Satellite Launch Vehicle Engines

23 Satellite Launch Vehicle Engines for Space Applications from 7 manufacturers listed on SatNow

Satellite Launch Vehicle Engines for space applications from multiple manufacturers are listed on SATNow. Use the filters to select products based on your requirement. View product details, download datasheets, compare products, get quotes and pricing for matching products. SATNow has compiled this list of products specifically for Space and Satellite Applications.

Description:BE-3U (Upper stage), optimized to operate in the vacuum of space. With a back-to-back turbine assembly and a larger nozzle
Vacuum Thrust:
710 kN (160, 000 lbf), 490 kN (110, 000 lbf) thrus...
Propellant:
Liquid Oxygen, LOX-LH2
more info
Description:It is a European demonstrator for a very low cost, potentially reusable engine
Propellant:
LOX, Methane
more info
Description:MB-XX is a new family of cryogenic upper stage rocket engines jointly developed by MHI Group and Aerojet Rocketdyne
Vacuum Thrust:
155687.76 to 266893.3 kN(35, 000 - 60, 000 lbf)
Specific Impulse:
467 sec (Isp (vacuum)
Propellant:
Liquid Oxygen, LOX-LH2
more info
Description:The engine is additively manufactured using just three parts, providing a low-cost solution for reusable launch vehicles
Vacuum Thrust:
111205.54 kN (25, 000 lbf)
Propellant:
Liquid Oxygen, Liquid Methane
more info
Description:STAR-3Dâ„¢ hybrid rocket engines are produced by 3D printing fuel grains using thermoplastic material.
more info
Description:European Space Agency (ESA) program in collaboration with the French national space agency (CNES)
Propellant:
Liquid Oxygen, Liquid Methane
more info
Description:Campus co-locates engineering, manufacturing, & testing operations
Vacuum Thrust:
22.24 kN (5, 000 lbf THRUST, SEA LEVEL)
Propellant:
LOX, Kerosene
more info
Description:BE-4 is the most powerful liquefied natural gas (LNG) fueled rocket engine ever developed.
Vacuum Thrust:
2, 400 kN (550, 000 lbf)
Propellant:
LNG
more info
Description:The Aestus engine powers the Ariane 5 ES version bipropellant upper stage for insertion of payloads into LEO, SSO and GTO
Vacuum Thrust:
29.6 kN
Specific Impulse:
324 sec
Engine Mass:
111 Kg (Thrust Chamber Mass)
Height:
2.2 m
Nozzle Outlet Diameter:
1.31 m
Propellant:
N2O4, MMH
Propellant Flow Rate:
9.3 Kg/sec
Space Heritage:
Yes
more info
Description:The LE-7A rocket engine, developed for the first stage of the H-II rocket and has a two stage burning cycle system
Vacuum Thrust:
1115.96 kN (112 ton)
Specific Impulse:
440 sec (Isp (vacuum)
Engine Mass:
1, 780 Kg (Weight)
Propellant:
Liquid Oxygen, LOX-LH2
more info

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Propellant Flow Rate (Kg/sec)

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Space Heritage