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Credits for providing information to Jim Glass
Boeing North American and Jane's Space
TRW SPACE & ELECTRONICS GROUP
One Space Park
Redondo Beach, California
90278-1001
Tel: (310) 535-4321
Fax: (310) 812-7111
| Dry Mass | unknown |
| Fuel | ammonia at 0.25mg/sec steady state |
| Isp | 800 sec |
| Design Life | 1500 hours and 400 on/off cycles |
| First Flight | April 1991 |
| Number Flown | 6 |
| Dry Mass | 4.8 kg |
| Length | 56.05 cm |
| Maximum Diameter | 30.15 cm |
| Mounting | fixed |
| Engine Cycle | pressure-fed at 15 atm |
| Oxidizer | MON 3-flow rate at 0.076 kg/sec |
| Fuel | high purity hydrazine-flow rate at 0.071 kg/sec |
| O/F Ratio | 1.070:1 |
| Thrust | 454N in vacuum |
| Isp | 314.5 sec in vacuum |
| Expansion Ratio | 204:1 |
| Cooling Method | radiation |
| Chamber Pressure | 7.0 atm |
| Ignition | hypergolic with initiation at 28 V electrical to an on/off bi-propellant torque motor valve |
| Burn Time | 24,000 sec total, with a 3600 sec maximum single burn |
| Dry Mass | 6.8 kg |
| Length | 70.05 cm |
| Maximum Diameter | 27.13 cm |
| Mounting | fixed |
| Engine Cycle | pressure fed |
| Oxidizer | di-nitrogen tetraoxide at 0.119 kg/sec during maximum thrust |
| Fuel | MMH at 0.0745 kg/sec during maximum thrust |
| O/F Ratio | 1.64 |
| Thrust | 57.8-578 N in vacuum, with a throttle range ratio of 10:1 |
| Isp | 280-308 sec in vacuum |
| Expansion Ratio | 125:1 |
| Cooling Method | radiative cooling |
| Chamber Pressure | 0.75-6.8 atm |
| Ignition | hypergolic |
| Burn Time | 28 hours total with a 2800 sec maximum sungle burn |
| Applications | missions requiring duty cycle flexibility |
| First Flight | 1991 |
| Number Produced | 22 |
| Mass | 1.13 kg |
| Length | 21 cm |
| Engine Cycle | decomposition of hydrazine over heated shell catalyst |
| Thrust | 12-24.5 N in vacuum |
| Isp | 232-240 sec in vacuum at steady state conditions |
| Inlet Pressure | 6.8-31.6 atm |
| Burn Time | 0.050 sec up to several hours |
| Minimum Firing Bit | 0.025 sec |
| Total Cycles | 50,000 |
| Random Vibration | 21 g rms |
| Mass | 1.13 kg |
| Length | 26.9 cm |
| Engine Cycle | decomposition of hydrazine over heated shell catalyst |
| Thrust | 44.5-89 N in vacuum |
| Isp | 225 sec in vacuum at steady state conditions |
| Inlet Pressure | 12-27 atm |
| Burn Time | 0.020 sec |
| Total Cycles | 100,000 |
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