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RD-0243
RD-0243
RD-0243
Credit: KBKhA
Kosberg N2O4/UDMH rocket engine. R-29RM stage 1. Out of Production. Consisted of single-chamber main engine RD-0244 plus four-chamber steering engines RD-0245 driven by turbine exhaust gas. Engine submerged in propellant tank.

Status: Out of Production. Date: 1977-85. Thrust: 825.80 kN (185,647 lbf). Unfuelled mass: 853 kg (1,880 lb). Specific impulse: 300 s. Burn time: 79 s. Height: 1.90 m (6.20 ft). Diameter: 2.27 m (7.44 ft).

Chambers: 1 + 4. Engine: 853 kg (1,880 lb). Thrust to Weight Ratio: 98.73.



Subtopics

RD-0244 Kosberg N2O4/UDMH rocket engine. R-29RM / RSM-54 (SS-N-23) stage 1. Out of Production. Main engine in system RD-0243. Staged combustion cycle. Submerged in propellant tank. First flight 1985.

RD-0244-HC Kosberg LOx/Kerosene rocket engine. Design concept 1990's. Proposed variant of RD-0244 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

RD R-29 (1) Makeyev N2O4/UDMH rocket engine.

RD R-29R (1) Makeyev N2O4/UDMH rocket engine.

Family: Storable liquid. Country: Russia. Launch Vehicles: R-29RM. Propellants: N2O4/UDMH. Agency: Kosberg bureau. Bibliography: 309, 312, 96, 7491.

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