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UR-500
Part of Proton Family
UR-500DH1
UR-500DH1
Memorial Museum of Cosmonautics, June 1994
Credit: © Dietrich Haeseler
The original UR-500 two stage configuration was designed as a monster ICBM. It was flown four times from 1965, but never deployed as an operational missile. The design was succeeded by three and four stage versions for launching of large payloads into space.

AKA: 8K82;Atlantis;D;Gerkules;Proton 2;SL-9;Ural. Status: Retired 1966. First Launch: 1965-07-16. Last Launch: 1966-07-06. Number: 4 . Payload: 8,400 kg (18,500 lb). Thrust: 8,847.00 kN (1,988,884 lbf). Gross mass: 595,490 kg (1,312,830 lb). Height: 46.28 m (151.83 ft). Diameter: 4.15 m (13.61 ft). Span: 7.40 m (24.20 ft). Apogee: 200 km (120 mi).

Data is accurate. Tsniimash has 1:10 model.

LEO Payload: 8,400 kg (18,500 lb) to a 200 km orbit at 65.00 degrees. Standard warhead: 12,200 kg (26,800 lb). Maximum range: 10,000 km (6,000 mi). Number Standard Warheads: 1. Warhead yield: 100,000 KT.



Family: orbital launch vehicle. Country: Russia. Engines: RD-0210, RD-253-11D48. Spacecraft: Kosmoplan, N-4. Launch Vehicles: Proton. Launch Sites: Baikonur, Baikonur LC81/23. Stages: UR-500-2, Proton K-1. Agency: Chelomei bureau.

1965 July 16 - . 11:16 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: UR-500.
  • Proton 1 - . Payload: N-4 s/n 1. Mass: 8,300 kg (18,200 lb). Nation: Russia. Related Persons: Chelomei. Agency: MOM. Program: Proton. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: N-4 . Decay Date: 1965-10-11 . USAF Sat Cat: 1466 . COSPAR: 1965-054A. Apogee: 578 km (359 mi). Perigee: 181 km (112 mi). Inclination: 63.4000 deg. Period: 92.20 min.

    The first launch of the Proton launch vehicle was not without problems. A leak in the oxidiser pipeline resulted in nitrogen tetroxide spilling on electrical wires. The question was: proceed with the launch or abort? Chelomei decided to go ahead, and on 16 July 1965 the first UR-500 successfully launched the Proton 1 satellite. In the first hours after launch specialists from OKB-52 could only receive signals in the first hours that indicated the satellite was ‘alive’. However it later functioned normally and provided physics data on ultra-high-energy cosmic particles for 45 days.

    At the first launch the rocket was called ‘Gerkules’ (other sources say ‘Atlantis’), as indicated by the large symbol on the second stage skin. This name was however was not taken up.


1965 November 2 - . 12:28 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: UR-500.
  • Proton 2 - . Payload: N-4 s/n 2. Mass: 8,300 kg (18,200 lb). Nation: Russia. Agency: MOM. Program: Proton. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: N-4 . Decay Date: 1966-02-06 . USAF Sat Cat: 1701 . COSPAR: 1965-087A. Apogee: 608 km (377 mi). Perigee: 189 km (117 mi). Inclination: 63.5000 deg. Period: 92.50 min. High energy physics laboratory. Investigation of ultra-high-energy cosmic particles. .

1966 March 24 - . 21:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: UR-500. FAILURE: Second stage malfunction.. Failed Stage: 2.
  • N-4 s/n 3 - . Payload: N-4. Mass: 8,300 kg (18,200 lb). Nation: Russia. Agency: RVSN. Program: Proton. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: N-4. Decay Date: 1966-03-24 .

1966 July 6 - . 12:57 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: UR-500.
  • Proton 3 - . Payload: N-4 s/n 4. Mass: 8,300 kg (18,200 lb). Nation: Russia. Agency: MOM. Program: Proton. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: N-4 . Decay Date: 1966-09-16 . USAF Sat Cat: 2290 . COSPAR: 1966-060A. Apogee: 594 km (369 mi). Perigee: 185 km (114 mi). Inclination: 63.5000 deg. Period: 92.30 min. Space station 'Proton 3'. Investigation of ultra high energy cosmic particles .


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