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MiG-17 Technical Description

The MiG-17 is a classic midwing. Wing is all-metal two-spar, with the inner strut. It consists of the center section and the two consoles. Sweep angle of the wing leading edge at the root portion is 45 deg. At the ends of 42 deg. The ailerons area of 1.6 m2 with a deflection angles in the range 18 to the axis of rotation have an internal aerodynamic compensation. On the left aileron trim was set. Shields-flaps with the axis of rotation of the moving area of 2.86 m2 rejected take-off at an angle of 20 degrees and landing at 60 degrees.

The fuselage is semi-monocoque with a maximum diameter of 1.45 m and a length of 8.805 m. It consists of the nose and tail portions having technological and operational connector of frames No. 13. This construction provides easy assembly and disassembly of the engine.

In the front part of the fuselage is hermetic type cockpit ventilation. Lantern consists of a peak and shifts back section, equipped with de-icing fluid. To improve visibility in the rear hemisphere sliding part has a periscope.

The pilot sits in the ejection seat for leaving the aircraft by pressing the handles located on the handrail of the seat. In the last series of the MiG-17 established chairs with protective shutter. The forward fuselage are also input channel inlet (at the beginning it is common, but the further costs for the two bypassing the cockpit), carriage with artillery installation, instrumentation and radio equipment, the nose landing gear niche with her cleaning.

The aft fuselage has two fuel tanks. On the sides are set forth operable brake pads with a deflection angle of 55 degrees .. (aircraft of the first series - 50 degrees ..). Kinematics management mechanism shields designed so that in case of hydraulic pipe fracture, they are closed under the pressure of the air. Under the aft fuselage is a small keel to increase the stock of directional stability.

The tail assembly of the classical scheme, swept. Vertical tail area is - 4.26 m 2, the horizontal - 3.1 m2. Vertical tail recruited from profiles of NACA-M relative thickness of 8.8% of the flow consists of the keel and rudder. Last is the area 0.947 m2 and the deflection angles in the range of -25 degrees. to +25 deg. Angle swept vertical tail leading edge - 55 degrees. 41 ', the narrowing-2.79. The horizontal tail with extension and contraction of 3.26 2.0 includes a stabilizer and elevator area of 0.884 m2, recruited from NACA-M profiles with a relative thickness of 8.7% of the flow. The elevator is deflected upward at an angle of 16 deg., And down - 21 degrees.

Chassis is a tricycle, with the nose wheel. The main wheels - brake size 660x160 mm, the nose wheel size of 480x200 mm. Track chassis - 3,849 m, the longitudinal base - 3,368 m. Cleaning and landing gear are made hydraulics, emergency pneumatic system graduates. Parking at the angle of the aircraft pneumatics .. 2 degrees 15 '.

Control of the aircraft by using rudder and aileron, cinematically connected with the control stick and rudder-related pedals. To reduce the effort on the control handle in the channels of pitch and roll set irreversible hydraulic actuators BU-1M. Elevator control is duplicated cable runs.

MiG-17 and MiG-17P installed TRD VK-1A with a centrifugal compressor on the MiG-17F and MiG-17PF-VK-1F, characterized by the presence of the afterburner. Engine life in 1952 amounted to 250 hours.

Maximum engine thrust is achieved at the surface at zero speed. Link sharply falls from a height, for example, to 10 m 000 at a flight speed of 900-1000 km / h is 1500-1600 kg afterburner and 1030-1050 kg - takeoff. At a constant altitude engine thrust at takeoff speed to 500-700 km / h is reduced, and then begins to gradually increase. In afterburner mode, increase the thrust begins with the speed of 500-600 km / h.

The engine cooling air flowing between its walls and the fuselage. Some airplanes were installed engines VK-1F with reinforced afterburner, allow adjustment of thrust in afterburner by throttling, to reduce engine speed to 10,870 rev / min. In accordance with the directive of the Air Force from 22 January 1959 it was forbidden to set the pace in excess of 11 350 r / min, and only in an emergency flight was allowed to 11,560 rev / min. At low revs increased by 8% and the length of the runway by 20-25% during the climb. Maximum speed, depending on the flight altitude was reduced by 10-30 km / h, service ceiling was reduced to 500 m.

Fuel was in the fuselage and wing. The aft fuselage mounted two tanks: one soft, rubber-fabric, the other - two-piece metal. The wings were placed six fuel tanks, two with a capacity of 65 liters, 75 liters for two and two for 45 liters. Under the wing were suspended two types of drop tanks with a capacity of 400 liters each - on racks and fairing. The first of these diameter 0.526 m and 3.01 m in length, the second length and a diameter of 0.52 2.81 m. Both types have stabilizers.

The hydraulic system of the MiG-17 consisted of a pump, a tank with a mixture of hydraulic and air battery discharge machine.

The equipment of the aircraft were connected radio RSIU-3 "Maple" (in operation is replaced by RSIU-4B "oak" or P-800), automatic direction finder ARK-5 "Cupid", equipment for blind landing CAP-48 radio altimeter small Heights RV-2 "Crystal", marker receiver MRP-48 "Chrysanthemum", electrified tape cartridges signal escrow-46 and periscope review rear hemisphere. On some machines installed navigation indicator NO-50B, designed to determine the wind direction and speed. Subsequently added indicator radar irradiation "Sirena-2", originally referred to as "tail circuit protection", the defendant CPO-1 "Barium" (then the "Chrome") and receiver air pressure PD-FOR.

Electrical equipment powered by the generator on the engine or the battery 12SAM-25. The aircraft had a set of navigation lights and a landing light.

At higher altitudes the oxygen device used KP-14 and four oxygen tanks with a total capacity of 8 liters. Since mid-1953 fighters manned antigravity suit PPK-1 and the system of their compressed air supply. Body armor consists of a front lamp bulletproof glass thickness of 64 mm armor plates in front of the cockpit (on a frame No. 4).

Armament consists of one 37-mm gun H-37D (OKB-16MV) and two 23-mm cannon NR-23, located on the same carriage weldment. For ease of maintenance carriage to descend on ropes by rotating the handle. Ammunition gun N-37D-40 cartridges and HP-23 - 80 rounds on the barrel. The pilot had sight ASP-ZN later TSA-3 nm. Some aircraft were equipped with DME SRD-1M. To monitor the results of shooting and training purposes on the MiG-17 was mounted C-13. The suspension of two bombs caliber 50, 100 or 250 kg 4-50 D-holders is possible under the wing. Bombing might be conducted from horizontal flight, dive or pitching.




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Page last modified: 30-01-2016 19:10:02 ZULU