UR-500DH1
Memorial Museum of Cosmonautics, June 1994
Credit: © Dietrich Haeseler
Russian orbital launch vehicle. 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.
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. Failures: 1. First Fail Date: 1966-03-24. Last Fail Date: 1966-03-24. 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.
AKA: Atlantis; Proton 2; UR-500; SL-9; 8K82; Ural; Gerkules; D.
Status: Retired 1966.
Gross mass: 595,490 kg (1,312,830 lb).
Payload: 8,400 kg (18,500 lb).
Height: 46.28 m (151.83 ft).
Diameter: 4.15 m (13.61 ft).
Span: 7.40 m (24.20 ft).
Thrust: 8,847.00 kN (1,988,884 lbf).
Apogee: 200 km (120 mi).
First Launch: 1965.07.16.
Last Launch: 1966.07.06.
Number: 4 .
More... - Chronology...
Associated Countries
Associated Spacecraft
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Kosmoplan Russian Mars orbiter. Cancelled 1965. Beginning in the late 1950's, Chelomei began studying use of his encapsulated cruise missile technology for spacecraft. A whole family of unmanned spacecraft, dubbed Kosmoplans, would be built using modular elements. More...
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N-4 Russian cosmic ray astronomy satellite. 4 launches, 1965.07.16 (Proton 1) to 1966.07.06 (Proton 3). Physics experiments. Space station "Proton 1". Investigation of ultra-high-energy cosmic particles. More...
Associated Engines
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RD-0210 Kosberg N2O4/UDMH rocket engine. 582.1 kN. Isp=326s. Cluster of four similar engines used in second stage of Proton - one providing tank pressurization (8D412K/RD-0211) and three (8D411K/RD-0210). Staged combustion cycle. First flight 1965. More...
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RD-253-11D48 Glushko N2O4/UDMH rocket engine. 1635 kN. Isp=316s. Six gimballed single chamber RD-253s provide the first stage power for the UR-500 Proton launch vehicle. First flown in 1965. More...
See also
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Proton The Proton launch vehicle has been the medium-lift workhorse of the Soviet and Russian space programs for over forty years. Although constantly criticized within Russia for its use of toxic and ecologically-damaging storable liquid propellants, it has out-lasted all challengers, and no replacement is in sight. More...
Associated Manufacturers and Agencies
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Chelomei Russian manufacturer of rockets, spacecraft, and rocket engines. Chelomei Design Bureau, Reutov, Russia. More...
Associated Programs
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Proton Investigation of ultra-high-energy cosmic particles. More...
Associated Launch Sites
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Baikonur Russia's largest cosmodrome, the only one used for manned launches and with facilities for the larger Proton, N1, and Energia launch vehicles. The spaceport ended up on foreign soil after the break-up of Soviet Union. The official designations NIIP-5 and GIK-5 are used in official Soviet histories. It was also universally referred to as Tyuratam by both Soviet military staff and engineers, and the US intelligence agencies. Since the dissolution of the Soviet Union the Russian Federation has insisted on continued use of the old Soviet 'public' name of Baikonur. In its Kazakh (Kazak) version this is rendered Baykonur. More...
Associated Stages
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Proton K-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 450,510/31,100 kg. Thrust 10,470.16 kN. Vacuum specific impulse 316 seconds. More...
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Proton-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 134,900/13,180 kg. Thrust 2,399.19 kN. Vacuum specific impulse 325 seconds. Proton UR-500 second stage. Flew only on two-stage version of Proton. Empty mass is correct; all other values estimated based on UR-500 Stage 2 original design and UR-500K stage 2 figures. More...
UR-500 Chronology
1965 July 16 - .
11:16 GMT - .
Launch Site:
Baikonur.
Launch Complex:
Baikonur LC81/23.
LV Family:
Proton.
Launch Vehicle:
UR-500.
LV Configuration: UR-500 107207-01 (207).
1965 November 2 - .
12:28 GMT - .
Launch Site:
Baikonur.
Launch Complex:
Baikonur LC81/23.
LV Family:
Proton.
Launch Vehicle:
UR-500.
LV Configuration: UR-500 209.
- Proton 2 - .
Payload: N-4 s/n 2. Mass: 8,300 kg (18,200 lb). Nation: USSR. 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. Summary: 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.
LV Configuration: UR-500 211.
FAILURE: Second stage malfunction..
Failed Stage: 2.
- N-4 s/n 3 - .
Payload: N-4. Mass: 8,300 kg (18,200 lb). Nation: USSR. Agency: RVSN. Program: Proton. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: N-4. Decay Date: 1966-03-24 . COSPAR: F660324A.
1966 July 6 - .
12:57 GMT - .
Launch Site:
Baikonur.
Launch Complex:
Baikonur LC81/23.
LV Family:
Proton.
Launch Vehicle:
UR-500.
LV Configuration: UR-500 212.
- Proton 3 - .
Payload: N-4 s/n 4. Mass: 8,300 kg (18,200 lb). Nation: USSR. 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. Summary: Space station 'Proton 3'. Investigation of ultra high energy cosmic particles .
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