The MiG-23 aircraft is a Soviet-made multipurpose fighter equipped with a wing with a variable sweep configuration. It belongs to the third generation, according to NATO classification - “Flogger”. The first flight took place in June 1967 (test pilot A.V. Fedotov was at the helm). This aircraft in various modifications was in service with many countries of Eastern Europe, China, Korea, African countries and CIS countries.
History of creation
The development of the MiG-23 aircraft began in the 60s of the last century. The engineers of the design bureau concluded that the model under the index 21 is not suitable for installing powerful radar equipment due to insufficient free space in the bow of the air intake.
It was planned to move this compartment to the side or to the lower part. At the same time, the new fuselage department was to be equipped with the Sapphire sighting system. The MiG-21 PF machine acted as the basis, on which the nose compartment was converted, a new power unit of the R-21F-300 type was installed with a lower air intake under the fuselage and frontal horizontal tail. A prototype under the factory index E-8/1 was raised into the air by tester G. Mosolov. It happened on March 2, 1962, and already in June, the second car began to pass tests.
Some complications during testing of the MiG-23 were caused by the adjustment system in the passage section of the main air intake. Automatic adjustment on the devices was disabled, the tests were carried out in manual mode, which often caused the motor stopper and its surge directly in the air. Subsequently, the inspection of the aircraft was carried out with the automation turned on, which made it possible to somewhat stabilize the control of the air intake device.
Interesting Facts
In September 1962, another test of the MiG-23 aircraft was conducted, the photo of which is shown below. This time there was a deformation of the disk of one of the stages of the compressor of the power plant. The plane was damaged by debris, which led to the failure of two hydraulic systems and loss of control. George Mosolov (test pilot) managed to eject, but received serious injuries. After this incident, testing the model of the E-8 series was suspended.
The next project from the MiG-23 series is the version under the code E-8M. She entered the test site in December 1963. Initially, the model was supposed to be able to shorten takeoff and landing. The engines were two turbine engines of the R-27F-300 type. They were equipped with an upper air intake. In addition, there are nozzles designed to divert the gas stream back or forward a few degrees (from 5 to 10) during take-off and braking.
Fuselage
This element of the MiG-23 aircraft is a half monocoque, which has an oval section, turning into a rounded rectangular configuration. The technological design of this element includes a large number of panels that are interconnected by electric welding and rivets.
The following mechanisms are provided in the bow:
- Radar compartment.
- Radome transparent.
- Electronic equipment.
- Cockpit.
- Chassis front mount socket.
- The space behind the cabin is divided by a partition.
Rectangular air intakes are mounted in the area of 4-18 frames. Their inlet parts do not touch the 55 mm side skin, forming a drain slot for the border structure of the bow.
The MiG-23 single sealed cabin, the photo of which is presented below, is equipped with one armchair with the possibility of bailout. The lantern consists of a visor and a hinged element, which opens up and back under the influence of a pneumatic cylinder. In addition, this part can be lifted 100 mm during parking. The visor is made of special armored glass; the periscope is mounted on the cover of the hinged part of the light element. An overview of the wing planes is guaranteed by a pair of mirrors. Under the cab floor there is a frontal niche for the chassis.
Wing features
The wing includes in its design a center section with a single power tank and a pair of rotary consoles in the form of trapezoids. The main element of the fixed part of the wing (central compartment) is welded to the upper frames. It houses the rotary nodes of the consoles and fuel tanks.
The wing turning element is a caisson welded structure that transforms into a reinforced fork. This node with a pair of spars has a console, divided into the bow, center and tail. The two-channel hydraulic engine of the type SPK-1 is responsible for the turns.
The nose block of the rotary part is four-section, it can deviate by 20 degrees. Between each other sections are connected using controlled rods. MiG-23 fighter wing spars are made by hot stamping of aluminum. Sealing of the assembly is ensured by sealant supplied through bolt holes, as well as by a rubber band laid along the entire perimeter of the compartment. The flap is divided into three sections, one of which is made of titanium alloy, and the rest is made of aluminum. All parts are interconnected by collets, controlled by a separate hydraulic motor. The maximum flap deflection angle is 50 degrees.
Plumage
The plumage of the horizontal type has an oblique axis, includes two parts of the stabilizer. Each half consists of a frontal stringer, ribs, skin and spar. There are panels in the center, and rivets on the nose and tail. Each element of the MiG-23 stabilizer rotates on a pair of bearings.
The design of the vertical tail includes a steering wheel and keel. The frame of the last element has a frontal stringer, two spars, a set of leaf ribs, as well as milled and side counterparts. The middle part of the keel is completely made of panels, a radio-transparent block with antennas is provided on top. The steering wheel is fixed on three legs.
Control system
The control of the MiG-23 aircraft (RF Air Force) in the cockpit is carried out by the handle, moved in the longitudinal-transverse direction, as well as the directional control pedals. The main elements are spoilers, a steering wheel and a dual-mode stabilizer of a rotary type. Irreversible boosters with two cameras act as power drives.
Angular movements of the knobs and pedals to the boosters are carried out by direct mechanical transmission. Electric devices of the “sliding traction” type RAU-107A are used as executive equipment for autopilot. Additional force on the handle is created using spring loaders, the load is removed by means of devices with a trim effect.
Armament MiG-23
The fighters in question could be used to destroy air targets, to carry out bombing and assault attacks on ground targets. This versatility is provided by the engineering equipment of the aircraft, which consists in replacing the external suspension holders. The maximum mass of airborne weapons reaches two tons.
The main means of eliminating aircraft are 4 guided missiles of the R-24 and R-60 type. To destroy ground targets, Kh-23M guided missiles, cluster and standard bombs (from 100 to 500 kg.) Were used. Modifications with a multi-castle holder were able to transport suspended ammunition in caliber 100 (in total - 16 pieces). It also provided for the possibility of suspension of unguided missiles such as UB and B-8M.
It was also possible to attach up to three PTB-800 hanging tanks and holders of traps for IR configuration with 16 charges to a combat aircraft. The GSh-23 L double-barreled gun (ammunition - 200 shells) was located in the lower fuselage compartment.
MiG-23 combat use
Among the actual military operations of the fighter in question, the following can be noted:
- The work of aircraft in Syria (1973). Two Israeli fighters were shot down over Mount Herman.
- Clashes in response to the provocations of the Chinese Air Force on the border (1960, 1975).
- In 1978, the Chinook Iranian helicopters were shot down after crossing the Soviet border over Turkmenistan.
- The aircraft in question were actively used to destroy reconnaissance and propaganda balloons.
- Participation in the Egyptian-Libyan and Chadian-Libyan conflict (1973, 1976, 1983, 1986).
- Wars in Lebanon, Afghanistan, Iran-Iraq confrontation.
- Operation in Nagorno-Karabakh, the Persian Gulf, Angola, Libya.
main parameters
The following is a list of the main characteristics of the MiG-23 as standard:
- Length - 16.7 m.
- Crew members - 1 pilot.
- Height - 5.0 m.
- The wing area is 34.16 square meters. m
- Chassis (base / gauge) - 5770/2660 mm.
- The weight of an empty fighter is 10.55 tons.
- Maximum take-off weight is 20.1 tons.
- The fuel capacity is 4.3 tons.
- Speed threshold - 2500 km / h.
- Practical flight range - 900/1450 km.
- Acceleration length - 450 m.
- The coefficient of aerodynamics is 12.1.
To summarize
As experts say, at one time the MiG-23 was a modern and high-speed fighter that could change sweep, had good weapons, but had a tight cockpit and an unimportant view of the rear hemisphere. After the end of the Cold War, these modifications were practically not exported, although the MiG-21 is still in service with some states (mainly due to better maneuverability).