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Credits for providing information to Jim Glass
Boeing North American, and Jane's Space
Three versions of this hypergolic engine are used on Proton.
| Applications | SL-12/13 Proton stage 2 and 3 |
| First Flown | July 1965 (stage 2), 1967 (stage 3) |
| Engine Cycle | closed (Oxidizer pre-burner gas routed to main chamber after driving turbine) |
| Oxidizer | N2O4 |
| Fuel | UDMH |
| Thrust | 594 kN vacuum (stage 2 version), 593.6 kN vacuum (stage 3, plus 31.5 kN added by four verniers) |
| Isp | 327.4 (stage 2) and 325.3 (stage 3) sec vacuum |
| Chamber Pressure | 148 atm |
| Burn Time | 210 sec |
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