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11d68.jpg+Block D / 11D68
Aft view of the Block D lunar crasher stage and its 11D68 engine. The Block D would have taken the LK lunar lander to near the surface of the moon. This stage remains in use today atop the Proton rocket.
Credit - © Mark Wade
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+398 Model: Proton 11S824. Gross Mass: 13,360 kg (29,450 lb). Empty Mass: 1,800 kg (3,900 lb). Thrust (vac): 83.300 kN (18,727 lbf). Isp: 346 sec. Burn time: 470 sec. Propellants: Lox/Kerosene. Diameter: 3.70 m (12.10 ft). Span: 3.70 m (12.10 ft). Length: 5.50 m (18.00 ft). Country: Russia. No Engines: 1. Motor: RD-58. Status: Retired 1975. Cost $ : 4.000 million. First Flight: 1967. Last Flight: 1975. No Launched: 40. No Failed: 6. Other designations: 11S824; Block D; D-1-e.

Originally designed as N1-L3 lunar expedition launch vehicle lunar orbit insertion/lunar crasher stage. Before it could fly on the N1, it was adapted for use with Proton UR-500K as a fourth stage for manned circumlunar flight. It was then further used to launch large Lavochkin bureau unmanned lunar/planetary spacecraft. In the 1970's it was adopted by the Soviet military and standardized for launch of geostationary satellites. Block D, article number 11S824. Without guidance unit (navigation commands come from payload). Adapted for use with Proton UR-500K as a fourth stage for manned circumlunar flight. Further used to launch large Lavochkin bureau unmanned lunar/planetary spacecraft. Flown from 1967 to 1975.

Model: N1 Block D. Gross Mass: 18,200 kg (40,100 lb). Empty Mass: 3,500 kg (7,700 lb). Thrust (vac): 83.300 kN (18,727 lbf). Isp: 349 sec. Burn time: 600 sec. Propellants: Lox/Kerosene. Isp(sl): 0 sec. Diameter: 2.90 m (9.50 ft). Span: 2.90 m (9.50 ft). Length: 5.70 m (18.70 ft). Country: Russia. No Engines: 1. Motor: RD-58. Status: Retired 1972. First Flight: 1969. Last Flight: 1972. No Launched: 8.

Block D as originally designed as a lunar crasher stage

Model: Proton 11S86. Gross Mass: 17,550 kg (38,690 lb). Empty Mass: 2,300 kg (5,000 lb). Thrust (vac): 85.020 kN (19,113 lbf). Isp: 352 sec. Burn time: 610 sec. Propellants: Lox/Kerosene. Diameter: 3.70 m (12.10 ft). Span: 3.70 m (12.10 ft). Length: 7.10 m (23.20 ft). Country: Russia. No Engines: 1. Motor: RD-58M. Status: Retired 1990. Cost $ : 4.000 million. First Flight: 1974. Last Flight: 1990. No Launched: 66. No Failed: 1. Other designations: Block DM; D-1-e.

Also known as Block DM; article number 11S86. With guidance unit, designed for insertion of military spacecraft into geosynchonous/ medium earth orbit. Used from 1974 to 1990. Succeeded by 11S861.

Model: Proton 11S824M. Gross Mass: 14,000 kg (30,000 lb). Empty Mass: 1,830 kg (4,030 lb). Thrust (vac): 85.020 kN (19,113 lbf). Isp: 352 sec. Burn time: 570 sec. Propellants: Lox/Kerosene. Diameter: 3.70 m (12.10 ft). Span: 3.70 m (12.10 ft). Length: 5.50 m (18.00 ft). Country: Russia. No Engines: 1. Motor: RD-58M. Status: Retired 1989. Cost $ : 4.000 million. First Flight: 1976. Last Flight: 1989. No Launched: 11. Other designations: 11S824; Block D; D-1-e.

Also known as Block D-1; article number 11S824M. Without guidance unit (navigation commands come from payload). Successor to 11S824. Used to launch large Lavochkin bureau unmanned lunar/planetary/high earth orbit spacecraft from 1976 to 1989.

Model: Proton 11S861. Gross Mass: 17,300 kg (38,100 lb). Empty Mass: 2,300 kg (5,000 lb). Thrust (vac): 85.020 kN (19,113 lbf). Isp: 352 sec. Burn time: 600 sec. Propellants: Lox/Kerosene. Diameter: 3.70 m (12.10 ft). Span: 3.70 m (12.10 ft). Length: 7.10 m (23.20 ft). Country: Russia. No Engines: 1. Motor: RD-58M. Status: Active. Cost $ : 4.000 million. First Flight: 1982. Last Flight: 2007. No Launched: 176. Other designations: Block DM; D-1-e.

Also known as Block DM-2 (different from commercial Block DM2 (no hyphen!)), article number 11S861. Commercial version designated Block DM1 and is equipped with Saab payload adapter for insertion of AS 4000 bus spacecraft into geosynchronous orbit. With improved guidance system as compared to 11S86, originally designed for insertion of military spacecraft into geosynchonous orbit. Used from 1982 to present.

Model: Energia RCS. Gross Mass: 17,000 kg (37,000 lb). Empty Mass: 2,000 kg (4,400 lb). Thrust (vac): 84.935 kN (19,094 lbf). Isp: 352 sec. Burn time: 680 sec. Propellants: Lox/Kerosene. Diameter: 3.70 m (12.10 ft). Span: 3.70 m (12.10 ft). Length: 5.70 m (18.70 ft). Country: Russia. No Engines: 1. Motor: RD-58. Status: Design 1987. Cost $ : 4.000 million. First Flight: 1987. Last Flight: 1988. No Launched: 2. Other designations: Retro and Correction Stage.

Adaptation of Block D for Energia payload orbital insertion.

Model: Proton 11S824F. Gross Mass: 16,900 kg (37,200 lb). Empty Mass: 1,800 kg (3,900 lb). Thrust (vac): 85.020 kN (19,113 lbf). Isp: 352 sec. Burn time: 610 sec. Propellants: Lox/Kerosene. Diameter: 3.70 m (12.10 ft). Span: 3.70 m (12.10 ft). Length: 5.50 m (18.00 ft). Country: Russia. No Engines: 1. Motor: RD-58M. Status: Retired 1996. Cost $ : 4.000 million. First Flight: 1988. Last Flight: 1996. No Launched: 10. Other designations: 11S824; Block D; D-1-e.

Also known as Block D-2; article number 11S824F. Without guidance unit (navigation commands come from payload). Successor to 11S824M. Used for launch of Lavochkin Mars-bound spacecraft in 1988 and 1996.

Model: Proton 11S861-01. Gross Mass: 18,650 kg (41,110 lb). Empty Mass: 2,650 kg (5,840 lb). Thrust (vac): 83.450 kN (18,760 lbf). Isp: 361 sec. Burn time: 680 sec. Propellants: Lox/Kerosene. Diameter: 3.70 m (12.10 ft). Span: 3.70 m (12.10 ft). Length: 7.10 m (23.20 ft). Country: Russia. No Engines: 1. Motor: RD-58S. Status: Active. Cost $ : 4.000 million. First Flight: 1994. Last Flight: 2006. No Launched: 46. No Failed: 1. Other designations: Block DM; D-1-e.

Also known as Block DM-2M, article number 11S861-01. Commercial versions are Block DM3, with Saab payload dispenser, for insertion of Hughes HS 601 bus spacecraft into geosynchronous orbit; and Block DM4, for insertion of FS-1300 bus spacecraft into geosynchronous orbit.. With guidance unit, originally designed for insertion of military spacecraft into geosynchonous orbit. Capable of boosting heavier payloads than 11S861 through use of higher-performance 'sintin' synthetic kerosene fuel.

Model: Proton 17S40. Gross Mass: 14,600 kg (32,100 lb). Empty Mass: 3,300 kg (7,200 lb). Thrust (vac): 85.020 kN (19,113 lbf). Isp: 352 sec. Burn time: 450 sec. Propellants: Lox/Kerosene. Diameter: 3.70 m (12.10 ft). Span: 3.70 m (12.10 ft). Length: 7.10 m (23.20 ft). Country: Russia. No Engines: 1. Motor: RD-58M. Status: Active. Cost $ : 4.000 million. First Flight: 1997. Last Flight: 2002. No Launched: 6. Other designations: Block DM; D-1-e.

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.

Model: Zenit-3. Gross Mass: 17,300 kg (38,100 lb). Empty Mass: 2,720 kg (5,990 lb). Thrust (vac): 84.920 kN (19,091 lbf). Isp: 352 sec. Burn time: 650 sec. Propellants: Lox/Kerosene. Diameter: 3.70 m (12.10 ft). Span: 3.70 m (12.10 ft). Length: 5.60 m (18.30 ft). Country: Russia. No Engines: 1. Motor: RD-58M. Status: In production. Cost $ : 20.000 million. First Flight: 1999. Last Flight: 2008. No Launched: 25. No Failed: 1.

Adaptation of Block D for Zenit.

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© Mark Wade, 1997 - 2008 except where otherwise noted.