BIPROPELLANT ATTITUDE CONTROL SYSTEM THRUSTERS
Overview
Our 5 lbf thrusters are designed with a high temperature Platinum/Rhodium chamber. Moog also offers a new 25 lbf thrust class, which leverages Moog’s experience designing high performance bipropellant engines. Moog attitude control system (ACS) engines have been the industry standard with more than 2,000 delivered.
5 lbf ACS Engines
| Model Family | DST-11H | DST-12 | DST-13/E | 5 lbf Columbium |
| Propellant | Hydrazine/MON | MMH/MON | MMH/MON | MMH/MON |
| Nominal Steady State Thrust | 5 lbf (22N) | 5 lbf (22N) | 5 lbf (22N) / 6.2 lbf (27.5) | 5 lbf (22N) |
| Feed Pressure Range | 80 – 400 psia (5.5 – 27.6 bar) | 60 – 400 psia (4.1 - 27.6 bar) | 80 – 400 psia (5.5 - 27.6 bar) | 39 - 320 psia (2.8 - 22.1 bar) |
| Nozzle Expansion | 300:1 | 300:1 | 300:1 | 150:1/300:1 |
| Nominal Mixture Ratio | 0.85 | 1.61 | 1.65 / 1.62 | 1.61/1.65 |
| Valve | Solenoid | Latching Torque Motor | Solenoid | Latching Torque Motor or Solenoid |
| Valve Power | 41 watts max (2 coils wired in series) | 6 watts max (Latch) 7 watts max (primary) 9 watts max (secondary) | 41 watts max (2 coils wired in series) | 6 watts max (Latch) 7 watts max (primary) 9 watts max (secondary) (Torque Motor) 15.6 watts max (solenoid) |
| Mass | 1.7 lbm (0.77 kg) | 1.4 lbm (0.64 kg) | 1.5 lbm (0.68 kg) | 1.4 – 2.0 lbm (0.64 – 0.91 kg) |
| Length | 10.3 in (262 mm) | 9.6 in (244 mm) | 10.4 in (264 mm) | 9.7-13.5 in (248 - 343 mm) |
| Chamber Material | Platinum/Rhodium Alloy | Platinum/Rhodium Alloy | Platinum/Rhodium Alloy | C-103 |
| Minimum Specific Impulse | 307 sec | 297 sec | 297 sec | 284 sec/288 sec |
| Throughput | 2019 lbm | 1402 lbm (uncoated) 2342 lbm (coated) | 1404 lbm/2169 lbm | 1600 lbm |
| Highlights | DST-11H provides highest performance available in a hydrazine/ MON ACS Thruster | DST-12/13 Provides highest performance available in MMH/MON ACS Thruster | Engine has been in production for more than 30 years, with > 2000 delivered and flown | |
25 lbf Engines
| Product Line | 25 lbf MMH (Monomethylhydrazine) | 25 lbf Hydrazine (N2H4) |
| Propellants (Ox / Fuel) | NTO / MMH | NTO / N2H4 |
| Thrust @ Feed Pressure | 25 lbf @ 230 psia | 25 lbf @ 250 psia |
| Specific Impulse | ~ 306 sec (Nominal) | ~ 311 sec (Nominal) |
| Nozzle Area Ratio | 300:1 | 300:1 |
| Mixture Ratio | 1.62 | 0.85 |
| Valve Type | Latch/Thruster Redundant Torque Motor | Latch/Thruster Redundant Torque Motor |
| Nozzle Material | Pt / Rh (Chamber) Inconel 625 Nozzle | Pt / Rh (Chamber) Inconel 625 Nozzle |
| Qualification Status | Qualification | Development |
