Site map

Site update log

About this site

About the author



At the beginning of the 1960, Vladimir Chelomei, the head of the OKB-52 design bureau, proposed Nikita Khrushchev to develop a series of the "versatile rockets" or in Russian abbreviation -- the UR series. Based on the each vehicle's expected liftoff mass, they received designations: UR-100, UR-200 and UR-500.

Chelomei's proposal competed with several other ICBM programs developed at the time by OKB-586 design bureau in Dnepropetrovsk and OKB-1 in Podlipki. The UR-200 offered similar capabilities to the R-36 ICBM, under development in OKB-586.

Chelomei advertised UR-200 as the launcher of the anti-satellite weapons, the ocean surveillance satellites and also as an intercontinental missile. In the ICBM role, the UR-200 could carry up to three warheads. The orbital version of the vehicle, designated UR-200B (8K83) was also under consideration. (74)

Nikita Khrushchev gave go ahead to both projects: the UR-200 and R-36, however only one of the vehicles was expected to be accepted for mass production. The government decrees authorizing the UR-200 development were issued on March 16 and August 1, 1961.

The construction of the launch complex for the UR-200 flight tests started at Site 90 on the left (western wing) of the NIIP-5 test range in Tyuratam (today Baikonur). The silo launches for the UR-200 were also planned. The underground pads would be based on the Sheksna-V complex developed for the R-16 ICBM.

The first stage of the two-stage UR-200 missile was equipped with an RD-0202 four-engine cluster, whose combustion chambers were designed to gimbale to control the missile in flight.

Test launches and termination

The preliminary design of the UR-200 rocket was completed in July 1962.

After several delays due to development problems, the first test launch of the rocket took place on November 5, 1963 and was unsuccessful. The second vehicle, launched on April 11, 1964, also failed. One more launch took place on May 15. During next two launches on May 30 and June 17, 1964, Marshall Grechko, the Minister of Defense at the time, was present at Baikonur to view the launches. One more launch took place on August 1, 1964.

On Sept. 24, 1964, Nikita Khrushchev personally viewed the UR-200 launch in Baikonur, only days before he was ousted from power in a bloodless coup in October 1964. During the same visit to Baikonur, Khrushchev also witnessed the launch of the UR-200's competitor -- the R-36 ICBM developed at OKB-586 design bureau (now KB Yuzhnoe in Dnepropetrovsk).

In the wake of the visit to Baikonur, Khrushchev made a decision to terminate the UR-200 project in favor of the R-36. In his memoirs, (87) published in 2000, Khrushchev's son, Sergei, who worked for Chelomei, still pondered the question why his father preferred Yangel's R-36, to the UR-200. "I don't know why, since rockets seemed almost identical," Sergei Khrushchev wrote.

According to the official publication (101) of the Khrunichev enterprise, which manufactured the UR-200 missile, the vehicle was not designed to stay fueled for the long period of time a flaw significantly increasing the pre-launch processing.

Upon cancellation, two more launches of the already manufactured UR-200 missiles took place on October 2 and October 20, 1964. Since the last launch was conducted after Khrushchev's fall, Chelomei tried to appeal to Michael Kosygin, then the Chairman of the Soviet of Ministers in the last-ditch attempt to revive his creation. Chelomei however, received less than warm response to his telephone call to Kremlin. According to Sergei Khrushchev, in response to Chelomei's report about successful launch, Kosygin rudely told that the rocket launches is responsibility of the supervising minister, and in the future Chelomei should report to him. (87)



Specifications of the UR-200 rocket:

Number of stages
Length of the vehicle
  • 32 meters (without a warhead)
  • 34.65 meters (with a warhead)
3 meters (with stabilizers - 4.2 meters)
Weight (fueled)
136 - 138 tons
Oxidizer Nitrogen tetroxide
Weight of propellant -
First launch 1963
Launch sites Tyuratam (two pads at Site 90)

Flight range:

12,000 km (with light warhead) 14,000 (with heavy warhead)
Warhead type (single):
Termonuclear 5 Megatons and 15 megatons
Stage I -

16.9 meters (19.4 meters with interstage section)

Diameter 3.0 meters

RD-0202 engine consisting of:

  • three one-chamber RD-0203 engines
  • one RD-0204 engine
Stage II -

12.9 meters

Diameter 2.2 meters

RD-0205 engine consisting of:

  • One (1) one-chamber RD-0206 main engine
  • One (1) four-chamber RD-0207 steering engine


Key participants in the development of UR-200:

Element Developer Leading designer Location
Overall design
V. Chelomei
The propulsion system (two stages)
OKB-154 (KBKhA)
S. Kosberg
The launch complex (surface)
Branch 2 of OKB-52
V. M. Barushev
Control system
N. A. Pilugin
The launch complex (silo)
E. G. Rudyak
Termo-nuclear warhead
B. V. Litvinov


Launch chronology for the UR-200 ICBM:

(All launches from Baikonur's Site 90; the first six launches from the left pad, the last three from right pad)


Nov. 5


April 11

May 15

May 30

June 17

Aug. 1

Sept. 24

Oct. 2

Oct. 20


The launch of the UR-200 missile in Baikonur. Credit: GKNPTs Khrunichev

The rollout of the UR-200 missile to the launch pad at Site 90 in Baikonur. Credit: GKNPTs Khrunichev

The assembly of the UR-200 missile. Credit: GKNPTs Khrunichev

The first stage of the UR-200 missile. Credit: GKNPTs Khrunichev

Models of the UR-200 (left) and UR-100 missiles shown to the same scale. Copyright © 2000 Anatoly Zak

A mockup of the UR-200 rocket used for dynamic tests. Copyright © 2000 by Anatoly Zak /

The second stage of the UR-200 missile. Copyright © 2000 Anatoly Zak

The propulsion system of the second stage of the UR-200 missile. Copyright © 2000 Anatoly Zak