MONARC Monopropellant Thrusters
Moog's MONARC hydrazine monopropellant thruster family covering 1 N to 445 N thrust across six model series, with over 3,000 units delivered to commercial and government satellite programs.
Typed specifications56 values
Discloses 6 of 10 fields engineers filter by in this category (category median 3).
- Propulsion family
- chemical Nominal Specific Impulse · datasheet p.2 chemical | chemical Engine Length/Exit Diam | chemical Steady State Thrust @ 260 psia | chemical Valve Power +3
- Mass
- 1.6 g datasheet p.2 380 g MONARC-1 | 690 g MONARC-22-12 | 720 g MONARC-22-6 | 1.6 kg MONARC-445 +3
- Thrust
- 100 mN Steady State Thrust @ 260 psia · datasheet p.2 1 000 mN nom. · MONARC-1, steady state @280 psia | 22 000 mN nom. · MONARC-22-12, 5 lbf (22N) @242 psia | 22 000 mN nom. · MONARC-22-12, printed 6.2 lbf (22N) @250 psia | 22 000 mN nom. · MONARC-22-6, steady state @250 psia +4
- Envelope (L×W×H)
- 16 in (41 cm) / 5.8 in (14.8 cm) Engine Length/Exit Diam · datasheet p.2
- Specific impulse
- 235 s Nominal Specific Impulse · datasheet p.2 235 s nom. · MONARC-1 | 232 s nom. · MONARC-22-12 (HT) | 227 s nom. · MONARC-22-12 (LT) | 228 s nom. · MONARC-22-6 +4
- Propellant
- hydrazine datasheet p.0
- Power consumption
- 18 W MONARC-1, valve power · datasheet p.2 30 W MONARC-22-12, valve power | 30 W MONARC-22-6, valve power | 58 W MONARC-445, valve power | 18 W MONARC-5, valve power +3
- Export status
- EAR datasheet p.2
- Thruster technology
- monopropellant hydrazine datasheet p.1
- Feed / tank pressure
- 4.8 bar datasheet p.2 4.8–27.6 bar MONARC-1 | 4.8–27.6 bar MONARC-22-12 | 4.8–27.6 bar MONARC-22-6 | 4.8–27.6 bar MONARC-445 +4
- Flight heritage
- Galileo, Sentinel, SMAP, Mars 2020, Jason-CS, MMS, EarthCare, LCROSS, Worldview, Skynet, ExoMars, SWOT, GOES, Landsat-8, Chandra product page
Each value is typed with its unit and measurement condition and cites the datasheet page it was taken from. Nothing is guessed: a field that is absent here has not been published by the manufacturer. machine-extracted ✓ checked by NewSpace Market ✓ manufacturer confirmed by the manufacturer.
As published by the supplier11 lines, in the manufacturer's own wording
- Monarc-1
- Thrust 0.9–1 N; Isp 227–235 s; Mass 0.38 kg
- Monarc-5
- Thrust 4.5–5 N; Isp 226–230 s; Mass 0.49 kg
- Monarc-22-6
- Thrust 22 N; Isp 228–229.5 s; Mass 0.72 kg; 6-in nozzle
- Monarc-22-12 lt/ht
- Thrust 22 N; Isp 227–232 s; Mass 0.69 kg; 12-in nozzle
- Monarc-90 lt
- Thrust 22–90 N; Isp 232 s; Mass 1.12 kg; low-temperature catalyst
- Monarc-90 ht
- Thrust 93–116 N; Isp 232–234 s; Mass 1.12 kg; high-temperature catalyst
- Monarc-445
- Thrust 111–445 N; Isp 234–235 s; Mass 1.6 kg
- Propellant
- Hydrazine (N2H4)
- Feed pressure
- 70–420 psia (model-dependent)
- Units delivered
- 3,000+
- Flight heritage
- Galileo, Sentinel, SMAP, Mars 2020, Jason-CS, MMS, EarthCare, LCROSS, Worldview, Skynet, ExoMars, SWOT, GOES, Landsat-8, Chandra
About
The MONARC (MONopropellant ARCjet-compatible) thruster family is Moog’s flagship monopropellant product line, using hydrazine as propellant with Shell 405/S-405 catalyst beds. The family spans six model groups covering Attitude Control System and main propulsion duties across all satellite sizes. MONARC-1 (1 N) and MONARC-5 (5 N) serve precision ACS applications on small- and medium-class satellites. MONARC-22 (22 N) in 6-in and 12-in nozzle variants covers mid-class ACS and orbit adjust. MONARC-90 in Low Temperature (LT, 22–90 N) and High Temperature (HT, 93–116 N) variants provides orbit raising and station-keeping for LEO constellations and GEO spacecraft. MONARC-445 (111–445 N) is the largest Moog monopropellant thruster, used for main propulsion and orbit maneuvers. All models operate across a feed pressure range of 70–420 psia and are qualified for long mission lives. Specific impulse ranges from 227 to 235 seconds. Over 3,000 MONARC thrusters have been delivered with heritage on Galileo navigation satellites, Sentinel Earth observation, SMAP, Mars 2020 (Perseverance), Jason-CS, MMS, EarthCare, Worldview, and ExoMars.
Documentation
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