Russian orbital launch vehicle. Version of the 17S40 with payload adapter for deployment of multiple LM 700 (Iridium) spacecraft into medium earth orbit.
LEO Payload: 5,000 kg (11,000 lb). Payload: 4,350 kg (9,590 lb) to a GTO.
Gross mass: 691,500 kg (1,524,400 lb).
More... - Chronology...
Payload: 5,000 kg (11,000 lb).
Height: 57.20 m (187.60 ft).
Diameter: 4.15 m (13.61 ft).
Span: 7.40 m (24.20 ft).
Thrust: 9,500.00 kN (2,135,600 lbf).
Apogee: 40,000 km (24,000 mi).
RD-0210 Kosberg N2O4/UDMH rocket engine. 582.1 kN. Isp=326s. Cluster of four similar engines used in second stage of Proton - one providing tank pressurization (8D412K/RD-0211) and three (8D411K/RD-0210). Staged combustion cycle. First flight 1965. More...
RD-0212 Kosberg N2O4/UDMH rocket engine. 613 kN. Proton stage 3. Engine unit consisting of 1 RD-0213 maine engine and 4 RD-0214 vernier/steering engines. 8D48 essentially similar to 8D411 and 8D412 and has the same combustion chamber. Isp=324s. First flight 1967. More...
RD-253-11D48 Glushko N2O4/UDMH rocket engine. 1635 kN. Isp=316s. Six gimballed single chamber RD-253s provide the first stage power for the UR-500 Proton launch vehicle. First flown in 1965. More...
RD-58M Korolev Lox/Kerosene rocket engine. 83.4 kN. Proton 8K824K / 11S824M; 11S824F; 11S86; 11S861; 17S40 stage 4 (block DM). In production. Isp=353s. First flight 1974. More...
Proton The Proton launch vehicle has been the medium-lift workhorse of the Soviet and Russian space programs for over forty years. Although constantly criticized within Russia for its use of toxic and ecologically-damaging storable liquid propellants, it has out-lasted all challengers, and no replacement is in sight. More...
Associated Manufacturers and Agencies
Chelomei Russian manufacturer of rockets, spacecraft, and rocket engines. Chelomei Design Bureau, Reutov, Russia. More...
Proton 17S40 Lox/Kerosene propellant rocket stage. Loaded/empty mass 14,600/3,300 kg. Thrust 85.02 kN. Vacuum specific impulse 352 seconds. Also known as Block DM-5. Commercial version is Block DM2, with Iridium dispenser, designed for insertion of multiple LM 700 (Iridium) spacecraft into medium earth orbit. With guidance unit, modification of 11S861 stage for heavier payloads and with different payload adapter. More...
Proton K-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 450,510/31,100 kg. Thrust 10,470.16 kN. Vacuum specific impulse 316 seconds. More...
Proton K-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 167,828/11,715 kg. Thrust 2,399.22 kN. Vacuum specific impulse 327 seconds. More...
Proton K-3 N2O4/UDMH propellant rocket stage. Loaded/empty mass 50,747/4,185 kg. Thrust 630.17 kN. Vacuum specific impulse 325 seconds. More...
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