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Soyuz and GR-1 ICBM
Soyuz and GR-1 ICBM - Dynamic test models of Soyuz and GR-1 ICBM

Credit: © Mark Wade. 30,995 bytes. 229 x 432 pixels.



Family: N. Country: Russia. Status: Cancelled 1964. ASCC Reporting Name: Scrag. Article Number: 8K713.

The Global Rocket 1 (GR-1) requirement of 1961 called for a system to place a large 1,500 kg nuclear warhead equipped with a deorbit rocket stage into a low earth orbit of 150 km altitude. The warhead could approach the United States from any direction, below missile tracking radar, so little warning was available. Not only could such a missile hit any point on earth, but the enemy would also be uncertain when it would be deorbited onto target. The main disadvantage was lower accuracy of the warhead in comparison to an ICBM.

Chelomei proposed his UR-200 for the requirement, while Yangel offered the R-36, and Korolev the 8K713. Korolev insisted on sticking to the liquid oxygen/kerosene propellants of his R-9 ICBM, despite the military's preference for the more toxic but storable propellants used by Yangel and Chelomei. Korolev considered the 8K713 a low risk project, using rocket elements already in development or production by his bureau:

The draft project for the GR-1 was completed in May 1962. Planning and drawing release for the GR-1 was completed on 24 September 1962 with test flights originally scheduled to begin in the third quarter of 1963. However continued development problems with the NK-9 engine resulted in continual delays. Finally in 1964 Korolev's GR-1 was cancelled and Yangel’s R-36 was selected for the mission.

Cancellation of the 8K713 had a significant and perhaps fatal impact on the project for Korolev’s N1 moon rocket: it was hoped that the GR-1 could be used to prove N1 engines and guidance systems. In a final bit of disinformation, the 8K713 mock-up was paraded in Red Square, and identified by NATO as an operational 'Scrag' ICBM. This confused Western defence analysts for many years to come.


Specifications

LEO Payload: 1,500 kg. to: 150 km Orbit. at: 52.0 degrees. Payload: 4,000 kg. to a: 14,000 km trajectory. Liftoff Thrust: 155,000 kgf. Total Mass: 113,500 kg. Core Diameter: 2.7 m. Total Length: 39.0 m.


GR-1 Chronology


- 1962 May -
1962 Sep 24 -
1962 Oct 13 -

Bibliography:



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