| Country of origin | USSR |
|---|---|
| Date | 1977-1986 |
| First flight | 1986-05-21 (Soyuz TM-1) |
| Designer | OKB-2, Anton Tavzarachvili |
| Application | Spacecraft main propulsion |
| Predecessor | 11D426 |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | N2O4 / UDMH |
| Mixture ratio | 1.85 |
| Cycle | pressure fed |
| Configuration | |
| Chamber | 1 |
| Nozzle ratio | 153.8 |
| Performance | |
| Thrust, vacuum | 2.95 kN (660 lbf) |
| Chamber pressure | 0.88 MPa (128 psi) |
| Specific impulse, vacuum | 302 s (2.96 km/s) |
| Burn time | 890 seconds |
| Restarts | 30 |
| Gimbal range | ±5° |
| Dimensions | |
| Length | 1.2 m (47 in) |
| Diameter | 2.1 m (83 in) |
| Dry weight | 310 kg (680 lb) |
| Used in | |
| Soyuz since Soyuz-TM and Progress since Progress-M | |
| References | |
| References | [1][2][3][4] |
The S5.80 is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It is currently used in the Soyuz-TMA-M spacecraft propulsion module KTDU-80, and its sibling, the S5.79 rocket engine, is still used as the main propulsion of the Zvezda ISS module. The S5.80 generates 2.95 kN (660 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 153.8 that enables it to achieve a specific impulse of 302 s (2.96 km/s). It is rated for 30 starts with a total firing time of 890 seconds. The engine, without the pressurization system or propellant tanks, weighs 310 kg (680 lb) and is an integrated unit that is 1.2 m (47 in) long with a diameter of 2.1 m (83 in).[4]
This engine has been used with certain variations in the crewed Russian space program since the Salyut 6inSoviet times. The three main versions are:
| Engine (SKD) | 11D426 | S5.79 | S5.80 |
|---|---|---|---|
| Propulsion module | KTDU-426 | KRD-79 | KTDU-80 |
| Development | 1968–1974 | 1968-1977 | 1977–1986 |
| Engine Type | Liquid pressure-fed rocket engine | ||
| Module | integrated spacecraft propulsion, pressurization and attitude control system | main propulsion engine | integrated spacecraft propulsion, pressurization and attitude control system |
| Propellant | N2O4/UDMH with 1.85 O/F ratio | ||
| Thrust (SKD) | 3.09 kN (690 lbf) | 3.09 kN (690 lbf) | 2.95 kN (660 lbf) |
| isp | 292 s (2.86 km/s) | 293.7 s (2.880 km/s) | 302 s (2.96 km/s) |
| Chamber Pressure | 0.88 MPa (128 psi) | 1.75 MPa (254 psi) | 0.88 MPa (128 psi) |
| Nozzle | 1 | 1 | 1 |
| Expansion Ratio | 153.8 | ||
| Burn time | 570s | 2700s | 890s |
| Ignitions | 40 | 70 | 30 |
| Mass | 270 kg (600 lb) | 38.5 kg (85 lb) | 310 kg (680 lb) |
| Length | 1,200 mm (47 in) | 840 mm (33 in) | 1,204 mm (47.4 in) |
| Diameter | 2,100 mm (83 in) | 550 mm (22 in) | 2,100 mm (83 in) |
| Uses | Soyuz-T | Salyut-6, Salyut-7, Mir Core Module, Zvezda | Soyuz-TM Soyuz-TM Soyuz-TMA Soyuz-TMA-M Progress-M Pirs Poisk |
| References | [1][2][6][7][8][9][10] | ||
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Spacecraft engines and motors
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|---|---|---|
| Liquid fuel engines |
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| Solid propellant motors |
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| Related articles |
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