RocketEngines: Difference between revisions

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m (typo fix)
(New colon on soyuz engine and new ignition row.)
Line 10: Line 10:
|'''Company'''
|'''Company'''
!Rocketdyne
!Rocketdyne
!NPO Energomash
!XCOR
!XCOR
!XCOR
!XCOR
Line 16: Line 17:
|'''Model'''
|'''Model'''
|[http://en.wikipedia.org/wiki/SSME SSME]
|[http://en.wikipedia.org/wiki/SSME SSME]
|[http://www.astronautix.com/engines/rd178d74.htm RD-107] series (Soyuz)
|[http://www.xcor.com/products/engines/4A3_LOX_alcohol_rocket_engine.html XR-4A3 (EZ-rocket)]
|[http://www.xcor.com/products/engines/4A3_LOX_alcohol_rocket_engine.html XR-4A3 (EZ-rocket)]
|[http://www.xcor.com/products/engines/5K18_LOX-kerosene_rocket_engine.html XR-5K18 (Lynx)]
|[http://www.xcor.com/products/engines/5K18_LOX-kerosene_rocket_engine.html XR-5K18 (Lynx)]
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|'''Propellants'''
|'''Propellants'''
|LOX & LH2
|LOX & LH2
|LOX & Kerosene
|LOX & Alcohol
|LOX & Alcohol
|LOX & Kerosene
|LOX & Kerosene
Line 30: Line 33:
|'''Tank pressurization'''
|'''Tank pressurization'''
|Yes, with O2 and H2 gases
|Yes, with O2 and H2 gases
|Yes, with Nitrogen
|No
|No
|No
|No
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|'''Fuel pump'''
|'''Fuel pump'''
|Turbopump
|Turbopump
|Turbopump driven by gaz generator using hydrogen peroxide decomposition
|Piston pump
|Piston pump
|Piston pump
|Piston pump
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|'''Cooling'''
|'''Cooling'''
|Regenerative w/ LH2 in three stages
|Regenerative w/ LH2 in three stages
|Regenerative?
|Regenerative (w/ Alcohol?)
|Regenerative (w/ Alcohol?)
|Regenerative w/ Kerosene
|Regenerative w/ Kerosene
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|'''Chamber metal'''
|'''Chamber metal'''
|Copper or iron?
|Copper or iron?
|Copper?
|Copper
|Copper
|Copper
|Copper
|?
|-
|'''Ignition system'''
|?
|Pyrotechnic, soon hypergolic
|?
|?
|?
|?
|-
|-
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|'''Energy'''
|'''Energy'''
|Hydraulic
|Hydraulic
|?
|
|
|
|
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|'''Provided by'''
|'''Provided by'''
|Engine's turbopumps
|Engine's turbopumps
|?
|
|
|
|
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|'''Actuator'''
|'''Actuator'''
|six hydraulic servoactuators
|six hydraulic servoactuators
|?
|None
|None
|None
|None
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|'''Valves'''
|'''Valves'''
|Hydraulically or pneumatically (helium) actuated
|Hydraulically or pneumatically (helium) actuated
|?
|?
|?
|?
|?

Revision as of 08:24, 17 November 2010

Rocket Engine

The general principle may be simple, but there are numerous ways of achieving it. Different features and properties differ between existing rocket engines, and they all have consequences on complexity of manufacturing, complexity of operation, cost and weight for example.

We gather in this table the main properties of existing rocket engines.

Rocket engines features
Company Rocketdyne NPO Energomash XCOR XCOR Armadillo
Model SSME RD-107 series (Soyuz) XR-4A3 (EZ-rocket) XR-5K18 (Lynx) LOX/methane (no name)
Combustion
Propellants LOX & LH2 LOX & Kerosene LOX & Alcohol LOX & Kerosene LOX & LCH4
Tank pressurization Yes, with O2 and H2 gases Yes, with Nitrogen No No Yes, with Helium
Fuel pump Turbopump Turbopump driven by gaz generator using hydrogen peroxide decomposition Piston pump Piston pump No
Cooling Regenerative w/ LH2 in three stages Regenerative? Regenerative (w/ Alcohol?) Regenerative w/ Kerosene ?
Chamber metal Copper or iron? Copper? Copper Copper ?
Ignition system ? Pyrotechnic, soon hypergolic ? ? ?
Actuators
Energy Hydraulic ? Electric
Provided by Engine's turbopumps ? ?
Actuator six hydraulic servoactuators ? None None Servo-motor
Others
Valves Hydraulically or pneumatically (helium) actuated ? ? ? ?

Pumps and tank pressurization

In order to get fuel from the tanks into the combustion chamber, the tanks must be either pressurized or the fuels pumped. In some cases, both techniques are used. The choice for this concern has a large impact on the design of the engine's hardware, and the complexity of manufacturing and operations.

Traditionnaly, only turbo pumps have been able to feed the engine at a large enough rate. Innovative solutions appeared in research projects or private space projects, like the use of piston pumps for LOX or simple pressurization using liquid helium.

Several possibilities exist for tank pressurization:

  • vaporization of liquid propellants back into their own tanks
  • external vaporization of inert gas like Helium (can Nitrogen be used for that?)
  • smoke generator, that basically react fuel and oxidizer and use the resulting smoke for pressurization.

Cooling

Regenerative cooling is most widely used in rocket engines.

Few of them however use other ways, like ablatively cooling carbon fiber composite in SpaceX Merlin 1A engine, or radiative cooling in the Merlin Vacuum nozzle (still regenerative for the chamber).