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|Proton 8K82K / 11S86 - Proton 8K82K / 11S86 Block DM launch vehicle - cutaway drawing showing arrangement of N2O4 oxidiser tanks (green) and UDMH fuel tanks (orange) in Proton, and Liquid oxygen (blue) and kerosene (pink) tanks in the Block DM stage. Block DM guidance package is housed in the light brown compartment above the LOX tank.|
Credit: © Mark Wade. 6,988 bytes. 60 x 430 pixels.
Family: UR. Country: Russia. Status: Hardware. Other Designations: Proton / Block DM4. Library of Congress Designation: D-1e. Department of Defence Designation: SL-12. Article Number: 8K82K. Manufacturer's Designation: UR-500K.
This four stage version has a guidance unit in the fourth stage, which reduces payload but does not require the spacecraft's guidance system to provide steering commands to booster. Fourth stage is a 'Block DM-2M' / 11S861-01 modified for insertion of FS-1300 bus spacecraft into geosynchronous orbit.
Launches: 1. Failures: 0. Success Rate: 100.00% pct. First Launch Date: 24 May 1997. Last Launch Date: 24 May 1997. Payload: 1,880 kg. to a: geosynchronous orbital trajectory. Liftoff Thrust: 902,100 kgf. Total Mass: 712,460 kg. Core Diameter: 4.2 m. Total Length: 59.0 m. Launch Price $: 70.00 million. in 1994 price dollars.
- Stage Number: 1. 1 x Proton K-1 Gross Mass: 450,510 kg. Empty Mass: 31,100 kg. Thrust (vac): 1,067,659 kgf. Isp: 316 sec. Burn time: 124 sec. Isp(sl): 267 sec. Diameter: 4.2 m. Span: 7.4 m. Length: 21.2 m. Propellants: N2O4/UDMH No Engines: 6. RD-253-11D48
- Stage Number: 2. 1 x Proton K-2 Gross Mass: 167,828 kg. Empty Mass: 11,715 kg. Thrust (vac): 244,652 kgf. Isp: 327 sec. Burn time: 206 sec. Isp(sl): 230 sec. Diameter: 4.2 m. Span: 4.2 m. Length: 14.0 m. Propellants: N2O4/UDMH No Engines: 4. RD-0210
- Stage Number: 3. 1 x Proton K-3 Gross Mass: 50,747 kg. Empty Mass: 4,185 kg. Thrust (vac): 64,260 kgf. Isp: 325 sec. Burn time: 238 sec. Isp(sl): 230 sec. Diameter: 4.2 m. Span: 4.2 m. Length: 6.5 m. Propellants: N2O4/UDMH No Engines: 1. RD-0212
- Stage Number: 4. 1 x Proton 11S861-01 Gross Mass: 18,650 kg. Empty Mass: 2,650 kg. Thrust (vac): 8,510 kgf. Isp: 361 sec. Burn time: 680 sec. Diameter: 3.7 m. Span: 3.7 m. Length: 7.1 m. Propellants: Lox/Kerosene No Engines: 1. RD-58S
Proton 8K82K / DM4 Chronology
1997 May 24 - - 17:00 GMT. LV Configuration: Proton 8K82K s/n 380-02 / DM4 s/n 1L. Launch Site: Baikonur . Launch Complex: LC81L.
- 67 - Kaesmann, Ferdinand, et. al., Journal of the British Interplanetary Society, "Proton - Development of A Russian Launch Vehicle", 1998, Volume 51, page 3.
- 42 - Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991.
- 151 - Clark, P S, Journal of the British Interplanetary Society, "Soviet Spacecraft Masses for Deep Space Missions", 1985, Volume 38, page 25.
- 219 - Mission Planner's Manual - Proton Commercial Launch Vehicle, Space Commerce Corporation, Houston, TX 1989.
- 274 - Vladimirov, A, Novosti kosmonavtiki, "Tablitsa zapuskov RN 'Proton' i 'Proton K'", 1998, Issue 10, page 25.
|Proton with Granat - Proton with Granat payload|
Credit: Lockheed Martin. 18,616 bytes. 356 x 446 pixels.
|R-7 vs Proton - R-7 / Proton LVs Cutaway|
Credit: © Mark Wade. 10,191 bytes. 287 x 720 pixels.
|Universal Rockets - Chelomei's Universal Rocket Family. From left to right: 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 as flown. UR-500K configuration with Block D upper stage.|
Credit: © Mark Wade. 36,031 bytes. 630 x 351 pixels.
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Last update 12 March 2001.
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