In 1959 design work and working drawings preparation began to transform second
E-150 prototype into E-152 aircraft. In 1960 the first E-152/1 prototype was built, and its ground tests started at the plant. Upon delivery of R-15-300 engine, the aircraft was presented for production tests on March 16, 1961. Test pilot G.K.Mosolov made the first flight on April 21. Balance weight of 263 kg was mounted in aircraft nose prior to ZP-1 radar delivery. The aircraft made 67 flights, including 5 flights in configuration with
K-9 rocket mock-ups, during production tests carried out at the period from March 16,1961 to January 8, 1962 and from March 20, 1962 to September 11, 1962.
E-152/1 aircraft, designated officially E-166, set three world records:
- test pilot A.V.Fedotov set the world closed-circuit speed record in flight along 100 km route on October 7, 1961. Speed of 2401 km/hour was attained.
- test pilot G.K.Mosolov set the world speed record on July 7, 1962. Average speed of 2681.7 km was attained in flight along 15-25 km speed base in two directions. The speed above 3000 km/hour was attained during one passage.
- on September 11,1962 test pilot P.M.Ostapenko set the world altitude record 22670 m in flight along 15-25 km speed base at the speed of 2500 km/hour.
E-152/2 aircraft was built by July 1961 and transferred to the airfield for flight tests on August 8. System for boundary-layer suction from air intake cone was improved by suppressor grid area increase; sequence of fuel consumption from the tanks was changed to extend the longitudinal stability margin. The first flight was made on September 21, 1961 following the ground tests. Production tests were continuing till July 3, 1962, and were ceased after 16th flight (test pilots P.M.Ostapenko and A.V.Fedotov). After the program cancellation, the E-152/1 and E-152/2 aircraft, under the names E-152M/1 and E-152M/2, were re-equipped for S-155 intercept complex development.
E-152 is the all-metal mid-wing monoplane with delta wing.
Fuselage consisted of nose and tail parts. The nose part had a semimonocoque design. Nose air intake had fixed radio-transparent three-stage cone and movable ring (lip) controlled in flight. The tail fuselage part had monocoque design. Skin of this fuselage part is made from thin steel sheets strengthened by corrugated metal bands. Ring-slot brake parachute was located in ventral strake.
Delta-wing had a thin TSAGI profile with 53о 47' sweepback: 3.5% at the wing root and 5% at the wingtip.
Powerplant consisted of R-15-300 turbojet engine. Engine and afterburner were joined together by a telescopic link. Engine compartment was cooled in flight by ram air tapped from a channel. Air left the engine compartment through an ejection slot between a gas jet and tail cone. On the ground cooling was provided through depression inside fuselage provoked by air jet ejection effect. In this case air entered engine compartment through inlet valves located on external skin. Total fuel tank capacity was 4960 l. Suspension of external fuel tank of 1500 l capacity was provided.
Aircraft had tricycle landing gear fitted out with hydro-nitrogen shock-absorbers. The nose undercarriage leg was retracted forward into fuselage well. This leg had a mechanism to return the wheel in neutral position. The main legs were retracted into wing wells; their wheels turned about leg struts were located in fuselage wells. The nose leg had a KT-93 wheel, size 660x160; the main legs were equipped with KT-69/4 wheels, size 880x230.
Aircraft equipment consisted of: ZP-1 radar, VB-158 computer with set of sensors, AP-39 autopilot, SAZO-SPK system, KSI compass system, AGD-1 attitude indicator, "Put-2" flight instrument set, RSIU-5 "Dub" VHF radio, ARK-10 "Ingul" radio compass, SPO-2M "Khrom" IFF transponder, SOD-57MU active responder. Aircraft armament consisted of two K-9 rockets attached to launchers located at the wingtips.
|Dimensions & Weight|
|Wing Span, m||8,793|
|Wing Area, m2||42,02|
|Take-off weight, kg||14350|
|Empty weight, kg||10900|
|Engines||1 Turbojet R-15B-300|
|Thrust (max / форсаж), kgf (kN)||6840 / 10210 (98,07)|
|Max. speed at altitude 15,4 km, km/h (M=)||3030 (2,82)|
|Landing speed, km/h||270|
|Practical ceiling, m||22680|
|Time to climb, min||10000 m||3,67|
|Take-off run (with missiles), m||1070 (1185)|
|Landing run, m||1270|
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