EKR (missile)
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The EKR (Eksperimentalniy Krilatiy Raket, or experimental winged rocket) was a Soviet intermediate range cruise missile designed by the Korolev design bureau based on B. Chertok's elaboration of the German R-13 cruise missile design.
By 1951 - 1953 the Korolev bureau had prepared an experimental design, incorporating a prototype astronavigation system. In 1953 an expert commission examined the design and felt that there were still many technical problems needing to be solved, which would be better handled by an aircraft designer rather than Korolev. Additionally, Korolev's chief priority was the development of the R-7 ICBM. In 1954 a government decree authorised the Lavochkin and Myasishchev aircraft design bureaux to proceed in parallel with full-scale development of trisonic intercontinental cruise missiles.
The EKR as designed by Korolev would have been a Mach 3 ramjet, accelerated to supersonic cruise speed by an R-11 rocket booster. Smaller than the missile proposed by the Germans, it would have had a range of 730 km with a flight time of 927 seconds, a lift to drag ratio of 2.51, and a wing area of 3.31 m².
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[edit] Specifications
[edit] General characteristics
- Function: Nuclear cruise missile
- Launch mass: 7,874 kg (17,359 lb)
- Total length: 21.00 m (68.00 ft)
- Launch platform: Launch pad
- Status: Canceled
[edit] Launch booster (stage 1)
- Function: Launch booster
- Engine: S2.253 rocket engine
- Length: 8.29 m (27.19 ft)
- Diameter: 0.88 m (2.88 ft)
- Thrust: 107.333 kN (24,129 lbf)
- Oxidizer: LOx
- Combustible: Kerosene
[edit] Cruise missile (stage 2)
- Engine: 1× EKR ramjet
- Speed : Mach 3
- Range: 730 km
- Flight altitude:
- Warhead: 200 kg (440 lb)
- Length: 9.43 m (30.95 ft)
- Diameter: 0.65 m (2.13 ft)
- Wing span: 2.02 m (6.62 ft)
- Wing area: 3.31 m²
