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Assembly Integration and Test

Thrust Chambers
Cryogenic valves


Rocket Engine Cryogenic Valves

Assembly, integration and test at Astrium's Ottobrunn facility.

 

Test

AIT 6Valve testing is performed in conjunction with specially developed test stands, state-of-the-art measuring equipment, data recording and test data evaluation.

Typical tests include:

  • Pressure tests using nitrogen and helium up to 300 bar.
  • Leak tightness tests using helium mass spectrometers in the temperature range from +100 C deg to approximately -270 C deg.
  • Thermal tests from +180 C deg. to -196 C deg.
  • Follow-through tests in the range around -150 C deg.
    - with gaseous nitrogen up to 2,000 g/sec.
    - with gaseous helium up to 800 g/sec.
  • Functional testing of electromagnetic and pneumatic valve systems.

 

Facilities

AIT 5Valve integration facilities include:

  • Clean room class 1000.
  • 3-axis interface measuring machine having an accuracy of 2 µm.
  • Vacuum drying chamber with GN2 supply.
  • Force / stroke test stand.
  • Cleaning facility with ultrasonic baths and hot air drying oven.
  • Clean bench equipment - class 100.
  • Endoscopic equipment with video recording.

It is necessary to inspect valves after the official acceptance test to be able to guarantee that the function of the valve is not impaired by, for example - rinsed out fuel particles. The follow-through area and the internal valve area are designed for particles larger than 30 µm.

 

 Valve Test facilities include:

Test stands dedicated to each type of valve tested. for example:

  • Liquid nitrogen test stand for the Ariane 5 Vulcain main feed valve
AIT 7

 

 

 

Temperature Range:
Media:
Pilot Pressure Feed Valve:
Pilot Pressure Chilldown Valve
Media Pressure:
Leakage internal:
Leakage external:

77 - 293 K
GHe
< 105 bar
< 45 bar
< 25 bar
0.001 - 200 cm3/sec
> 10-5 mbar/sec
  • Force versus Stroke Test Stand for Feed, Isolation and NW70 Valve.

Force:
Stroke:

< 5,000 N
100 mm
  • Thrust / Mass flow Measurement Test Stand for Roll Control Assembly.

Thrust:
Mass flow:
Operating Media:

< 2,000 / 5,000 N
< 1,000 g/sec
GHe

 

 

Contact for Further Information


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