin folding mechanism     Aft structure design     Ceramic Matrix Composite (CMC) rudder, body flaps and nose cone     Trunnion retraction mechanism     Aerodynamic and Aerothermodynamic database     Landing gear system     Crew seats     International berthing/docking mechanism development model     Cockpit display technique development     Avionics (architectural support)

 
 
Last update: 19 July 2004