EKR Cutaway

Intermediate range cruise missile. Family:

B Chertok of NII-8 took the preliminary German R-13 cruise missile design and elaborated it, including consideration of the key problem of long-range automatic astronavigation. By 1951 to 1953 Korolev's design bureau had prepared an experimental design, the EKR. I Lisovich had developed a prototype astronavigation system that met the necessary specifications, and solution of basic problems in use of steel and titanium hot airframe technology had been solved at VIAM (All-Union Institute of Aviation Materials) and MVTU Bauman Institute. An expert commission in 1953 examined the EKR design and felt that there were still many technical problems to be solved, most of which were better handled by an aircraft designer rather than Korolev.

Further, Korolev had to place the highest priority on development of the R-7 ICBM. Therefore a final government decree on 20 May 1954 authorised the Lavochkin and Myasishchev aircraft design bureaux to proceed in parallel with full-scale development of trisonic intercontinental cruise missiles. The Eksperimentalniy krilatiy raket (experimental winged rocket) as designed by Korolev would have been a Mach 3 ramjet, accelerated to supersonic cruise speed by an R-11 booster. Smaller than the operational vehicle proposed by the Germans, it would have a range of 730 km with flight time of 927 seconds, a lift to drag ratio of 2.51, and a wing area 3.31 square meters.

Manufacturer: Korolev. to a: 730 km trajectory. Liftoff Thrust: 93.000 kN (20,907 lbf). Total Mass: 7,874 kg (17,359 lb). Core Diameter: 0.88 m (2.88 ft). Total Length: 21.00 m (68.00 ft). Standard warhead mass: 200 kg (440 lb). Maximum range: 730 km (450 mi).

• Stage1: 1 x .

• Stage2: 1 x EKR Stage 2. Gross Mass: 1,484 kg (3,271 lb). Empty Mass: 1,167 kg (2,572 lb). Motor: 1 x EKR Ramjet. Thrust (vac): 6.129 kN (1,378 lbf). Isp: 1,580 sec. Burn time: 800 sec. Length: 9.43 m (30.95 ft). Diameter: 0.65 m (2.13 ft). Propellants: Air/Kerosene.

1949 October - Albring G-3 cruise missile German aerodynamicist Albring designed the G-3 missile for the Russians. This would use a rocket-powered Groettrup-designed G-1 as the first stage. The cruise stage would have an aerodynamic layout like that of the Saenger-Bredt rocket-powered antipodal bomber of World War II. Cruising at 13 km altitude, the supersonic missile would carry a 3000 kg warhead to a range of 2900 km. This was an alternate approach to Ustinov's 3000 kg over 3000 km range missile requirement of April 1949. This design would be elaborated at Korolev's bureau into the EKR ramjet design of 1953.

1953 January - Expert commission examined the EKR design Spacecraft: M-42. In 1951 to 1953 Korolev's design bureau had prepared an experimental trisonic ramjet design, the EKR.The expert commission ifelt that there were still many technical problems to be solved, most of which were better handled by an aircraft designer rather than Korolev. Further, Korolev had to place the highest priority on development of the R-7 ICBM. Therefore a final government decree on 20 May 1954 authorised the Lavochkin and Myasishchev aircraft design bureaux to proceed in parallel with full-scale development of trisonic intercontinental cruise missiles.

1953 February 13 - Authorisation for development of Soviet intermediate and intercontinental range missiles. Council of Soviet Ministers (SM) Decree 'On approval of work on themes T1 and T2, on approval of work on the R-5, R-11, and EKR missiles, and on transferring draft project work for the R-12 from NII-88 to SKB-586' was issued. The decree set forth three phases of state trials tests for the R-5 missile.