Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
Monoblock UR-500
Part of Proton Family
UR-500 Monoblock
UR-500 Monoblock
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
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 oxidizer 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.

Status: Design 1962. Payload: 12,000 kg (26,000 lb). Thrust: 8,119.80 kN (1,825,404 lbf). Gross mass: 543,400 kg (1,197,900 lb). Height: 54.00 m (177.00 ft). Diameter: 6.20 m (20.30 ft). Apogee: 200 km (120 mi).

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.



Family: orbital launch vehicle. Country: Russia. Engines: 8D43 + 11D43, RD-0212, RD-0213, 11D43, 8D43. Stages: Monoblock UR-500-1M, Monoblock UR-500-2, Monoblock UR-500-3. Agency: Chelomei bureau.
Photo Gallery

Universal RocketsUniversal Rockets
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



Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2017 Mark Wade - Contact
© / Conditions for Use