Warszawa 2005-05-24
OKB Suchoj Su-24 / M. CCCP.
Section 1970-01-17
Construction Su-24.
Two-seat twin-engine supersonic nuclear strike aircraft with variable airfoil geometry. The design withstands an overload of +6.5g. Its most important parameter is flight at a speed of approx. 1,400 km/h at an altitude of 200 m.
A wing with variable geometry, with a triangular fixed center wing. The leaf with the profile SR14S-5.376 in the fixed part and from SR14S-9.226 to SR16M-10 at the end. The moving parts are attached to the center wing spar by means of ball joints. Along the entire span of the leading edge of the movable parts of the wings, there are 4-part, and from the 25th series 3-part, front flaps with an area of 3.04 m2, tilted at an angle of 27 degrees. On the trailing edge there are double-slotted, 3-section flaps, and in late production series – 2-section flaps. Only the outer sections work at maximum skew. The total area of the flaps is 10.21 m2 and they are tilted at an angle of 34 degrees. Differential deflected 2-section breakers located in front of the flaps, together with a differential deflected horizontal tail act as ailerons at low speed. Choppers deflected simultaneously are used for coasting braking. The fixed part of the leaf has a slope of 69 degrees, the angle of the moving parts is adjustable in the range of 16 to 69 degrees, but it can be set in four positions: 16 degrees, 35 degrees, 45 degrees and 69 degrees (along the front edge). The wings are moved by the SPK-2-3 system (return system). The angle of the wings is zero, and the angle of lift is -4.5 degrees. The elongation of the wings ranges from 2.107 to 5.64.
The fuselage of the aircraft is semi-monocoque with a rectangular cross-section, of the load-bearing type, with side air intakes for the engines. The fuselage consists of eight parts: the nose compartment with a radio-transparent cover; crew cabins with the compartment of the front landing gear and the compartment behind the cabin; mid-lobe with wing movement mechanisms; fuel compartment with tanks number 1, 2, 3 and 3a; main landing gear compartments; tail part; engine air intakes and fairings on the fuselage. In the process of operation, the fuselage of the Su-24 aircraft cannot be dismantled. The engines are inserted from the bottom through the hatches, closed with power covers. At the rear of the fuselage, in the root of the vertical tail, there is a container with two PTK-6 braking parachutes (from the 16th series – PTK-6 M) with a total area of 46 m2. Underneath the fuselage, in its central part, there are air brakes, which are also the front covers of the main landing gear. Their area is 1.68 m2, they tilt at an angle of 62 degrees. To ensure adequate directional stability, two aerodynamic steering wheels were installed under the rear fuselage.
The pilot and the navigator-operator, sitting in the cockpit next to each other. Pilot on the left. The controls are placed both in front of the pilot and in front of the operator, but the operator’s control stick is smaller so as not to obscure the radar screen. K-36 D or K-36 DM ejection seats, from the 10th production series. The canopy has two flaps that open upwards, one above each seat. The cabin is hermetic, of the ventilation type.
The flat horizontal tail can be deflected in unison or differential. The span of the horizontal tail is 8.39 m, the area is 13.707 m2, the bevel is 55 degrees (along 1/4 of the chord), it is tilted at the angles of +17 -25 degrees. The vertical tail also has a slant of 55 degrees, its area is 9.473 m2 (the first Su-24 – 9.23 m2), including the rudder is 1.44 m2; rudder deflection +-24 degrees.
Three-support landing gear, retracted in flight, with doubled wheels on each leg. The front wheels KN-21 with dimensions of 660 (600) x 200 mm and 9.1 bar are covered with a mudguard at the rear. The front landing gear is steerable, folded back to the fuselage. The main low-pressure landing gear with KT-172 wheels with dimensions of 950 x 300 mm and 12.15 bar is folded into the aircraft. Oil-air shock absorbers, adapted to operate from ground airfields. Retracting and extending the landing gear using a hydraulic system, in an emergency – pneumatically. KT-69.430 disc brakes on main assemblies with IA-58 anti-slip installation. The wheels of the front assembly are equipped with mudguards. The base of the chassis is 8.510 m, and the track of the main wheels is 3.317 m.
Su-24 M design.
On the first series of the Su-24 M, Su-24 MR and Su-24 MP aircraft, aerodynamic combs were installed on the wings, above the armament booms, which were later removed.
In the Su-24 M aircraft, the fuselage was extended by 750 mm by inserting an additional compartment in front of the cockpit. There is new electronic equipment, as well as an installation for refueling in the air.
Su-24 power unit.
It is powered by two single-flow turbojet engines AL-21 F-3, AL-21 F-3 A or AL-21 F-3 AT ( izdelije 89 ) built by Archip Lulka’s team. AL-21 F-3 – maximum thrust 2 x 75.0 kN (2 x 7,650 kG), and with afterburning 2 x 108.4 kN (2 x 11,050 kG). It has a 14-stage axial compressor and a three-stage turbine. The engine has a dry weight of 1,720 kg, a length of 5,340 mm, an intake diameter of 885 mm and a maximum diameter of 1,030 mm. Compression ratio is 14.5:1, air flow 104 kg/s. Specific fuel consumption is 0.86 kg/kG/h in the maximum range and 1.86 kg/kG/h with afterburning. AL-21 F-3 A with 2 x 75.00 kN thrust and 2 x 109.80 kN afterburning.
Fuel is located in three tanks inside the hull, marked with numbers 1, 2, 3 and 3a. The total capacity of the internal tanks is 11,800 liters (until the eighth series, tank No. 1 was 600 liters smaller). The tanks have a neutral gas installation.
In addition, the aircraft can carry three suspended fuel tanks: two PTB-3000 with a capacity of 3000 l each on outriggers under the fixed wing section and one PTB-2000 with a capacity of 2000 l under the fuselage. In total, the plane takes 19,800 liters. Standard T-1 or TS-1 fuel.
The Su-24 M version and its modifications are adapted to refuel in the air. A retractable fuel receiver was installed on the fuselage frame No. 4. The Su-24 M can also be a tanker aircraft itself, after installing the UPAZ-A Sakhalin unit under the fuselage (unified podwiesnoj set-up unit). It contains a pump driven by an air turbine and a drum with a 28 m coiled cable used to transfer fuel from its own fuel system to another aircraft. The capacity of the fuel flow system is up to 1,200 l/min.
Su-24/M installations.
Mechanical control system with two-chamber non-returning hydraulic amplifiers. There are three independent hydraulic systems on the plane. Each powered by two pumps, one on each motor. All installations use AMG-10 oil at a pressure of 210 kgf/cm2. The hydraulics on the Su-24 aircraft moves all the rudders, air brakes, moves the wings, retracts and extends the landing gear, controls the nose wheel, etc. The pneumatic system consists of two independent systems, main and emergency. It provides wheel braking and emergency landing gear extension. The electrical system is used to power the on-board equipment. The main sources of energy are two alternating current generators and two direct current generators. Two batteries serve as a reserve.
Su-24 equipment.
The aircraft has an automatic control system SAU-6 (in the Su-24 M aircraft – SAU-6 M 1 ), which enables flight without the pilot’s participation along a given course, also at low altitude, avoiding terrain obstacles, using the Reljef radar station. The Su-24’s weapons control and navigation devices are connected to the PNS-24 Puma-A system. It is used to detect and attack ground targets in any weather conditions and at any time of the day. To a limited extent (with heat-finding visibility) it can attack aerial targets. In addition, the Puma system is used for automatic navigation along a programmed route, including at low altitude, avoiding terrain obstacles. Everything is controlled by the Orbita digital on-board computer. Puma includes the following subsystems: SR Orion-A with a range of 150 km, SR obstacle collision warning Reljef. Antenna under a common cover with the Orion radar in the front of the fuselage. Filin-N passive radar pelengator. Antennas on the tip of the nose cone and under the front of the fuselage. Czajka optical viewfinder, under the front of the fuselage, along with Filin antennas. Heat meter TP-23 Je. Delta radio equipment for controlling the Ch-23 and Ch-23 M missiles. Moreover, the Puma includes small RW-3 MP and high-altitude RW-18 A radio altimeters. 1. DISS-7 Doppler speed and drift angle meter. Radio compass ARK-10, then ARK-15 M. RSBN-6 S ( ffom£>-1 K ) close navigation system, and later RSDN-10 ( Skip-2 ) long-distance navigation system, after some time also fitted to previously produced aircraft . The aircraft has an MRP-56 P radio beacon receiver. The SO-63 B active response station. The Su-24 navigation system allows it to automatically fly along a programmed route, bring it to its own airport or another previously programmed one, as well as perform an approach to landing in difficult conditions up to a height of 50 m. Two radio stations are used to maintain communication: R-832 M and R-847. SPU-9 intercom. The first aircraft had the SPO-10 Sirena warning station. In later series, as well as in the Su-24 M and its modifications, the more modern SPO-15 S (Ł-006) Bierioza apparatus and the Parol friend-foreign device are used. The aircraft has permanently installed active jamming stations SPS-141 / SPS-143 Siren. The reconnaissance equipment of the Su-24 aircraft is the AFA-39 camera built into the bottom of the fuselage. SARPP flight parameters control system, and later Tester.
Su-24 M equipment.
PNS-24M Tigr-NS navigation and targeting system. Compared to the Puma, the TP-23 heat-finder and the Czajka viewfinder were removed from the system, and the remaining elements were modernized. Instead of the passive Filin radar, cooperating with the Ch-28 rocket, the Fantasmagoria stations (Ł-080 or Ł-081), cooperating with the Ch-58 rocket, can be installed in the suspended pod. The modernized on-board computer is called CWM-10-058 K Orbita (CWM, centralnaja wyczys/itielnaja macha). The Kajra-24 laser and television station enables the aiming and guidance of laser-guided missiles and bombs. To control the Ch-59 and Ch-59 M TV rockets, a special container with the APK-9 apparatus must be hung under the plane. The aircraft’s equipment was modernized, e.g. R-862 and R-864G radio stations, SO-69 active response station, ARK-15M radio compass, new Klistron short-range navigation system, two radio altimeters were replaced with one RW-21. In order to simplify the refueling procedure in the air, the Vstriecz navigation system was set up to find and approach the tanker from a distance of 300 km in all weather conditions and at night. WRe system. In the Su-24 M aircraft and its modifications, all individual defense devices were combined into the BKO-2 Karpaty system. It consists of the SPO-15 S (Ł-006 S) Bierioza warning station, the Mak-UL heat detector (Ł-082, it is in a small dome on the top of the fuselage, just behind the cockpit), the SPS- 161/SPS-162 Gerań (Ł-101/Ł-102) and the APP-50 A heat trap and radar launcher (four 50 mm three-round launchers are built into the fuselage on both sides of the vertical stabilizer). All these devices are combined into one system, controlled by the Neon digital machine.
Su-24 armament.
Six-barrel 23 mm GSz-6-23 Gatling cannon or the modernized GSz-6-23 M (AO-19) gun with a supply of 500 rounds, 23 mm caliber placed in a fairing under the right side of the fuselage. On the left side there is an identical fairing with the AKS-5 photo rifle. These fairings are unnaturally long, because the wheels of the main landing gear are hidden in their rear parts. 7,000 kg. Number of armament suspension nodes 6, and later 8. Four of them are located under the fuselage (two on the sides and two in the middle part of the fuselage, one behind the other), two on the fixed part of the wing and two on the movable parts of the wings. The latter change their attitude as the angle of the wing sweep changes, so that they always remain parallel to the plane’s axis. This solution was used for the first time in CCCP. C.P.R. class p-z: Ch-23 / M up to 4 pieces, Ch-24, Ch-28 up to 2 pieces. To defend against aerial attackers, the aircraft can be armed with 2 infrared-guided air defense systems. R-55. Unguided armament includes bombs up to 1,500 kg, RBK-250 and RBK-500 bomb cassettes, incendiary mixture tanks, unguided rockets of caliber from 57 mm to 420 mm. SPPU-6 and UPK-23-250 shooting pods can be suspended under the wings and fuselage. The defensive armament is two k.p.r. R-55 infrared.
Su-24 M armament.
GSz-6-23 / M cannon. Weapon weight up to 8,000 kg. C.P.R. p-z class: Ch-25MP, Ch-27 and Ch-58U anti-radiation, and recently also Ch-31P. A novelty are laser-guided missiles and bombs (Ch-25MŁ / ML, Ch-29Ł / L, S-25Ł, KAB-500Ł, KAB-1500Ł) and television guided missiles (Ch-29T, Ch-59, Ch-59M, KAB-500Kr , KAB-1500TK). Little is known about the nuclear armament of the Su-24, although in the initial period performing nuclear strikes was its primary task. To this day, in the characteristics of the aircraft published by the Sukhoi design bureau, the normal take-off weight is given as the mass with a load of 1,000 kg, i.e. a nuclear bomb. For self-defense, the plane takes 2 R-60 missiles. The armament was unguided, e.g. increased by new KMGU bomb clusters.
T-T Su-24 data (1970):
Span 10.366 – 17.638 m. Length 22.67 m. Height 5.92 m. Bearing area 51.024 – 55.168 m2. Curb weight 21,177 kg. Total weight 32,300 kg. Maximum weight 39,700 kg. Weapon weight 7,000 kg. Fuel 11,800 (11,200) liters + 8,000 liters. Top speed 2,200 km/h. Top speed Ma-2.16. Range 2,550 km.
T-T Su-24 M data (1977):
Span 10.366 – 17.638 m. Length 24.532 m. Height 6.19 m. Bearing area 51.024 – 55.168 m2. Curb weight 22,250 kg. Gross weight 35,910 kg. Maximum weight 39,700 kg. Weapon weight 8,000 kg. Fuel 9,400 + 6,590 kg. Top speed 1,450 km/h. Maximum speed Ma-1.35. Range 2,550 km. Ceiling 16,500 m.
T-T Su-24 MK data (1987):
Span 10.366 – 17.638 m. Length 24.594 m. Height 6.19 m. Bearing area 51.024 – 55.168 m2. Curb weight 19,000 kg. Total weight 35,000 kg. Maximum weight 39,700 kg. Weapon weight 8,000 kg. Fuel 11,700 + 10,000 kg. Top speed 1,450 km/h. Maximum speed Ma-1.35. Range 2,550 km. Ceiling 17,500 m.
Written by Karol Placha Hetman