RD-253 (original) (raw)

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RD-253

RD-253 engine
Credit: Khrunichev

Glushko N2O4/UDMH rocket engine. In Production. Version of RD-253 with thrust increased by 7%. Included an additional gas generator for tank pressurization. First flight 1986.

AKA: RD-275. Status: In Production. Date: -1986. Thrust: 1,745.00 kN (392,291 lbf).

This enhancement is accomplished with only a minor modification to the propellant flow control valves. This modification first flew as a mission-unique enhancement on the Proton K that delivered the MIR space station core module in 1986. Engines incorporating this change have undergone extensive additional qualification firings since then, in order to approve them for use in standard production vehicles. Shipsets have already been produced and incorporated onto production Proton K vehicles. To 1999, 65 Proton K's had been launched with the modified engines operating at 102% of rated thrust. Eight Proton K vehicles had flown with the 107% engines. There had been no flight anomalies attributed to the increased thrust engines.

Subtopics

RD-222 Glushko Nitric acid/UDMH rocket engine. missile stage 1 (stage 2 used RD-223). Developed 1960-61. Precursor to RD-253.

RD-223 Glushko Nitric acid/UDMH rocket engine. missile stage 2 (stage 1 used RD-222). Developed 1960-61. Precursor to RD-253.

RD-254 Glushko N2O4/UDMH rocket engine. N-1 upper stage, UR-700 stage 3. Proposed for use in N-1. High altitude version of RD-253 for 2nd stages. Later proposed for R-56 and UR-700 upper stages.

RD-253-UR-700 Glushko N2O4/UDMH rocket engine. Designed 1964-1968. UR-700 Stage 3. Development of RD-253 with increased expansion ratio for upper stage use.

RD-275 Glushko N2O4/UDMH rocket engine. Proton stage 1. In Production. Uprated version of RD-253, developed in the 1980's. First flight 1986.

	RD-253-14D14 Glushko N2O4/UDMH rocket engine. Proton KM-1. In production. Developed in 1990s. First flight 1999.

	RD-253-11D48 Glushko N2O4/UDMH rocket engine. Six gimbaled single chamber RD-253s provide the first stage power for the UR-500 Proton launch vehicle and the third stage of the planned UR-700 moon launcher. First flown in 1965.

Family: Storable liquid. Country: Russia. Propellants: N2O4/UDMH. Agency: Glushko bureau. Bibliography: 219, 225, 273, 287, 335, 7511.

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