Soyuz 11A510 (original) (raw)

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Soyuz 11A510

Part of R-7

Russian orbital launch vehicle. Version of R-7 launch vehicle with Vostok second stage and unknown third stage used only twice to launch prototype RORSATs. These satellites were originally to have been launched on the cancelled UR-200 launcher, and operational satellites used Tsyklon-2 launchers.

AKA: 11A510;A;SL-5;Vostok 11A510. Status: Retired 1966. First Launch: 1965-12-27. Last Launch: 1966-07-20. Number: 2 . Payload: 4,500 kg (9,900 lb). Thrust: 4,037.70 kN (907,711 lbf). Gross mass: 275,000 kg (606,000 lb). Height: 31.00 m (101.00 ft). Diameter: 10.30 m (33.70 ft). Apogee: 200 km (120 mi).

LEO Payload: 4,500 kg (9,900 lb) to a 200 km orbit at 65.00 degrees.

Stage Data - Vostok 11A510

Stage 0. 4 x Soyuz 11A511-0. Gross Mass: 43,000 kg (94,000 lb). Empty Mass: 3,550 kg (7,820 lb). Thrust (vac): 994.300 kN (223,528 lbf). Isp: 314 sec. Burn time: 118 sec. Isp(sl): 257 sec. Diameter: 2.68 m (8.79 ft). Span: 2.68 m (8.79 ft). Length: 19.60 m (64.30 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-107-11D511. Other designations: 11S59 Blocks A,B,V,G. Status: In Production.
Stage 1. 1 x Soyuz 11A511-1. Gross Mass: 100,500 kg (221,500 lb). Empty Mass: 6,500 kg (14,300 lb). Thrust (vac): 977.700 kN (219,796 lbf). Isp: 315 sec. Burn time: 292 sec. Isp(sl): 252 sec. Diameter: 2.95 m (9.67 ft). Span: 2.95 m (9.67 ft). Length: 27.80 m (91.20 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-108-11D512. Other designations: 11S59 Block D. Status: In Production.
Stage 2. 1 x Vostok 8A92-2. Gross Mass: 7,775 kg (17,140 lb). Empty Mass: 1,440 kg (3,170 lb). Thrust (vac): 54.900 kN (12,342 lbf). Isp: 326 sec. Burn time: 369 sec. Diameter: 2.56 m (8.39 ft). Span: 2.56 m (8.39 ft). Length: 2.84 m (9.31 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-0109. Status: Out of Production.
Stage 3. 1 x Tsyklon 2-3. Gross Mass: 3,200 kg (7,000 lb). Empty Mass: 400 kg (880 lb). Thrust (vac): 77.960 kN (17,526 lbf). Isp: 317 sec. Burn time: 112 sec. Diameter: 2.00 m (6.50 ft). Span: 2.00 m (6.50 ft). Length: 2.50 m (8.20 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: RD-861. Status: In Production. Comments: Integral portion of payload.

Family: orbital launch vehicle. Country: Russia. Spacecraft: US-A. Projects: RORSAT. Launch Sites: Baikonur, Baikonur LC31. Stages: Vostok 8A92-2, Soyuz 11A511-0, Soyuz 11A511-1, Tsyklon 2-3. Agency: Korolev bureau.

1965 December 27 - . 22:19 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A510.

Cosmos 102 - . Mass: 3,800 kg (8,300 lb). Nation: Russia. Agency: MOM. Program: RORSAT. Class: Surveillance. Type: Naval Radarsat. Spacecraft Bus: Kosmoplan. Spacecraft: US-A. Decay Date: 1966-01-13 . USAF Sat Cat: 1867 . COSPAR: 1965-111A. Apogee: 267 km (165 mi). Perigee: 205 km (127 mi). Inclination: 64.90 deg. Period: 89.20 min. Prototype RORSAT hardware using chemical batteries in place of nuclear reactor..

1966 July 20 - . 09:07 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A510.

Cosmos 125 - . Mass: 3,800 kg (8,300 lb). Nation: Russia. Agency: MOM. Program: RORSAT. Class: Surveillance. Type: Naval Radarsat. Spacecraft Bus: Kosmoplan. Spacecraft: US-A. Decay Date: 1966-08-02 . USAF Sat Cat: 2351 . COSPAR: 1966-067A. Apogee: 260 km (160 mi). Perigee: 204 km (126 mi). Inclination: 64.90 deg. Period: 89.10 min. Prototype RORSAT hardware using chemical batteries in place of nuclear reactor. Lost on the 52nd revolution as a result of a possible failure in the chemical power units placed on board instead of the nuclear BES-5..

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