UR-500 conventional 'monoblock' configuration studied at the beginning of the program. This design was slightly lighter than the selected 'polyblock' configuration but had disadvantages in the missile role: difficult ground handling and payload access.
Credit: © Mark Wade
Chelomei's Universal Rocket Family. From left to right: UR-100 (three variants) and UR-100N (three variants). UR-200. Original UR-500 configuration, composed of clustered UR-200's. Conventional UR-500 monoblock configuration. Selected UR-500 polyblock configuration. UR-500 two-stage configuration - ICBM version and as flown. UR-500K configuration with LK-1; with Block D upper stage and L1; with Block D upper stage for satellite launch. UR-700.
Credit: © Mark Wade
Russian orbital launch vehicle. During UR-500 design studies, two variants of the first stage were considered: polyblock and monoblock. The monoblock approach was that the first stage be assembled from two separate modules with the same diameter: an upper oxidiser module and a lower fuel and engine block. In assembly trials of this design it proved difficult, because of the height of the first stage, to obtain access to the upper stages and payload atop the rocket. Although there was a payload advantage compared to the more compact polyblock design, this was relatively small and outweighed by the operational difficulties.
This variant was studied by Chelomei's Filial Number 1, Chief Designer V N Bugayskiy, under the lead engineer M S Mishetyan.
The design mass and engine performance figures for this version have been given. The calculated payload is 12,000 kg (26,000 lb) to a 200 km orbit.
Stage Data - Monoblock UR-500
- Stage 1. 1 x UR-500 Monoblok Stage 1M. Gross Mass: 367,360 kg (809,890 lb). Empty Mass: 25,560 kg (56,350 lb). Thrust (vac): 8,989.700 kN (2,020,965 lbf). Isp: 310 sec. Burn time: 115 sec. Isp(sl): 280 sec. Diameter: 6.20 m (20.30 ft). Span: 6.20 m (20.30 ft). Length: 30.00 m (98.00 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: 8D43 + 11D43. Status: Study 1962. Comments: Original conventional 'Monoblock' design for Proton first stage.
- Stage 2. 1 x UR-500 Stage 2. Gross Mass: 137,700 kg (303,500 lb). Empty Mass: 16,000 kg (35,000 lb). Thrust (vac): 3,183.200 kN (715,612 lbf). Isp: 320 sec. Burn time: 119 sec. Diameter: 4.10 m (13.40 ft). Span: 4.10 m (13.40 ft). Length: 10.90 m (35.70 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: RD-0213. Status: Study 1962. Comments: Original Proton second stage design.
- Stage 3. 1 x UR-500 Stage 3. Gross Mass: 23,940 kg (52,770 lb). Empty Mass: 2,180 kg (4,800 lb). Thrust (vac): 613.110 kN (137,833 lbf). Isp: 320 sec. Burn time: 110 sec. Diameter: 4.10 m (13.40 ft). Span: 4.10 m (13.40 ft). Length: 3.70 m (12.10 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: RD-0212. Status: Study 1962. Comments: Original Proton third stage design.
Status: Design 1962.
More... - Chronology...
Gross mass: 543,400 kg (1,197,900 lb).
Payload: 12,000 kg (26,000 lb).
Height: 54.00 m (177.00 ft).
Diameter: 6.20 m (20.30 ft).
Thrust: 8,119.80 kN (1,825,404 lbf).
Apogee: 200 km (120 mi).
11D43 Glushko N2O4/UDMH rocket engine. 1642 kN. Developed 1960-64. Isp=316s. Low-expansion ratio gimbaled variant for Proton stage 1 concept. Configuration 4 x 8D43 clustered with 4 x 11D43 abandoned in favor of 6 x Glushko 11D48 in final Proton design. More...
8D43 Kosberg N2O4/UDMH rocket engine. 559 kN. UR-500 stage 1 original concept. Hardware. Isp=316s. In early Proton design would be clustered with 4 x Glushko 11D43. Abandoned in favor of 6 x Glushko 11D48, but later developed into the RD-0208 and RD-0210. More...
8D43 + 11D43 Kosberg N2O4/UDMH rocket engine. 2247.450 kN. Design 1962. Isp=310s. Originally the first stage of the Proton was designed for 4 x fixed 11D43 and 4 x gimballed Kosberg 8D43; replaced by 6 x 11D48 from Glushko in final Proton design. 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-0213 Kosberg N2O4/UDMH rocket engine. 582.1 kN. Proton stage 3. Design 1962. Version of RD-0210. Staged combustion cycle (Oxidizer pre-burner gas routed to main chamber after driving turbine). Main engine for Proton Stage 3 in system RD-0212. Isp=326s. 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...
UR-500 Monoblok Stage 1M N2O4/UDMH propellant rocket stage. Loaded/empty mass 367,360/25,560 kg. Thrust 8,989.70 kN. Vacuum specific impulse 310 seconds. Original conventional 'Monoblock' design for Proton first stage. More...
UR-500 Stage 2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 137,700/16,000 kg. Thrust 3,183.20 kN. Vacuum specific impulse 320 seconds. Original Proton second stage design. More...
UR-500 Stage 3 N2O4/UDMH propellant rocket stage. Loaded/empty mass 23,940/2,180 kg. Thrust 613.11 kN. Vacuum specific impulse 320 seconds. Original Proton third stage design. More...
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