Spacecraft Propulsion Products
IHI Aerospace is the leading manufacturer of propulsion systems in Japan
and has been developing and manufacturing spacecraft propulsion systems since 1964.
We offer monopropellant, cold-gas, bipropellant
and electric propulsion systems with flight qualified products for satellites and rockets.
Spacecraft Propulsion Systems
Our spacecraft propulsion systems have been used in a wide range of missions for over 40 years. IHI Aerospace has developed and built over 100 propulsion systems as well as its thrusters and tanks.
Our propulsion systems and sub-systems have been used for:
- ●Orbit control and reaction control of spacecraft including H-II transfer vehicles (HTV）
- ●Reaction control of launch vehicles
- ●Control for re-entry capsules.
Bipropellant Propulsion Systems
IHI Aerospace developed and manufactured bipropellant propulsion systems with hydrazine N2H4 and mixed oxides of nitrogen MON3 since1980s. These systems have a bipropellant apogee engine and monopropellant thrusters for reaction control. We have also developed and manufactured bipropellant propulsion systems with mono methyl hydrazine MMH and MON3. The MMH/MON3 bipropellant propulsion system has been used for ETS-Ⅷ satellite and H-II Transfer Vehicles (HTV). The HTV propulsion system is equipped with four main thrusters and fully meets the safety requirements of the ISS.
| Program | Launch Year |
Orbit | Propellant Load [kg] |
Thruster Configuration |
|---|---|---|---|---|
| UNAR-A | cancelled | Lunar orbit | N2H4 :143 NTO: 49 |
500N main engine, 20N x 6, 1N x 4 |
| ETS-VI（LAPS） | 1994 | GEO | N2H4 : 910 NTO: 825 |
1700N main engine. 50N x 4 |
| J-I EVE | 1996 | Launcher | N2H4 : 126 NTO : 120 |
3600N main engine |
| COMETS（UPS） | 1998 | GEO | N2H4 : 1030 MON3 : 840 |
1700N main engine. 50N x 4, 1N x 16 |
| DRTS（UPS） | 2002 | GEO | N2H4 : 973 MON3 : 641 |
500N LAE 20N x 8, 1N x 16 |
| ETS-VIII（BPS） | 2006 | GEO | MMH : 1120 MON3 : 1849 |
500N LAE 22N x 12 |
| SELENE（UPS） | 2007 | Lunar orbit | N2H4 : 960 MON3 : 355 |
500N LAE 20N x 12, 1N x 8 |
| WINDS（UPS） | 2007 | GEO | N2H4: 1460 MON3 : 1067 |
500N LAE 20N x 8, 4N x 16 |
| HTV（BPS） | 2009~2020 | ISS orbit | MMH : 918 MON3 : 1514 |
500N main engine x 4 120N x 28 |
| HTV-X（BPS） | - | ISS orbit | MMH : 981 MON3 : 1619 |
120N x 24 |
| MMX（outbound)（BPS） | - | Martian moon | N2H4: 916 MON3 : 858 |
450N x 4 |
| MMX（inbound)（BPS） | - | Martian moon | N2H4: 607 MON3 : 531 |
450N x 2 22N x 20 |
Monopropellant Propulsion Systems
IHI Aerospace have developed and manufactured hydrazine propulsion systems since 1980s. We have continued to deliver a number of monopropellant systems for over 40 years A wide range of propellant tanks and thrusters developed by IA IHI Aerospace have been used on monopropellant propulsion systems.
| Program | Launch Year |
Propellant Load [kg] |
Thruster |
|---|---|---|---|
| ETS-IV | 1981 | 64 | 18N x 2 |
| ETS-III | 1982 | 18 | 1N x 12 |
| MOS-1 | 1987 | 18 | 1N x 14 |
| ETS-V | 1987 | 113 | 20N x 2, 1N x 16 |
| CS-3 series | 1988 | 118 | 20N x 4 |
| MOS-1b | 1990 | 14 | 1N x 14 |
| JERS-1 | 1992 | 115 | 1N x 22 |
| ETS-VI | 1994 | 115 | 1N x 16 |
| ADEOS series | 1996~ | 170 | 20N x 4, 1N x 16 |
| ETS-VII | 1997 | 440 | 20N x 28, 1N x 12 |
| Program | Launch Year |
Propellant Load [kg] |
Thruster |
|---|---|---|---|
| MDS-1 | 2002 | 24 | 1N x 4 |
| OICETS | 2005 | 40 | 1N x 8 |
| ALOS | 2006 | 170 | 4N x 4, 1N x 16 |
| GOSAT | 2008 | 115 | 20N x 4, 1N x 8 |
| GCOM series | 2012~ | 260 | 4N x 12 |
| ASNARO series | 2014~ | 40 | 4N x 4 |
| Classified program | - | 283 | 4N x 8 |
Launch vehicle RCS
IHI Aerospace has developed reaction control systems (RCS) for launch vehicles for over 40 years. The RCS has been used on board H-I, H-II, H-II A and H-IIB rockets launch vehicles which were used as Japanese flagship launchers. IHI Aerospace has been developing low-pricing RCS for the H3 launch vehicle.
| Program | Launch Year |
Orbit |
|---|---|---|
| N-I | 1975~1982 | 18N x 12 |
| N-II | 1981~1987 | 18N x 12 |
| H-I | 1986~1992 | 18N x 12 |
| H-II | 1994~1999 | 50N x8, 18N x 2 |
| H-IIA | 2001~ | 50N x 8 |
| H-IIB | 2009~2020 | 50N x 8 |
| Epsilon (PBS) | 2013~ | 50N x 8 |
| H3 | - | 50N x 8 |
| Microlauncher | - | 20N x 8 |
Cold gas
We have developed and manufactured cold gas propulsion systems for small satellites with lower ΔV and sounding rockets. The simplified system reduces costs related to handling, propellant loading and transportation. We have also developed a cold gas system with liquefied gas as propellant that reduces tank volume.
| Program | Launch Year |
Propellant | Thruster |
|---|---|---|---|
| HYFLEX | 1996 | GN2 | 40N x 6 |
| ETS-Vll | 1997 | GN2 | 20N x 28, 1N x 12 |
| DASH | 2002 | GN2 | 1N x 1 |
| IKAROS | 2010 | HFC-134a | 1N x 8 |
| SS-520 series | 1998~ | GN2 | 23N x 1~4 |
Bipropellant Thrusters
IHI Aerospace has manufactured and delivered over 350 bipropellant thrusters for spacecraft since the start of development in the 1980s. We have developed 450N thrusters and 22N thrusters with hydrazine and MON3 for geostationary satellites in 2001. The high-performance 450N thruster has been widely used by US satellite manufactures. IHI Aerospace delivered its first bipropellant thruster ,for the 1700N N2H4/MON apogee engine, in the 1980s and remains at the forefront of apogee engine production. The 490N and 110N thrusters were developed with MMH and MON as fuel for the HTV. These bipropellant thrusters are stable over a wide operational range? and are less expensive than imported thrusters.
| Model | Thrust | Propellant | Isp | Inlet pressure | Demonstrated life | Throughput | Status |
|---|---|---|---|---|---|---|---|
| BT-4 | 450N | Hydrazine/ NTO | 326s | F : >1.69MPa,O : >1.62Mpa | 32850s | - | Flight proven |
| BT-6 | 21.5N | Hydrazine/ NTO | 295s | 1.69MPa | - | 583kg | Flight proven |
| HBT-5 | 478N | MMH/MON3 | 316s | 1.72MPa | 15000s | - | Flight proven |
| HBT-1 | 124.4N | MMH/MON3 | 274.9s | 2.05MPa | 40000s | 446kg | Flight proven |
Hydrazine Bipropellant Thrusters
450N Thruster (BT-4)
22N Thruster (BT-6)
MMH Bipropellant Thrusters
490N Thruster (HBT-5)
120N Thruster (HBT-1)
Monopropellant Thrusters
Over 1,100 hydrazine monopropellant thrusters manufactured by IHI Aerospace have been launched since the start of development in the 1964. Its thrust range from 1N from 50N. The advanced 1N and 4N thrusters have?recently been developed to enhance its competitiveness, reliability and lifetime.
| Model | Thrust | Isp | Number of pulses | Throughput | Status |
|---|---|---|---|---|---|
| MT-9 | 0.29-1.13N | 208-215s | >850,000 | >100kg | Flight proven |
| MT-8A | 1.80-5.01N | 212-225s | >850,000 | >190kg | Flight proven |
| MT-2 | 6.9-19.6N | 210-226s | >261,914 | >115kg | Flight proven |
| MT-2B | 8.5-30N | 212-223s | >150,000 | >140kg | Being developed |
| MT-6 | 23-50N | 215-225s | >14,800 | >120kg | Flight proven |
| MT-6A | 50N | 225s | >14,000 | >107kg | Qualified |
1N Thruster (MT-9)
4N Thruster (MT-8A)
20N Thruster (MT-2)
50N Thruster (MT-6)
Propellant Tanks
IHI Aerospace has developed a wide range of propellant tanks and pressurant tanks for launchers and satellites since the start of development in the 1964. Over 200 propellant tanks have been launched and successfully operated. IHI Aerospace’s product line covers a wide range of tanks from 3 to 1500 liters in volume and from diaphragms to surface tension channel mesh propellant management devices (PMDs).
| Volume [L] | Size [mm] | Internal device | Mount type | Status |
|---|---|---|---|---|
| 3 | 182 ID Sphere | DIAPHRAGM | Boss | Flight proven |
| 10 | 270 ID Sphere | NONE | Tab (Lug) | Fully developed |
| 14 | 300 ID Sphere | BLADDER | Flange | Flight proven |
| 14 | 300 ID Sphere | VANE | Flange | Flight proven |
| 18 | 278 ID Tear-drop | NONE | Tab (Lug) | Flight proven |
| 22 | 300 ID x 390? length | SPONGE METAL | Tab (Lug) | Flight proven |
| 37 | 420 ID Sphere | DIAPHRAGM | 3 Tab (Lug) | Flight proven |
| 37 | 420 ID Sphere | DIAPHRAGM | Pedestal | Flight proven |
| 48 | 449 ID Tear-drop | NONE | Tab (Lug) | Fully developed |
| 56 | 474 ID Sphere | NONE | Tab (Lug) | Flight proven |
| 67 | 420 ID x 750? length | DIAPHRAGM | Pedestal | Flight proven |
| 74 | 420 ID x 754? length | DIAPHRAGM | 4 Tab (Lug) | Fully developed |
| 74 | 570 ID x 500? length | DIAPHRAGM | 4 Tab (Lug) | Being developed |
| 86 | 550 ID Sphere | CHANNEL MESH | Tab (Lug) | Flight proven |
| 117 | 609 ID Sphere | START BASKET | Tab (Lug) | Flight proven |
| 141 | 650 ID Sphere | DIAPHRAGM | 3 Tab (Lug) | Flight proven |
| 169 | 650 ID x 750? length | DIAPHRAGM | 3 Tab (Lug) | Fully developed |
| 202 | 720 ID Sphere | CHANNEL MESH | Tab (Lug) | Being developed |
| 289 | 820 ID Sphere | START BASKET | Tab (Lug) | Flight proven |
| 300 | 820 ID x 845? length | START BASKET | Tab (Lug) | Flight proven |
| 389 | 820 ID x 1011? length | START BASKET | Tab (Lug) | Flight proven |
| 427 | 820 ID x 1087 length | CHANNEL MESH | Tab (Lug) | Flight proven |
| 430 | 820 ID x 994 length | VANE | Tab (Skirt) | EM developed |
| 430 | 820 ID x 1087 length | CHANNEL MESH | Tab (Lug) | Flight proven |
| 510 | 995 ID Sphere | START BASKET | Tab (Lug) | Flight proven |
| 552 | 1020 ID Sphere | CHANNEL MESH | Tab (Lug) | Flight proven |
| 672 | 1020 ID x 1260 length | CHANNEL MESH | 8 Tab (Lug) | Being developed |
| 726 | 1020 ID x 1316 length | CHANNEL MESH | 4 Tab (Lug) | Fully developed |
| 760 | 1136 ID Sphere | START BASKET | Tab (Lug) | Flight proven |
| 1018 | 1156 ID x 1361 length | CHANNEL MESH | Tab (Lug) | Flight proven |
| 1147 | 1300 ID Sphere | CHANNEL MESH | Tab (Lug) | Flight proven |
| 1494 | 1300 ID x 1565 length | CHANNEL MESH | Tab (Lug) | Flight proven |
HTV 552 [liters]
ASNARO 67 [liters]
Internal Devices
-Diaphragm (SiO2-free diaphragm is under development)
-Surface tension channel mesh
-Vane
-Others (Start basket and sponge metal)
Diaphragm
Channel Mesh
Vane
HTV 552 [liters]
ASNARO 67 [liters]
Electric Propulsion Thrusters
Electric Propulsion Thrusters
IHI Aerospace has designed, developed and manufactured several types of electric thrusters for spacecraft since 1983. We are currently developing high-power Hall Thrusters for all-electric satellites.
| Model | Propellant | Thrust Level | Electrical Power (nom.) |
Number of Units Delivered |
Status |
|---|---|---|---|---|---|
| Electro-thermal Hydrazine Thruster (EHT) | Hydrazine | 0.40-0.13N | 500W | 2 | Flight proven |
| MPD Thruster | Hydrazine | >20mN | 1kW | 4 | Flight proven |
| DC Arcjet Thruster | Hydrazine | 90-130mN | 1kW | - | EM completed |
| Low power Hall Thruster | Xe | 62mN | 1.0kW | - | Being developed |
| High power Hall Thruster | Xe | >230mN@BOL >219mN@MOL >212mN@EOL |
4kW | - | Being developed |
| >359mN@BOL >330mN@MOL |
6kW |
Low Power Hall Thruster
High Power Hall Thruster
Launch Site Support / Testing Capabilities
Launch Site Support
IHI Aerospace has a great deal of expertise and heritage in propellant loading and testing support after delivery .
Manufacturing and Testing Capabilities
Our manufacturing capabilities include the processes, testing and equipment required for fabrication of variety of propulsion components and propulsion systems for spacecraft.
- Firing test stand for apogee engines
- Firing test stand for small thrusters（3 Vacuum chambers）
- Stage firing test stand (sea level)
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