MiG-27 - Domestic fighter-bomber
Domestic fighter-bomber was based on the fighter MiG-23. Operation MiG-23 showed the need to improve the basic aircraft the Air Force, as it in its combat and flight characteristics inferior uniformity of the Su-17.
Modernization of the aircraft was carried out in three main areas: design, strengthening and improvement of weapons (introduction) board systems. In creating essentially a new aircraft had a lot of work the chief designer and his first deputy MR Waldenberg.
By the end of 1974, the industry has already produced some copies of the MiG 50-27.
The plane had a variable sweep wing in flight. As the power plant was used a double-boosted turbojet engine: the first machines AL-21F-3, in the series - R29B-300. Power 78 / 113 kN without afterburner and afterburner.
MiG-27 has a normal aerodynamic scheme of arrangement, which includes a high-wing variable sweep, all-moving horizontal tail and tricycle landing gear.
Airframe consists of the following structural units:
the nose of the fuselage;
head of the fuselage with the fuel tanks, compartments zakabinnogo special equipment, fixed part of the wing and the side air intakes;
movable wing console spoilers, flaps, controlled socks and tanks;
tail section with the rudder, keel, stabilizer and the fuel tank.
The fuselage is in the MiG-27 made by the type of semi-monocoque, has a welded and riveted construction. Riveted part is made of sheet aluminum alloy bearing elements are stamped from aluminum and steel. Welded part made of separate panels for argon-arc or resistance welding. Hatches that are frequently opened for maintenance of the unit, made for easy folding.
The structure of the wing of the aircraft consists of two fixed parts which are fixed to the fuselage, and two rotary trapezoidal console. Sweep angle brackets set in three positions: 16 °, 45 ° and 72 °. Central compartment occupied by the main power element fixed part. His welded to frames and № 18 № 20. The bay units are placed in charge of the consoles and rotate the wing fuel tanks.
Rotary Wing consists of two side members. Turn console provides a hydraulic motor, included in CPC-1.
The side walls are made of aluminum alloy for hot stamping technology. The wing compartments are sealed. Above is a two-piece wing spoiler.
Flap three sections: the first (bow) section is made of titanium alloy, the next two - aluminum alloy. The flap control mechanisms are utilized hydraulic cylinders total. Each section is controlled by a separate hydraulic cylinder.
Gap between the fuselage and the consoles released and retracted the gap between the console and the fuselage close movable and stationary plates that reinforce the structure and provide the required sealing during a heavy load on the wing.
Tsentralnopovorotnoe horizontal tail, it includes a front stringer, spar, a set of ribs and planking. The central part is milled panels, nose and tail - riveted. Stabilizer composed of two halves, each of which rotates on two bearings. The board set a combined root rib bearing inside the stabilizer - the roller end.
It consists of the rudder and keel. The components of the keel frame front stringer two spar, a set of stamped sheet metal ribs, rib milled № 9, side ribs. The middle part of the keel is completely manufactured from milled panels. Equipped with radio transparent upper part ending with an antenna.
Mounting the rudder to the keel was performed at three points. The sock steering dampers installed CD-16-5000-0 A. Casing made of aluminum alloy.
The canopy consists of a movable part and a peak that rises and falls under the influence of the air cylinder. The lantern is equipped with the drop in the emergency management system and a hinged part. The latter is responsible for opening and closing the canopy, its fixation and sealing. The windscreen is equipped with electric heating system, which counteracts the occurrence of icing lantern. In order to counter the emergence of misting inside the cab lantern placed on the perimeter of the pipe through which the hot air blowing. At the time of operation of the fighter on the ground (standing position or performance of taxiing at speeds up to 30 km / h) cab ventilation can be achieved by raising the lantern on 100 mm.
For the rear view from the cockpit is equipped with a viewing device CU-27AMSH, which is mounted on a folding of the flashlight. It also placed two mirrors, which were visible in the plane of the wing.
MiG-27 had a tricycle landing gear. Nose wheel had composed two tubeless wheel size 520h140, basic support - one of tubeless wheel size 840h360.
The main desk is composed of welded beams, console poluvilki, swivel head, remote damper mechanism and an additional turn. Poluvilka and shock absorber fixed on swivel head, which was installed on the beam. During the landing gear retracted plate cylinder that touches the beam while performing a U-turn and poluvilki wheel. Inside there is a nose landing gear wheel return to its original position during flight.
The design of the landing gear; a mud guards that prevent ingress of dirt and small objects in the air vents. Their use allows for taxiing and takeoff on unpaved runways.
The nose landing gear wheel turning mechanism installed MRK-Z2-25, which is responsible for the deviation angle of the front wheels is proportional to the deviation of the pedals in the cockpit controls.
MiG-27 installed pneumatic braking system with disc brakes.
It comprises six wing tanks, five fuselage and two compartments, which involve fuel upon the occurrence of negative overloads.
Fuselage tank compartment № 1 placed near the air duct of the motor, tank number 1A placed under zakabinnogo compartment tank № 3 placed on the engine and carried out in the form of half-rings, № 4 tank located in the rear fuselage tank № 2 - the main expenditure.
The aircraft has an automatic system responsible for the sequence out of fuel in the tanks.
The wing have a common PTB 800 liter capacity and can be used only when the wing in position 16 ° to the front edge.
MiG-27 has a centralized system of filling all tanks except the wing, also allowed refueling through an open mouth of a fuel tank.
The performance characteristics of the MiG-27
Wingspan, m 7,40-13,8
Wing sweep, hail 16-72
Length, m 16,46
Height, m 3,95
Wing area, m2 27,26
Empty weight, kg 10 700
Launch weight, kg: normal 15 500
Launch weight, kg: maximum 20 100
The speed at the ground, km / h .1350 (M = 1,1)
The speed at an altitude of 11000 m
km / h 1805 (M = 1,7)
Radius, km 575-1370
The armament of the aircraft.
One gun missile of class "air-to-surface X-23 et al.
missiles "air-air" P-3S et al.
cassette with unguided rockets
different purpose and class bomb
MiG-27 6 can carry bombs FAB-500.
The aircraft experienced some of the best test pilots: A. Fedotov, VE Menitsky, Boris Orlov, AG Fastovets. In the creation of the plane their work can not be overestimated.
However, there have been serious failure: failure in flight, engine failure, defects in electrical equipment, the difficulties in operation.
The tests of the MiG-27 were hard, people died. Experienced pilots A. Bezhevets hardly brought the aircraft from a spin at low altitude - in the dense layers of air. In 1980 it was not out of the corkscrew and the pilot was killed L. Ivanov. He died on the MiG-27 HSU N. Ricks.
Despite the difficulties of the fighter-bomber MiG-27 he produced commercially and has been one of the major Air Force aircraft for a long time.
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