IHI Aerospace Spacecraft Propulsion Products
IHI Aerospace
IHI Aerospace's full line of spacecraft and launch vehicle propulsion hardware, including monopropellant, bipropellant, cold-gas and electric (Hall) propulsion systems, thrusters, and propellant tanks, flight-proven since 1964.
Key figurescomparable across the catalogue
- Power
- 6,000 W
- Thrust
- 326 N
Normalised to common units so this product can be compared with others in its category. The supplier's own wording is below.
As published by the supplier
- Bipropellant systems - unar-a
- Launch Year: cancelled; Orbit: Lunar orbit; Propellant Load: N2H4 143 kg, NTO 49 kg; Thruster Configuration: 500N main engine, 20N x6, 1N x4
- Bipropellant systems - ets-vi
- Launch Year: 1994; Orbit: GEO; Propellant Load: N2H4 910 kg, NTO 825 kg; Thruster Configuration: 1700N main engine, 50N x4
- Bipropellant systems - j-i eve
- Launch Year: 1996; Orbit: Launcher; Propellant Load: N2H4 126 kg, NTO 120 kg; Thruster Configuration: 3600N main engine
- Bipropellant systems - comets
- Launch Year: 1998; Orbit: GEO; Propellant Load: N2H4 1030 kg, MON3 840 kg; Thruster Configuration: 1700N main engine, 50N x4, 1N x16
- Bipropellant systems - drts
- Launch Year: 2002; Orbit: GEO; Propellant Load: N2H4 973 kg, MON3 641 kg; Thruster Configuration: 500N LAE, 20N x8, 1N x16
- Bipropellant systems - ets-viii
- Launch Year: 2006; Orbit: GEO; Propellant Load: MMH 1120 kg, MON3 1849 kg; Thruster Configuration: 500N LAE, 22N x12
- Bipropellant systems - selene
- Launch Year: 2007; Orbit: Lunar orbit; Propellant Load: N2H4 960 kg, MON3 355 kg; Thruster Configuration: 500N LAE, 20N x12, 1N x8
- Bipropellant systems - winds
- Launch Year: 2007; Orbit: GEO; Propellant Load: N2H4 1460 kg, MON3 1067 kg; Thruster Configuration: 500N LAE, 20N x8, 4N x16
- Bipropellant systems - htv
- Launch Year: 2009-2020; Orbit: ISS orbit; Propellant Load: MMH 918 kg, MON3 1514 kg; Thruster Configuration: 500N main engine x4, 120N x28
- Bipropellant systems - htv-x
- Launch Year: 2025- (TBD); Orbit: ISS orbit; Propellant Load: MMH 981 kg, MON3 1619 kg; Thruster Configuration: 120N x24
- Bipropellant systems - mmx (outbound)
- Launch Year: 2026 (TBD); Orbit: Martian moon; Propellant Load: N2H4 916 kg, MON3 858 kg; Thruster Configuration: 450N x4
- Bipropellant systems - mmx (inbound)
- Launch Year: 2026 (TBD); Orbit: Martian moon; Propellant Load: N2H4 607 kg, MON3 531 kg; Thruster Configuration: 450N x2, 22N x20
- Monopropellant systems - ets-iv
- Launch Year: 1981; Propellant Load: 64 kg; Thruster: 18N x2
- Monopropellant systems - ets-iii
- Launch Year: 1982; Propellant Load: 18 kg; Thruster: 1N x12
- Monopropellant systems - mos-1
- Launch Year: 1987; Propellant Load: 18 kg; Thruster: 1N x14
- Monopropellant systems - ets-v
- Launch Year: 1987; Propellant Load: 113 kg; Thruster: 20N x2, 1N x16
- Monopropellant systems - cs-3 series
- Launch Year: 1988; Propellant Load: 118 kg; Thruster: 20N x4
- Monopropellant systems - mos-1b
- Launch Year: 1990; Propellant Load: 14 kg; Thruster: 1N x14
- Monopropellant systems - jers-1
- Launch Year: 1992; Propellant Load: 115 kg; Thruster: 1N x22
- Monopropellant systems - ets-vi
- Launch Year: 1994; Propellant Load: 115 kg; Thruster: 1N x16
- Monopropellant systems - adeos series
- Launch Year: 1996-; Propellant Load: 170 kg; Thruster: 20N x4, 1N x16
- Monopropellant systems - ets-vii
- Launch Year: 1997; Propellant Load: 440 kg; Thruster: 20N x28, 1N x12
- Monopropellant systems - mds-1
- Launch Year: 2002; Propellant Load: 24 kg; Thruster: 1N x4
- Monopropellant systems - oicets
- Launch Year: 2005; Propellant Load: 40 kg; Thruster: 1N x8
- Monopropellant systems - alos
- Launch Year: 2006; Propellant Load: 170 kg; Thruster: 4N x4, 1N x16
- Monopropellant systems - gosat
- Launch Year: 2008; Propellant Load: 115 kg; Thruster: 20N x4, 1N x8
- Monopropellant systems - gcom series
- Launch Year: 2012-; Propellant Load: 260 kg; Thruster: 4N x12
- Monopropellant systems - asnaro series
- Launch Year: 2014-; Propellant Load: 40 kg; Thruster: 4N x4
- Monopropellant systems - government program
- Launch Year: 2024-; Propellant Load: -; Thruster: 4N x8
- Launch vehicle rcs - n-i
- Launch Year: 1975-1982; Thruster Configuration: 18N x12
- Launch vehicle rcs - n-ii
- Launch Year: 1981-1987; Thruster Configuration: 18N x12
- Launch vehicle rcs - h-i
- Launch Year: 1986-1992; Thruster Configuration: 18N x12
- Launch vehicle rcs - h-ii
- Launch Year: 1994-1999; Thruster Configuration: 50N x8, 18N x2
- Launch vehicle rcs - h-iia
- Launch Year: 2001-; Thruster Configuration: 50N x8
- Launch vehicle rcs - h-iib
- Launch Year: 2009-2020; Thruster Configuration: 50N x8
- Launch vehicle rcs - epsilon (Post Boost Stage)
- Launch Year: 2013-; Thruster Configuration: 50N x8
- Launch vehicle rcs - h3
- Launch Year: 2023-; Thruster Configuration: 50N x8
- Launch vehicle rcs - kairos (Payload Acceleration Module)
- Launch Year: 2024-; Thruster Configuration: 20 N x8
- Cold gas - hyflex
- Launch Year: 1996; Propellant: GN2; Thruster Configuration: 40N x6
- Cold gas - ets-vii
- Launch Year: 1997; Propellant: GN2; Thruster Configuration: 20N x28, 1N x12
- Cold gas - dash
- Launch Year: 2002; Propellant: GN2; Thruster Configuration: 1N x1
- Cold gas - ikaros
- Launch Year: 2010; Propellant: HFC-134a; Thruster Configuration: 1N x8
- Cold gas - ss-520 series
- Launch Year: 1998-; Propellant: GN2; Thruster Configuration: 23N x1-4
- Bipropellant thruster bt-4
- Propellant: Hydrazine/NTO; Thrust: 450 N; Isp: 326s; Inlet pressure: F >1.69 MPa, O >1.62 MPa; Demonstrated life: 32850s; Status: Flight proven
- Bipropellant thruster bt-6
- Propellant: Hydrazine/NTO; Thrust: 21.5 N; Isp: 295s; Inlet pressure: 1.69 MPa; Throughput: 583 kg; Status: Flight proven
- Bipropellant thruster hbt-5
- Propellant: MMH/MON3; Thrust: 478 N; Isp: 316s; Inlet pressure: 1.72 MPa; Demonstrated life: 15000s; Status: Flight proven
- Bipropellant thruster hbt-1
- Propellant: MMH/MON3; Thrust: 124.4 N; Isp: 274.9s; Inlet pressure: 2.05 MPa; Demonstrated life: 40000s; Throughput: 446 kg; Status: Flight proven
- Monopropellant thruster mt-9
- Thrust: 0.29-1.13N; Isp: 208-215s; Number of pulses: >850,000; Throughput: >100 kg; Status: Flight proven
- Monopropellant thruster mt-8a
- Thrust: 1.80-5.01N; Isp: 212-225s; Number of pulses: >850,000; Throughput: >190 kg; Status: Flight proven
- Monopropellant thruster mt-2
- Thrust: 6.9-19.6N; Isp: 210-226s; Number of pulses: >261,914; Throughput: >115 kg; Status: Flight proven
- Monopropellant thruster mt-2b
- Thrust: 24.5 N; Isp: >211s; Number of pulses: >7500; Throughput: >15 kg; Status: Qualified
- Monopropellant thruster mt-6
- Thrust: 23-50N; Isp: 215-225s; Number of pulses: >14,800; Throughput: >120 kg; Status: Flight proven
- Monopropellant thruster mt-6a
- Thrust: 50 N; Isp: 225s; Number of pulses: >14,000; Throughput: >107 kg; Status: Flight proven
- Propellant tank - 3l
- Volume: 3L; Size: 182 ID Sphere; Internal device: Diaphragm; Mount type: Boss; Status: Flight proven
- Propellant tank - 37l (Tabs)
- Volume: 37L; Size: 420 ID Sphere; Internal device: Diaphragm; Mount type: 3 Tabs (Lugs); Status: Flight proven
- Propellant tank - 37l (Pedestal)
- Volume: 37L; Size: 420 ID Sphere; Internal device: Diaphragm; Mount type: Pedestal; Status: Flight proven
- Propellant tank - 67l
- Volume: 67L; Size: 420 ID x 750 length mm; Internal device: Diaphragm; Mount type: Pedestal; Status: Flight proven
- Propellant tank - 74l (Tabs)
- Volume: 74L; Size: 420 ID x 754 length mm; Internal device: Diaphragm; Mount type: 4 Tabs (Lugs); Status: Flight proven
- Propellant tank - 74l (570 ID)
- Volume: 74L; Size: 570 ID x 500 length mm; Internal device: Diaphragm; Mount type: 4 Tabs (Lugs); Status: Qualified
- Propellant tank - 141l
- Volume: 141L; Size: 650 ID Sphere; Internal device: Diaphragm; Mount type: 3 Tabs (Lugs); Status: Flight proven
- Propellant tank - 169l
- Volume: 169L; Size: 650 ID x 750 length mm; Internal device: Diaphragm; Mount type: 3 Tabs (Lugs); Status: Qualified
- Propellant tank - 427l
- Volume: 427L; Size: 820 ID x 1087 length mm; Internal device: Channel mesh; Mount type: 4 Tabs (Lugs); Status: Flight proven
- Propellant tank - 552l
- Volume: 552L; Size: 1020 ID Sphere; Internal device: Channel mesh; Mount type: 4 Tabs (Lugs); Status: Flight proven
- Propellant tank - 726l
- Volume: 726L; Size: 1020 ID x 1316 length mm; Internal device: Channel mesh; Mount type: 4 Tabs (Lugs); Status: Qualified
- Tank internal devices
- Diaphragm (SiO2-free diaphragm under development); Surface tension channel mesh
- High power hall thruster - 6kw BOL
- Propellant: Xe; Electrical Power: 6 kW; Thrust Level: >359 mN@BOL; Isp: >1783s@BOL; Status: Qualified
- High power hall thruster - 6kw mol
- Propellant: Xe; Electrical Power: 6 kW; Thrust Level: >330 mN@MOL; Isp: >1712s@MOL; Status: Qualified
- High power hall thruster - 4kw BOL
- Propellant: Xe; Electrical Power: 4 kW; Thrust Level: >230 mN@BOL; Isp: >1673s@BOL; Status: Qualified
- High power hall thruster - 4kw mol
- Propellant: Xe; Electrical Power: 4 kW; Thrust Level: >219 mN@MOL; Isp: >1589s@MOL; Status: Qualified
- High power hall thruster - 4kw EOL
- Propellant: Xe; Electrical Power: 4 kW; Thrust Level: >212 mN@EOL; Isp: >1539s@EOL; Status: Qualified
About
IHI Aerospace is described as the leading manufacturer of propulsion systems in Japan, developing and manufacturing spacecraft propulsion systems since 1964. The company offers monopropellant, cold-gas, bipropellant and electric propulsion systems, all flight qualified, for satellites and rockets. Over 40+ years IHI Aerospace has developed and built over 100 propulsion systems plus their thrusters and tanks. Systems have been used for orbit control and reaction control of spacecraft (including H-II Transfer Vehicles, HTV), reaction control of launch vehicles, and control for re-entry capsules. Bipropellant propulsion systems use hydrazine (N2H4) with mixed oxides of nitrogen (MON3) since the 1980s, combining a bipropellant apogee engine with monopropellant thrusters for reaction control; MMH/MON3 bipropellant systems have been used on HTV, equipped with four main thrusters meeting ISS safety requirements. Monopropellant hydrazine propulsion systems have been produced since the 1960s using IHI Aerospace’s own tanks and thrusters, flown on missions since 1981. Launch vehicle reaction control systems (RCS) have been developed for over 50 years and flown on N-I, N-II, H-I, H-II, H-IIA, H-IIB, Epsilon, H3 and KAIROS launch vehicles. Cold gas propulsion systems for small satellites and sounding rockets use GN2 or liquefied gas (HFC-134a) propellant to reduce cost and tank volume. Bipropellant thrusters (over 400 delivered since the 1980s) include the 450N and 22N hydrazine/MON3 thrusters for GEO satellites (widely used by US satellite manufacturers), the 1700N N2H4/MON apogee engine (first delivered in the 1980s), and the 490N/120N MMH/MON thrusters developed for HTV. Monopropellant thrusters (over 1,100 launched since the 1960s) range from 1N to 50N thrust. Propellant and pressurant tanks have been produced since 1964, with over 200 tanks launched, ranging from 3 to 726 liters, using diaphragm or surface-tension channel-mesh propellant management devices (PMDs); a SiO2-free diaphragm is under development. Electric propulsion thrusters have been designed and manufactured since 1983, with a high-power Hall Thruster (4kW and 6kW variants) currently under development for all-electric satellites. Manufacturing and testing capabilities include a firing test stand for apogee engines, a firing test stand for small thrusters with 3 vacuum chambers, and a sea-level stage firing test stand, plus launch site support for propellant loading and post-delivery testing.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.