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KDU-426
Isayev N2O4/UDMH rocket engine. Soyuz-T orbital correction engine. In Production. Pressure-fed engine. Used as long duration engine for correction orbits of satellites.

AKA: 11D426;KTDU-426. Status: In Production. Date: 1968-74. Thrust: 3.09 kN (694 lbf). Unfuelled mass: 270 kg (590 lb). Specific impulse: 292 s. Burn time: 570 s. Height: 1.24 m (4.05 ft). Diameter: 2.10 m (6.80 ft).

Engine: 270 kg (590 lb). Chamber Pressure: 8.80 bar. Thrust to Weight Ratio: 1.16. Oxidizer to Fuel Ratio: 1.85.

Subtopics
KRD-79 Isayev N2O4/UDMH rocket engine. Salyut 6, 7and Mir orbital propulsion maneuvering engine. In Production. Probably derived from engine of propulsion system KDU-426. Pressure fed engine.
Family: Storable liquid. Country: Russia. Spacecraft: Soyuz T. Propellants: N2O4/UDMH. Agency: Isayev bureau. Bibliography: 314, 329, 344.
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