Mikojan i Guriewicz MiG-21 bis. 2010.

Kraków 2009-04-20


256b Section 1980-02-04.

OKB Mikojan and Guriewicz MiG-21 bis in Poland.

A supersonic fighter aircraft operating in "all weather conditions".

MiG-21 bis nb 9204. Czyżyny 2007. Photo by Karol Placha Hetman
MiG-21 bis nb 9204. Czyżyny 2007. Photo by Karol Placha Hetman

Construction MiG-21 bis.

MiG-21 bis is the seventh version introduced to the armament of Poland. The last combat version and the last time version.

Single-seat, single-engine, supersonic fighter aircraft.

The MiG-21 bis has a "delta" wing with beveled ends, 57 degrees, total area 23 m2, symmetrical wing profile CAGI S-12, with a relative thickness of 4.2% at the base and 5% at the end, wedging 0 degrees, rising -2 degrees, chord at the root 5.97 m, at the end 0.46 m. The wing structure is the main, auxiliary, front and rear girder. Cover thickness from 1.5 to 2.5 mm. There are two fuel tanks in each wing. 4 armament hooks under the wings. The wings are equipped with ailerons with a total area of 1.18 m2, swing out 20 degrees. The dampers are equipped with a blowing system, area 1.84 m2, are swingable by 25 degrees for takeoff and 45 degrees for landing.

Aircraft fuselage with frontal air grip, with central movable cone. The cone from the speed of the Ma-1.5 plane begins to move forward and at the speed of Ma-1.9 it occupies the extreme extended position. The cone is equipped with a wall suction system. The axis of the cone is inclined 3 degrees downwards. Behind the cone, the channel splits into two to bypass the pilot's cabin on the sides. The channel is equipped with anti-pump flaps and additional grips at the cabin height. These grips are equipped with covers protecting against foreign bodies being sucked in from the ground, under the front wheel. The airframe was equipped with three aerodynamic brakes. The first two are a pair and are placed in front of the main chassis. They have an area of ​​2 x 0.442 m2. They are tilted 35 degrees. The third aerodynamic brake was placed under the fuselage, behind the main chassis. It has an area of ​​0.47 m2, is perforated and tilted by 40 degrees. The SPRD-99 U2 start accelerators with adjustable thrust from 1 280 kG can be attached to the hull. up to 3 230 kG., and thus different operating times, from 9.8 seconds to 17.8 seconds. The mass of one rocket accelerator is 221 kg. An aerodynamic steering wheel was placed after the fuselage. The braking parachute with an area of ​​19 m2, can be released at a speed of 320 km / h and discarded after braking. Hermetic cabin and automatically air-conditioned. The pilot can wear either a suit with a sealed helmet or a suit with an oxygen mask. The KM-1 M armchair provides rescue at 130 to 1,200 km / h and from 0 meter height. The cab cover consists of a windbreak with 55 mm thick armored glass. The glass is de-iced by spraying with spirit. Wind deflector to the right, manually. It was equipped with a periscope with de-icing system and anti-glare.

Horizontal slab formation, area 3.94 m2, span 3.74 m, angle of attack 55 degrees, tilt down 7.5 degrees, up 16.5 degrees. Anti-flutter masses at the ends. Vertical fixture with a skew angle of 61 degrees 21 minutes, relative thickness 6%. Ballast surface 5.32 m2, rudder 0.965 m2, swing 25 degrees.

Chassis with all single wheels. All wheels with disc brakes. The front shin is retracted forward. Wheel size 500 x 180, pressure 7 atm. Shimmy muffler on the shin. Main wheel size 800 x 200, pressure up to 8 atm. Chassis spacing 2.787 m., Base 4.71 m.

MiG-21 bis engine.

The drive unit is an R-25-300 engine with 1 x 4 020 kG thrust without afterburning, with first afterburning 1 x 6 960 kG, with second afterburning 1 x 9 708 kG. Single-flow engine, two-shaft, 3 stages of one shaft compressor, 5 stages of the other, 1 turbine of one shaft and 1 turbine of the other shaft, double afterburner. Engine length 4.61 m, diameter 0.967 m, weight 1 210 kg. Fuel installation with a capacity of 2 885 liters.

Armament MiG-21 bis.

The MiG-21 bis aircraft is equipped with the RP-22 SM radar station and the semi-automatic guidance system for Lazur-M air targets. It ensures that the aircraft is led to the rear half-zone of the target, intercepting and attacking individual targets detected by a radar, in the altitude range from 1000 m to 17 500 m, at relative speeds up to 1,600 km / h, in "all weather conditions". This attack can be carried out with R-3 S, R-13 M, R-55, R-60 M missiles, or R-3 R missiles with radar guidance. The number of shells taken is up to 4 pieces. Only R-60 M can be carried in the amount of 6 pieces (two on the inner hooks). Various weapon combinations are possible.

The search radar scans the space horizontally 30 degrees, vertically 17 degrees up, 15 degrees down. Tracking leads in a 3 degree cone.

Slow flying and ground targets can be fought by eye contact with the ASP-PFD-21 sight.

Fighting ground or surface targets is possible from horizontal flight, at speeds of 700 km / h to 1,000 km / h, with S-5 missiles from 25-100 m. Bombardment is carried out from 300 m, with standard and incendiary bombs. An attack from a dive flight is performed up to a falling angle of 40 degrees, in the speed range of 600 - 1,000 km / h, with S-5, S-24 B missiles, or CCP with thermal heads for thermal radiation sources. Missiles S-5 come in a variety of variants to combat weakly armored, heavily armored and flying targets. They are always fired from 16- or 32-pipe containers. Missiles S.-24 aircraft can take 4 pieces. They are fired from rail launchers.

The GSz-23 Ł gun has a supply of 200 rounds. It is a 23mm two-barrel cannon.

The bombs used for the fighter have mass; 50, 100, 250 or 500 kg.

During combat duty, Polish MiG-21 bis were prepared for duty so that one had 2 x R-3 R suspended and the other 2 x R-60.

Data T-T MiG-21 bis:

Data T-T MiG-21 bis. 2009 year. Work by Karol Placha Hetman
Data T-T MiG-21 bis. 2009 year. Work by Karol Placha Hetman

Written by Karol Placha Hetman