Su-24 Soviet and Russian tactical bomber with variable sweep wing, for applying air strikes in simple and difficult meteorological conditions, day and night, including low-level lesion with impact ground and surface targets.
Su-24M in Syria – video
Initially, after adopting the Su-7B was supposed creation of all-weather aircraft modifications for the destruction of small targets, but the development of the Su-7 with the performance requirements of TTT was impossible, therefore, the Sukhoi Design Bureau began development of the aircraft under the designation S-6 - with a delta wing, R21F-300 engine and a tandem arrangement of the crew. AT 1963 year, full-scale specimen was built, a year later the project was changed to cipher the T-58m - the modification of the Su-15, changed the concept of aircraft, Now at the request of the TTT supposed creation of a low-altitude bomber with short take-off / landing (required low-altitude supersonic flight with a overcoming air defense). FROM 1965 , the crew layout has changed, instead of tandem pilots are adjacent because of the large volumes of radar "Orion", engines - P-27F-300, to provide a short take-off / landing additional four RD36-35 installed. 24 August 1965 , the aircraft received the code T-6. 2 July 1967 year test pilot in. FROM. Ilyushin attack aircraft made its first flight. In October 1967 year were installed more powerful AL-21F, it is possible to get rid of four RD36-35.
Elaboration embodiment T-6 with variable sweep wing started in 1967 , under the leadership About. FROM. Samoilovych. At all stages of the work directly involved in the design took P. ABOUT. Dry. For the first time in the USSR provided pylons for suspension installation of an external load on the moving parts of the wing. The first prototype of the T-6-2I with a new wing 17 January 1970 the year flew the test pilot B. C. Ильюшин. T-6 has received the official designation Su-24.
It is considered, that the Soviet Su-24 was designed in the late 1960's - early 1970's with a large eye on the American F-111, While talking about the full copy can not be. According to About. FROM. Samoilovych, given in his memoirs, "Near Dry", when creating the Su-24 have helped numerous Exploded view photos F-111, made by him personally at the air show in Le Bourget 1967 year.
17 January 1970 , the Su-24 made its first flight. The state tests were conducted from January 1970 to July 1974 of the year. Su-24 adopted by the 4 February 1975 of the year. During the test flight occurred "titanium" aircraft fires, since the engine was made of a titanium alloy and in fire occurred in the compressor blades rapid destruction of the aircraft in the air. When it was established the cause of titanium fires, CB "Saturn" redesigned compressor. The weight and dimensions of the engine slightly increased, but its reliability and thrust also increased significantly.
On the basis of the aircraft have been established scout modifications and jammer. Su-24M / MP / MP / M2 equipped with flight refueling system.
Su-24 tests were carried out in more than 2000 flights. GSI Su-24M conducted from December 1976 in May 1981 of the year. Resolution of the Government of 22 June 1983 , the aircraft Su-24M was adopted. Produced on the NAPO and KnAAPO. Serial production of all modifications discontinued 1993 year. Only about it has been released 1200 these machines. Upgraded Su-24M2 made the first flight in 2001 year. Preliminary testing phase started in 2004 year. AT 2006 , the modernized aircraft is in the final testing stage. AT 2007 , the first two Su-24M2 were transferred to the Lipetsk Center of combat use. Delivery of all ordered Su-24M2 first batch was completed in December for the Russian Air Force 2009 of the year.
Design
The plane is a twin-vysokoplan variable sweep wing. Depending on the mode of flight of the wing front part (console) installed in one of four positions: 16° - on takeoff and landing, 35° - in subsonic cruising flight, 45° - during combat maneuvers and 69 ° - when flying at transonic and supersonic speeds. By airplane landing gear trohstoechnoe. The fuselage is of semi-monocoque construction, double cab. Pilot and navigator are located near, "shoulder to shoulder", dual control. Ejection seats K-36DM.
Fuselage
Fuselage Semi-monocoque. Power set consists of frames, spars and stringers. It consists of front part to 16 špangouta: of the radome antennas sighting and navigation systems and the equipment compartments, cockpit, podkabinnogo compartment with a niche nose landing gear, zakabinnogo compartment wheel housing, nose landing gear flaps niche, canopy, comprising a fixed front portion and two reclining back-up flaps. Under the nose radome radar antennas placed "Orion" forward-looking station and radar collision warning with natural terrain obstacles (RPS) "Relief". In the fore part of the fairing installed antenna front hemisphere antenna-feeder system "Peony" set of radio range navigation system (RSBN), pitot-static system of the PST 18 and the passive antenna of the radar system (LFS) "Owl". To access the radome swings on its hinges to the left side. Antennas are mounted on the rotary frame, which leans to the right hinged, providing access to the radio and radio-electronic equipment, set deep in the front compartment.
For the forward compartment equipment, limited 4th frame attachment, posted double sealed cabin crew with pilot and navigator landing near. Beneath it are three podkabinnyh compartment: the two side, in which the unit is installed and the airplane avionics equipment, middle compartment and the front landing gear niche. Closes the head of the fuselage behind the cockpit compartment, Situated where the bulk part of the special equipment and systems aggregates Jets. For access to the right and left are easily removable hatches, and on operational aircraft axis formed well with a hatch on the underside of the fuselage. In gargrot on the upper surface of the fuselage laid rigid wiring aircraft control system, fuel lines and other communication systems Jets. Forkil mounted thereon with cooling air inlet generators (from aircraft № 15-28). On the bottom surface of the middle part of the fuselage are four point suspension arms: № 3, № 4, № 7 and number 8, The last two - the tandem axial plane of symmetry (7-I 8th attachment points were installed on aircraft with №№ 8-11).
The middle part of the fuselage, frames with 16 by 35, It consists of three fuel tanks, compartments, avionics bay and units Jets systems, channels air motors, gargrota, front engine compartment, niches with the main landing gear and flaps niches harvesting of root portions of the wing the pivot arms with sealing flaps. compartment consists of a power frame 19 frames and 6 longerons. Front-compartment tank (tank number 1) It located on the axis of symmetry of the aircraft and has a rear portion through a rectangular recess to accommodate ammunition box built gun mount. Fuel tank compartment № 2 -expenditure, in the front part it consists of a central and two lateral parts, connecting into one of the load-bearing frames, which carries the main landing gear. Above these tanks are placed equipment compartments, in particular air-conditioning systems, air intake-air cooler is put to a top panel gargrota. Fuel tank compartment № 3 consists of two parts: front, bounded above cylindrical sloping plateau, and the bottom and sides - milled panels, and back, situated between the engines and the panels formed by milled.
Above the cylindrical tub inclined plateau № 3 Jets are two equipment bays: one has hydraulic motors drive the pivot arms and the wing control system mechanization, Second on removable panels are installed hydraulic units. Between the tanks № 2 and number 3 power beam center-located. Nishi main landing gear are separated by a symmetry of the fuselage in the vertical plane of the wall and the central portion of the fuel tank № 2. Both niche closed in flight three doors (side, central and rear), as well as the brake flaps. Nishi rotary wing panels intended for cleaning their root portions with increasing sweep angle over 16 ° and are arranged on both sides in the upper part of the fuselage. When swept wing 16 ° inside the niche closed spring-loaded flaps, with increasing sweep the root of the console, pressing the sash, go inside niches. The front part of the motor compartment has hatches, used when removing and replacing the engines. They are installed on the outer corners of the front part of the ventral fins.
Center section serves to mount the rotary wing panels, mounted at the top of the middle part of the fuselage and includes a power beams with struts and two compartments, It is a fixed wing segment. The upper and lower belt power beams made of steel VNS-5 integrally with hinge eyelets and bolted to the walls, support struts and a hinge assembly. The walls of the beams within the fuselage made of alloy AK4-1, and it is - 30HGSNA of steel and form together with the closed box section chords. The struts are designed as I-beams of steel 30HGSNA, with cutouts for the passage of screw jacks pivot arms and placing socks in brackets state the minimum sweep. The bottom surface of the center-mounted pylons for suspension holder compartments arms (1 -I 2nd the suspension point). Tailpieces center section composed of upper and lower panels, linked to the hinge beam. The ending of the top panel is formed as a winglet, compressed to the pivot arm spring mechanism. Center wing sweep angle of the leading edge is 69 °, it has a zero or negative angle of the transverse V -4 ° 30′.
Aft fuselage (for špangoutom № 35) It consists of the rear engine compartment, gargrota and tail spinners. The compartments mounted engines AL-21F-3, and steering assemblies stabilizer control consoles. To a tail portion attached rotary half stabilizer, fin and the rear part of the ventral fins. The power circuit includes the rear fuselage 11 frames. Power pitching frame consists of two side frames, two semiaxes stabilizer and lower. Gargrot gargrota compartment is a continuation of the middle part of the fuselage, and has the same plane with naznachenie.Nachinaya №№ 15-28 set narrowing of the tail portion fyuzedyazha. Engines are separated by the firewall. Inside the engine compartment of one of the frames is further transverse the firewall, behind each engine it is enclosed in a cylindrical housing.
Air intakes of engines
engine intake - side, flat, with vertical braking wedge. After a series of experiments on the production aircraft (since №№ 21-26) ceased to establish the movable panel and the other elements of control system of the air intake passage section of the channel, leaving only a leaf feeding, whose work is tied to the release / cleaning system flap. At the rear of the air inlets between their lower surface and the air ports are located equipment bays.
The wing and tail
The wing consists of a center wing and rotary wing portions. Power unit swing arm is a caisson with a power set of four side members and six ribs. Mechanization of the wing slats includes Quad, three-section double-slotted flaps (in the later series of aircraft – Two-section) and interceptory. mechanization control system provides first release slats at an angle of 27 °, and then release the flap at an angle of 34 °, and when cleaning, first retract the flaps, then – predkrыlki. The drive of both Implemented common two-channel hydraulic RP-60-3 driven by the dispensing mechanism.
Swivel allows wing allows to rearrange at any angle with 16 to 69 degrees, SEC-2-3-channel system is arranged, wing is driven dual-motor (RP-steering actuator 60-4), the rotation of which is transmitted to the rotary shaft through the nodes VP-4 Screw converters. The spoilers are used to improve the lateral control wings sweep efficiency at less than 53 °, their total deflection angle is 43 °. At the bottom of the wing consoles installed on one pivot suspension pylon, that at any angle of the sweep plane is always parallel to the axis of the construction.
All-moving stabilizer is used for the longitudinal and transverse plane management. The halves of the stabilizer on the power frame hinged rear fuselage and deviate combined two hydraulic aggregates are controlled by angles of + 11 ° to -25 °. The angle of sweep along the line 3/4 chord is 55 °. Vertical tail fin consists of two ventral fins, sweep through the keel 3/4 chord is 55 °. The rudder is hung on 4 attachment points, controlled hydraulic steering unit and by angles may deviate ± 24 °. Wheel weight balancing implemented through three cargo-balancers, set out in his socks.
The chassis and the brake parachute
The aircraft trohstoechnoe chassis mounted at the front and the two main struts. At the main racks installed along the two brake wheels CT-172 with the tire 950×300 mm and normal charging pressure pneumatics 12 kgf / cm2 (1,2 MPa). Bearing equipped with a pair of front wheels non brake related KH-21 with the tire 660×200 mm, and reversal mechanism, allows the airplane control while driving on the airfield. Also, the top-rear wheel bearing set front mudguard, prevents debris from entering the engine air intakes. Cleaning and the landing gear is made by means of the hydraulic system, in case of its failure chassis produced by the emergency pneumatic, when it first comes out the front support, and then – main. In the retracted position, the rack held mechanical locks with hydraulic control, released in – device stays (brace and lock ring). Braking wheels made from the basic pneumatic aircraft, emergency – from emergency pneumatic.
Niche front desk closes folding the front and two side flaps. Niche main pillars are equipped with three-leaf and leaf-brake flaps. track chassis 3,31 m, base - 8,51 m. Drogue parachute PTK-6 consists of a round container with two doors, two suction and two main cruciform parachutes, release locks and uncoupling. Initially, the container is in the upper part of the fuselage, since the plane №№ 15-28 It has been moved under the rudder. Brake parachutes nominally used for each aircraft landing.
Power point
The aircraft is equipped with two Turbojet AL-21F-3 (product "89") a thrust in afterburner (at ground level) 2× 11200 kgf, at maximum besforsazhny mode - 7800 kgf. The fuel is kerosene stamps TS, T-1 and mixtures thereof. The peculiarity of the aircraft are electric throttles, no mechanical connection to the engine.
Structurally, the engine consists of a:
– axial 14-stage compressor guide vanes turning blades;
– uniflow tubular-annular combustor;
– a three-stage axial turbine;
– trehstabilizatornoy ramjet afterburner;
– variable speed controlled exhaust nozzle with the divergent part;
– turbine starter with aggregates autonomous system startup;
– box units drive;
– regulation and fuel automation system;
– Engine power systems and fuel oil, electrical and anti-icing.
Fuel system
The fuel system consists of three internal fuselage tank-compartments (the second tank - Consumption) and has a capacity of 11 860 liters (airplanes to №№ 8-11 — 11200 liters). Fuel is pressurized 0,2 kgf / cm3 (20 kPa), provided by the drainage system and boost. Also on the plane possible suspension of three additional external fuel tanks - two wing FTB-3000 and FTB-2000 fuselage, thereby increasing fuel capacity by another 8000 liters. To provide the required range of center of gravity out of fuel is performed automatically in sequence. Under the action of near-zero and negative accelerations fuel for engines supplied from the storage tank, where it is squeezed air. To control the supply of fuel on an airplane set toplivomerno-FLOW machinery. Filling fuel tanks made centrally via a standard charge connection, in the absence of airfield tanker - dispensing gun through the tank filler neck № 1 neck and external fuel tanks. By plane provided emergency fuel return system, drain pipes removed for the tail of the fuselage kok.
Fire-fighting equipment
Fire fighting aircraft equipment consists of a control and fire extinguishing systems, and neutral gas system. The latter is intended to protect aircraft fuel tanks from the explosion at the lumbago and injuries, and to maintain an overpressure therein at all flight modes by their pressurization with nitrogen gas. Nitrogen under pressure 210 kgf / cm2 (21 MPa) in four cylinders 16 UBTS capacity of 16 liters. Aggregates neutral gas system located in the aft fuselage section between the engine compartment engines.
The hydraulic system of the aircraft
To improve the reliability and survivability of hydraulic system consists of three independent stand-alone hydro systems, each of which has its own power supply (NP96A hydraulic pumps 2, one for each motor), distribution units and pipelines. Working fluid is oil AMG-10, general stock which is on a plane 65 liters. Working pressure in the hydraulic system - 210 kgf / cm2. For smoothing and stabilizing the pressure pulsations in the hydraulic piston are provided pneumosecondary, rechargeable nitrogen.
The first hydraulic system provides operation control rotary actuators stabilizer, rudder and spoilers. The second hydraulic duplicates in the first part of the drive control surfaces, and also provides the rotation systems wing panels, extension and retraction of the flaps and slats, chassis, opening and closing the flap feeding right channel vrozduhozabornika, performs power steering units RM-130. A third hydraulic system is used to actuate the rotation of the wing system consoles, management mechanization, opening and closing the shutters of the air intake feeding the left channel, Release brake flaps, Turning the wheels on the front of the rack, switching nonlinear mechanism, Automatic braking of the wheels when cleaning the chassis, management fotoustanovkoy. Pneumatic aircraft consists of two autonomous systems, main and emergency, and operably linked to a hydraulic system. Air for both stand-alone systems is contained under pressure 180-200 kgf / cm2 (18-20 MPa) six spherical cylinders with a capacity of 6 liters (of three cylinders on each system). The main pneumatic braking wheels designed for, and producing pressure hydraulic fluid in the third tank of the hydraulic system. Emergency pneumatic system is used for emergency braking of the wheels and the main pillars of the emergency landing gear extension.
electrics
The main sources of electricity are the two plane alternator with a rated voltage GT30P48B 200/115 V at 400 Hz capacity of 30 KBA, two dc generator GSR CT-12 / 40a with a nominal voltage 28,5 In the capacity of 12 kW each, and two three-phase power transformer for voltage 36 The frequency 400 Hz. Redundant DC sources are two nickel-cadmium batteries 20NKBN-25. Emergency source of single-phase AC voltage 115 The rotating converters is current PO-750A, three-phase current 36 V / 400 Hz – PT-500TS. there are standard plugs airfield power SHRAP-500K and SHRAP-400 for connection to the power network of ground power sources.
Control system
The control system aircraft twin, performed by irreversible circuit with two-chamber hydraulic actuators, established directly by the governing bodies. Each half of the stabilizer is controlled by its electro-hydraulic drive - combined CAU-120 control unit. The pitch control system includes spring zagruzhateli, automatic control and loading mechanism trimmer effect. Successively connected to the automatic control system regulating, which changes the gear ratios of the control knob to the stabilizer according to the dynamic pressure and altitude.
The cross is controlled differentially deflectable stabilizer, wherein movement of the handle rigid rods is transmitted to the spool through the mixing of the combined hydraulic booster mechanism, allows you to control the stabilizer as a channel pitch, and channel bank.
The spoilers are connected with the wing sweep less than 53 °. Management Interceptor – distance, using the RM-120 electro-hydraulic actuators, deflecting each section spoilers and receiving electrical signals to move from the inductive sensor, mechanically linked to the control handle in the cab. Also in the roll control system provides mechanisms for loading and trimmer effect.
Rudder actuated booster BU-190A-2, bonding conductor to pedal hard wiring. The directional control system includes a steering damper unit, mechanisms for loading and trimmer effect.
Cabin Su-24M2
aircraft cabin - Hermetic, ventilation type, It provides normal work crew in high suits over the entire range of flight altitudes. Jobs crew members with an ejection seat K-36D (from the plane №№ 9-11 - K-36DM) placed next: the left seat pilot, right navigator. emergency escape system allows you to eject both individually, and force all over the operating range of altitudes and speeds, as well as on the ground during the run-up / run, at a rate of at least 75 km / h. On the dashboard, panels and consoles, mounted on the cabin side, placed instruments and apparatus for management and control of the airplane systems,, power plant, equipment, weapons, aircraft and engine controls. At the disposal of the crew has 46 indicators, 206 signal lamps and buttons, more 20 leverage, over 300 switches, AZS, buttons, switches and other controls. Inner cabins coloring: on the first series of the machine cab gray, black dashboard, further dashboards and consoles began to paint in cyan (Emerald). In-cab lighting performed filled with red light. Airplanes since №№ 14-11 cabin equipped with light shielding shutters from the light radiation a nuclear explosion (SZ), which are also used for training flights (called the flights "under the curtain").
the cockpit canopy consists of the stationary part and two flaps, recline – laterally independently. doors lamp control system provides operational opening and closing, as well as emergency relief flaps at ejection. To protect the glass front of the lamp-icing system installed defroster hot air. required temperature, air pressure and ventilation in the cabin are provided with air conditioning. cab sealing along the perimeters of folding parts lamp made using inflatable sealing air hose, Riveted by the seams and bolted connections - Damage to the inner surface of the hermetic cabin. pipelines, traction control and electroplaits withdrawn from the cabin through sealed terminals. Inner cabins papered surface coated heat-.
coloring aircraft
Almost all the combatant aircrafts in the USSR received a light gray color top and sides, the lower surface of the fuselage and planes painted white (so-called anti-nuclear, protects the surface of the flash of light). Delivered abroad at the request of the customer can have a different color camouflage. Nevertheless, feature of all SU-24 is a fuselage belly chronically dirty, especially in the engine area. In the area of the left side of the cabin is drawn emblem - manufacturer's logo. Also shelves, armed Su-24, wide practice got applied to all kinds of fuselage designs and logos, the so-called "bead painting".
Electronic equipment
automatic flight control system SAU-6.
airplane pitch control, roll rate and can be carried out by the crew, and with an automatic control system ACS-6. This automatic control system can be operated in modes ESP, damping, as well as ensure compliance with low-altitude flight with rounding terrain according to RPS area “Relief”. automatic control signals are routed directly to the input of electro-hydraulic actuators and aggregates, deflecting control surfaces. In the event of failure of the ACS in the low-altitude flight mode in the longitudinal and lateral control system, special steering units provided, ensure safe aircraft leaving the ground and bringing it to zero roll.
Sighting and navigation system PNS-24 “Puma”
The system is designed for the following tasks:
– day and night all-weather detection and the impact of defeat tactical ground targets all types of aircraft armament;
– Autonomous and automatic piloting solutions to programming problems given route;
– safe low-altitude flight with collision warning and terrestrial flyby of obstacles in the vertical plane;
– ensure the impact of air targets defeat malomanevrennyh (transport, connected airplanes etc.) detection of visually or by teplopelengator.
In the composition of PNS-24 “Puma” includes: Forward-looking radar (RPO) “Orion-A”, radar collision warning with terrestrial natural obstacles (RPS) “Relief”, passive radar finder (PRP) “Owl”, Electron-optical sight “Gull-1”, teplopelenhator TP-23E, X-23 missile guidance system “Arkan” with radio command line “Delta” and television direction finder “Taran”, Doppler speed measurer and angle Diss-7 demolition, small radio altimeters (RV-3MP) and large (RV-18A1 “Crown”) heights, malogabaritnaya inertsialynaya system IIA-P, SHS-Mo-air data computer 5-3, system of automatic control of the aircraft ACS-6, to attack and navigation sighting PPV indication system, on-board digital computer system based on digital computer “Orbit-10” (CVU-10-058), communication equipment and a number of other systems. system weighs 837 kg.
Radio communication equipment
– command VHF / UHF radio R-832M “Eucalyptus”
– Transceiver shortwave radio R-847 “prism” (or R-846; airplanes with N15-28 – P-864)
– Fixed-wing intercom SPU-9
– tape MS-61
radio navigation equipment
– onboard radio system of short-range navigation RSBN 6c “Diamond-1K”
– onboard radio system of long-range navigation RSBN-10
– automatic radio ARC-10 (on planes later series – ARC-15M)
– the aircraft transponder SB-63B,
– Antenna-fidernaâ system (AFS) “Pion-GT-6”, providing job RSBN 6c and SB-63B
– marker radio MRP-56P.
Onboard Defense Complex
– warning station on the irradiation of the ACT-10 “Sirena-3M”, subsequently SPO-15 “Birch”
– jammer “Lilac”
– teplopelenhator “Mac STR” (Su-24M)
– automatic setting APP-50 noise (“TO” and “LTC”)
And:
– IFF equipment SRZO-2M “Silicon-2M”, subsequently replaced by izd.62 “Password”
– objective control equipment “Tester-U3” (to N8-11 aircraft installed equipment SARPP)
weaponry
– arms-pushechnoe vooruzhenie
– unguided bombing ordnance
– unguided rocket
– guided air missiles “air-to-surface” and “air-radar”
– controlled missiles “air-to-air”.
The aircraft has 8 Trailing dots: four ventral, two under center, and two – a rotary wing panels. Maximum weight of the payload of the Su-24 aircraft is 7000 kg. To solve the problems of preparation and selection of weapons, launch control (reset) aircraft weapons and detonators for various versions of the aircraft load is installed on board the weapon control system (SUO).
Small-pushechnoe vooruzhenie
It consists of a built-in gun mount – sextuple gun GSH-6-23 or GSH-6-23M (AO-19, product 9A-9A-620 or 768) caliber 23 mm, having ammunition 500 shells. The gun is placed on the bottom surface of the fuselage at the junction with the right air intake. Rate gun mount – to 9 thousands of rounds per minute, It is the initial velocity of the projectile 715 m / s, return – 4500 kgf (44 kN), gun weight – 73 kg.
In addition to the CPG, the plane can be suspended three removable movable gun mount SPPU-6.
bomber weapons
FROMis edit of unguided bombs caliber 1500,500,250 and 100 kg, single cluster bomb (RBC 500 and RBC-250), incendiary tanks (BZ-500), placed on the external load on the beam holders 4th and 3rd groups. Plane can be hung 3 high-explosive bombs FAB-1500 in the beam holders BD4-U, 8 bomb FAB-500M-62 on baločnyh holder BDZ-U, 16 bomb FAB-250M-62 or 28 FAB-250M-54 (variant with maximum bomb load) on the Multi Lock holders MBDZ-Y6, 38 high-explosive bombs OFAB-100-120 on the holders MBDZ-Y6.
Ungovernability raketnoe vooruzhenie
It consists of missile caliber 57, 80, 240 and 266/340(420) mm fragmentation warheads, high-explosive, cumulative and action pronykayuscheho, as well as special purpose. Unguided rockets caliber 57 mm applied from blocks UB-32A-73, having 32 barrel launchers, and presented NAR type C-5M, C-5Mo, C-5K, C-5KO(KP) with high-explosive warheads, high-explosive, and cumulative-cumulative fragmentation type respectively, specialized flares (C-5-O) and anti (C-5P) destination. Unguided rockets caliber 80 applied 20 mm from the barrel-blocks and B-8M can be completed cumulatively-fragmentation (HAP C-8, C-8B, C-8A, C-8M) or high-explosive penetrating (C-8B) warheads, flechette (HAP C 8VS, C-8AS). Heavy rockets type C-24 (C-24B) caliber 240 have mm high-explosive fragmentation warhead and are used with aircraft launchers APU-68UM2. Unguided rockets S-25 caliber 266 mm have nadkalibernuyu warhead fragmentation (C-25-O) or high-explosive (S-25 OF) actions diameter 420 and 340 mm, respectively, and are run from disposable devices 0-25. Simultaneously, the plane can be suspended until 6 blocks UB-32 and B-8M, 4 missiles or C-24 6 devices 0-25 with HAP -25.
Controlled Missiles
It includes tactical guided missiles (SKILLS) class “air-to-surface” Kh-23 and anti-tank guided missiles X-28 and X-58. X SD-23 (product “68”) It has radio command guidance system with transmission by radio commands “Delta”, equipment which is installed on board the aircraft carrier and missiles. The Su-24 suspension possible to 4 X-23 rocket launchers devices on AAP-68UM2. Guided missiles “air-radar” X-28 (product “D-8”) It has a passive radar homing head. X SD-58 (product “D-7”) It has a similar purpose and guidance system. Plane can be hung two X-28 rocket (to launch IP-28 devices) or two X-58 (on aircraft ejection devices such as AKU-58-1).
For self-defense on a plane, you can hang two missiles “AIR-TO-AIR” R-55 (product “67”) with IR homing heads for actuating device for pivoting the movable parts of the wing pylons.
Su-24M
Installed sighting and navigation system PNS-24M “Tiger-NA” on the basis of laser-sighting television station “Re-24” (MiG-27K), onboard computer with the CWU-10-058K ; airborne defense, more advanced radio navigation and communication equipment, modified system of objective monitoring and recording flight data. Also slightly modified electrical and hydraulic. A pull-rod refueling in flight with the receiver ATG-2. The fuselage lengthened by increasing the nose equipment bay. Some changes in the airframe – reshaped keel, JHA change form, additional operating hatches, setting aerodynamic ridges on the wing, and so on. d.
radio navigation equipment
– radio system of short-range navigation A-321 “Klystron” (instead RSBN 6c “Diamond-1K”)
– radio system of long-range navigation (RSDN) A-720 “Skip-2”
– Automatic Direction Finder ARK-15M “Tobol” (I installed and the latest Su-24 series)
– Airplane defendant SB-69 (instead of CO-63B)
– AFS “Pion-GT-6M-9” with antenna units RSBN “Klystron” and CO-69.
Radio communication equipment
Includes a command UHF-VHF radio R-862 (instead of VHF radios R-832M) and the shortwave station F-864G (instead of P-847).
Onboard Defense Complex (BKO) “Carpathians”
– electronic intelligence station ACT-15C “Birch” (ed. L-006FROM) (It installs and runs on the latest Su-24)
– teplopelenhator “poppy”
– Jammer radar range “gardenia”
– chaff ejection system and false heat goals APP-50 with two holders of units 12 caliber 50 mm, placed on the upper surface of the fuselage on both sides of the vertical tail
– the evaluating and control device “Neon-F” (izd.L-167)
Through the installation of a flight of the new sighting system, it became possible to cleanly apply munitions with laser, television and television-command guidance – responsive bombs and missiles:
– 4 X-23 rocket (X-23M) or X-25MR with radio command guidance system
– 4 rocket X-25 or X-25ML with semi-active laser guidance system
– 3 Kh-29L with a semi-active laser guidance system
– 3 Kh-29T with a television homing
– 2-3 Kh-59 with television-command guidance system
– 6 S-25L missiles with semi-active laser guidance system
– 2 X-58 rocket passive radar homing
– guided aerial bombs KAB-500L type, TO-1500L, TO-1500TK
Technical problems and operational features of the Su-24
All planes of the Su-24 are structurally complex machines and require highly trained as the flight personnel, and ground staff, Besides, they do not tolerate sloppiness and connivance and do not forgive mistakes. High saturation electronics and automatic triggers high Exemption systems. In the initial period of operation about the causes of failures of serviceability of aircraft fleet was low, carried out numerous improvements industry representatives. However, faults and failures of many aircraft systems are not critical for the safe completion of the flight, that was originally provided by developers.
Escape system, according to instructions, It provides safe emergency escape plane in flight, as well as during takeoff or run at a speed of 70 kmh, nevertheless there was a case of abnormal operation of the navigator seat in the parking lot ( during engine starting, and the appearance of pressure in the hydraulic system is deviated “to myself” jerk control knob stood in the neutral position and, hooked for Derzhko catapult, caused tripping chair). Navigator, I did not understand, “came out” from the cockpit, All systems worked nominally chair and landing went well. After this incident on all aircraft with all-moving stabilizer of the aircraft parking area began to record the fuselage slung over tether, preventing its movement – when the aircraft parked and no pressure in the hydraulic stabilizer socks tend to spontaneously sinking down, of kabrirovanie, It was finalized ejection seat.
Modifications Su-24
Su-24 - basic modification of.
Su-24M - modernized bomber, It made its first flight in 1976 year. Installed a new sighting and navigation system PNS-24M "Tiger". Capable of automatic and semi-automatic mode to make a flight with rounding terrain at an altitude of 50 m. released 770 PC.
Su-24M2 - modernization of the second bomber (1999 year)
Su-24MP - jammer, It made its first flight in December 1979 of the year. released 10 Flight.
Su-24MR - reconnaissance plane, It made its first flight in September 1980 of the year. released 130 Flight.
Su-24MK - export version of the Su-24M, It made its first flight in 1987 year.
Combat application of Su-24
Afghan war (1979—1989) – The Afghan war (1979—1989) Soviet Su-24 restrictions apply. To combat the work they are involved only during the Panjshir operation 1984 year, and to cover the withdrawal of the Soviet troops in 1988-1989. The Su-24 has never been based in Afghanistan, acting with the Soviet air bases in Central Asia. Combat losses was not.
The Gulf War – Iraqi Su-24 during the Gulf War combat sorties did not commit and were flown to Iran, assign those planes after the end of the war.
Karabakh war – Aircraft, dostavshyesya Azerbaijan, restrictions apply during the Karabakh war.
The civil war in Tajikistan – Uzbek Su-24 took part in the civil war in Tajikistan, one car was hit.
The Chechen conflict – The most intense combat use of Russian aircraft had during the two Chechen wars. All were shot down or crashed three Su-24 in the North Caucasus, Three more burned at the airport in preparation for a combat flight.
The war in South Ossetia (2008) – Also, the Russian Su-24 were used during the war in South Ossetia 2008 year. Official Russian reports loss Su-24 is not mentioned, but some experts point to the loss of two aircraft of this type. AT 2012 , Lieutenant Colonel Vladimir Bogoduhov, received for combat missions in South Ossetia, the title of Hero of Russia, He said in an interview with the newspaper "Arguments and Facts", that in the course of the war anti-aircraft missile was shot down by one of the Su-24, aircraft crew ejected and landed in the location of Russian troops. Who died in a sortie in the Su-24, Colonel Igor Rzhavitinu was posthumously awarded the title Hero of Russia.
The civil war in Libya – One Libyan Su-24 was shot down by rebel fire during the civil war in Libya 2011 of the year.
War in Donbass – Ukrainian army used during the conflict in the east. According to Ukrainian data on 4 October 2014 Kills years ognem to land two Su-24M, and one Su-24 is lost as a result of equipment failure.
Syrian Civil War – Syrian Air Force used in the Civil War. 23 September 2014 , the Su-24 Patriot missile shot down, vtorhshyysya on 800 meters in Israeli airspace.
Russia's military operation in Syria – 12 Su-24M with 30 September 2015 year involved the Russian Air Force in Syria to fight against the "Islamic State" terrorist organizations. 24 November 2015 , the Su-24M was shot down a Turkish F-16 fighter near the Syrian-Turkish border. Both pilots ejected, but one of them was killed during the descent by parachute.
Accidents and Disasters
Su-24 is considered to be quite difficult to pilot the machine and has a high accident rate. Only during the flight tests have been lost 14 Su-24 and Su-24M. After the adoption of the aircraft into service each year going 5-6 accidents and disasters. According to Deputy Chief of the Russian Air Force, Victor Cota, on 1998 year aircraft Su-24 was the most alert aircraft of the Russian military aviation.
armed with
31 August 2016 Year in Russia ended the exploitation of the Su-24 bombers in the original version (no letters in the index). Bombers were retired.
It is in service
– Azerbaijan - 2 Su-24M as at 2017 year
– Algeria - 33 Su-24M / Su-24MK and 4 Su-24MR, as of 2017 year
– Iran - 29 Su-24MK as of 2017 year
– Russia - 100 Su-24M / M2 and 79 Su-24MR as of 2017 year
– Syria - 11 Su-24M / M2 as of 2017 year
– Sudan - 6 Su-24M as at 2017 year
– Ukraine - 14 SU-24M and 9 Su-24MR as of 2017 year
It was in service
– Belarus - 23 Su-24M and 12 Su-24MR, as of 2010 year. Retired in 2012 year.
– Iraq - part destroyed during the war 1991 of the year, the other flew to Iran.
– Uzbekistan - 23 Su-24 and 11 Su-24MR, as of 2015 In the year 2017 It was not listed in the ranks.
– Kazakhstan - 25 Su-24 / Su-24M as at 2015 In the year 2017 It was not listed in the ranks.
– Libya - 6 Su-24MK, as of 2010 year. Destroyed during the Civil War in Libya.
– Angola - 1 Su-24 as of 2011 In the year 2017 It was not listed in the ranks.
The performance characteristics of the Su-24M
Su-24 crew
– 2 man
The dimensions of the Su-24
– Length: 24,594 m (with LDPE)
– Wingspan at sweep angle χ = 16 °: 17,638 m
– Wingspan at sweep angle χ = 69 °: 10,366 m
– Height: 6,193 m
– Area under the wing sweep angle χ = 16 °: 55,16 m²
– Area under the wing sweep angle χ = 69 °: 51 m²
– Sweep angle of the leading edge: 16°/ 35°/ 45°/ 69°
– The cross-wing V: −4,5°
– The base chassis: 8,51 m
– track chassis: 3,31 m
All Su-24
– empty weight: 22300 kg
– Curb weight: 23700 kg
– Normal takeoff weight: 33500 kg
– Maximum takeoff weight: 39700 kg
– Normal landing weight: 24500 kg
– Maximum landing weight: 28000 kg
– Mass fuel in internal tanks: 9800 kg
– Volume of fuel tanks: 11860 l
Engine Su-24
– Power point: 2 × TRDDF AL-21F-C
– dry power: 2 × 7800 kgf (76,5 kN)
– afterburning power: 2 × 11200 kgf (110 kN)
Su-24 speed
– Maximum speed at height 200 m: 1320 kmh (without suspension)
– The maximum speed at high altitude: 1600 kmh (M = 1.35)
– unstick speed: 360-400 km / h
– landing speed: 285-310 km / h
Combat radius Su-24
– 560 km (on high 200 m PTB and normal combat load)
Ferry range Su-24
– 2850 km (with PTB)
Practical ceiling Su-24
– 17000 m
Length of start SU-24
– 1150-1250 m (during normal takeoff weight)
Length PROBE Su-24
– 950-1000 m (during normal takeoff weight and a drogue parachute)
Maximum overload of Su-24
+6,5G
– Wing loading: 607 kg / m (during normal takeoff weight at 16 ° χ =)
– thrust-to-weight ratio: 0,67 / 0,56 (at normal / maximum takeoff weight afterburner)
Weapon Su-24
– Small-pushechnoe: 1 x 23 mm six-barreled gun with GSH-6-23 500 sn.
– combat load: 7500 kg (maximum), 8 nodes suspension arms
Guided missiles, the Su-24
– missiles "air-to-air": 2 × R-60 (AA-8)
– "Air-to-ground" missiles: 4 × H-25ML / MR-23 or H; 3 29L × X / T or X-59; 6 × C 25L; 2 × X 58
Rockets Su-24
– 192 (6 × 32) × 57 mm-5 PB-32 blocks or
– 120 (6 × 20) × 80 mm C-8 in the blocks B-8M or
– 30 (6 × 5) × 122 mm C-13 B-blocks 13L or
– 4 × 240 mm C-24 or
– 6 × 266 mm C-25
Bomby Su-24
– 3 × 1500 kg (FAB-1500, TO-1500L / m and TC. d.) or
– 7 × 500 kg (TO-500l / KR, BZ-500) or
– 10 × 500 kg (FAB-500M-62, RBK-500) or
– 16 FAB-250M-62 “or” RBC-250 or 30 × 250 kg FAB-250M-54, or
– 38 × 100 kg (OFAB-100) or
– 7 Container 2 × KMGU
– gun pods: 3 × SPPU-6 23 mm GSh-6-23 with 400 shells
– Suspended container "Phantasmagoria" missiles for target designation X-58
Photo Su-24M
