Warszawa 2005-05-24
OKB Sukhoi Su-24 MR reconnaissance and Su-24 MP electronic warfare WRe.
Section 1980-05-06
WRe supersonic tactical reconnaissance and combat aircraft developed from the Su-24 M version. See Su-24.
Su-24 MR (T-6 MR-1) reconnaissance. 1980 year.
From the very beginning of work on the Su-24, it was envisaged to build its reconnaissance variant and such a task was set as early as August 1965, with the start of work on the T-58 M. Work on this version could start only after the final formation of the Su-24 aircraft . In October 1970, when the first prototypes were flying, the designers were again instructed to develop a reconnaissance version, designated T-58 MR.
Further work was related to the construction of the specialized BKR-1 apparatus (base razvedki complex). The work was relatively slow, and since the Su-24 M aircraft had already been built, the reconnaissance version was adapted to this variant and renamed the Su-24 MR (T-6 MR).
The first flight on the T-6 MR-1 prototype was made in May 1980 by Anatoly Ivanov. Probably on May 6, 1980. It was a converted T-6 M-26 aircraft No. 0115305. State trials of the T-6 MR ended in 1982, and serial production began in 1983 in Novosibirsk. At the production plant, the aircraft received the code izdelije 48.
The Su-24 MR has the largest set of reconnaissance devices among Soviet tactical reconnaissance aircraft and is designed for comprehensive reconnaissance. This means that the aircraft has reconnaissance equipment: radar, infrared, television, laser, radio engineering and radiation, as well as photographic, combined into one BKR-1 system. The aircraft has the ability to directly transmit the collected reconnaissance information to the ground by radio via the SzRK-1 apparatus.
From the outside, the reconnaissance Su-24 MR from the bomber Su-24 M is most easily distinguished by a different arrangement of antennas at the front of the fuselage. In the Su-24 M, the entire nose is occupied by one large radar cover, in the Su-24 MR, radio-transparent covers are located at the very tip of the nose and on the sides. In addition, the housing of the additional air intake for cooling on the top of the fuselage is convex in the Su-24 MR.
The task of the machine is to reconnaissance to a depth of 400 km when flying at an altitude of 400 m in any weather conditions. The plane, apart from 2 R-60 rockets, does not carry any armament for its own defense. Therefore, the NK-24MR navigation system was installed instead of the Tiger system.
Su-24MP WRe. 1980.
Work on the construction of a version to combat air defense, or rather its electronic paralysis, i.e. the WRe (electronic warfare) version, began in OKB Sukhoi in 1976. The plane was not supposed to have any armament. The initial model became the Su-24 M (T-6 M). The machine received the designation Su-24 MP (T-6 MP).
The prototype T-6 MP-25 (25 is the broadside number) was flown in April 1980. The second T-6 MP-35 prototype quickly joined the tests. The tests lasted until 1982.
Production of the Su-24 MP izdielie 46 began in Novosibirsk in 1983. However, until 1990, only 12 were built. The first two serial Su-24 MP with board numbers 15, 55, and the remaining 8 pieces for unit 118 in Czertkiv, Ukraine.
The WRe Łandysz system was installed in the nose of the machine, while the other containers, i.e. Łoś, Bean or Mimosa, are carried in suspended containers. The system allows for jamming working terrestrial SRs operating in different wave ranges. The Ładysz system works with the remaining Reliew station and the simpler NK-24 navigation system. The details of WRe’s work in 2000 were not known. It is known that they were supposed to paralyze even the American Patriot system. The machine can support both strike (fighter-bomber) and reconnaissance aircraft, e.g. Su-24 MR.
According to the available information, no serial Su-24 MP has been brought to full operational capability. It is estimated that the withdrawn Yak-28 PPs worked better and more effectively. The underdeveloped version is evidenced by the fact that after the collapse of the CCCP, the Moscow state did not demand the return of 8 machines from Ukraine. Work on the post-CCCP version was discontinued.
Application of the Su-24 MR / MP.
Interestingly, the stationing of Su-24 MR aircraft was not always associated with Su-24 / M fighter-bomber aircraft. They were often independent units providing information for various types of troops.
In October 1990, 12 Su-24 MR aircraft were stationed in Poland together with 69 Su-24 / M machines. There were only 24 Su-24 MR aircraft in the GDR.
The largest Su-24 grouping was stationed in Ukraine: 288 aircraft, including 36 Su-24 MR and 8 Su-24 MP. The only one in this version. There were 131 aircraft in Belarus (including 12 Su-24 MR), 12 in Latvia (reconnaissance only), 60 in Georgia, 52 in Azerbaijan (including 23 reconnaissance). In the European part of the CCCP, there were 112 Su-24s in the air force, 99 aircraft were in the Baltic Fleet (including 12 reconnaissance aircraft). According to estimates, about 120 – 150 Su-24 aircraft were stationed in the Asian part of the CCCP, which gives a total number of just over 1,000 Su-24s, including over 130 reconnaissance Su-24 MR and 8 Su-24 MP.
Due to the collapse of the CCCP, the dislocation of all Soviet aircraft, including the Su-24, has changed. As of October 1992; Ukraine had 257 Su-24s. Belarus took over 40 aircraft, including 12 Su-24 MR. The rest belonged to the air force of the Moscow state, but some of them were temporarily stationed in Belarus (82) and Latvia (12 Su-24 MR). At that time, 95 (12 Su-24 MR) Su-24s belonging to the Baltic Fleet were stationed in the Kaliningrad Oblast. Several planes were also seized by Azerbaijan at Dalliar Airport in June 1992.
The design of the Su-24 MR.
Changes compared to the Su-24 M aircraft:
The aircraft takes fuel in internal tanks and 2 x 3,000 liter tanks under the wings. It does not carry the UPAZ unit for refueling other aircraft.
Compared to the Su-24 M bomber, the PNS-24M "Tigr" navigation and targeting system has been removed. However, the NK-24MR navigation system was installed. At the very tip of the nose, the "Reljef" radar antenna remained, for avoiding obstacles in low-altitude flight.
All reconnaissance devices of the aircraft are connected to the BKR-1 system (base complex razvedki), designed by O. Yakovlev from OKB Wega. The place of the "Orion" radar was occupied by the M-101 "Sztyk" side-view radar reconnaissance station (main designer W. Wieprincew from the Wega team). Under the left air intake is the A-100 camera. In place of the "Kajra" apparatus, another panoramic camera AP-402P and a TV camera Aist-M were installed. The AP-402P camera has a lens with a focal length of 90.5 mm, a film frame size of 68 x 285 mm and a resolution of 0.3 m, from a height of 400 m. from a height of 400 m. Under the central part of the aircraft’s fuselage, the "Winter" infrared reconnaissance apparatus is built in, registering temperature differences of 0.3 degrees Celsius.
Other equipment is suspended in containers. On the central boom under the fuselage, the Szpil-2M laser device pod or the SRS-14 Tangaż general reconnaissance radio pod is suspended (detects and records the location and types of Radar Stations, it can be distinguished from the Szpla-2M pod by the fact that it is smaller). On the boom under the right movable part of the wing hangs the EC/r-1M radiation reconnaissance apparatus, and on the opposite side, on the left wing, there are two R-60 rockets.
The reconnaissance information collected by the aircraft is continuously transmitted to the ground by radio by the SzRK-1 “Pomediak” apparatus. The photographic material is automatically developed on board the aircraft and dropped in the "Kadr" container on the ground. Other equipment (pilot, interference, identification) remained unchanged compared to the Su-24 M. The aircraft was also deprived of the cannon. 130 Su-24 MR and 8 Su-24 MP were built.
T-T Su-24 MR data (1980 year):
Crew of two aviators. Span 10.366 – 17.638 m. Length 24.594 m. Height 6.19 m. Bearing area 51.024 – 55.168 m2. Weight shipped 22,000 kg. Gross weight 33,325 kg. Maximum weight 39,000 kg. Fuel 11,700 + 6,000 liters. Maximum speed Ma-1.35. Top speed 1,320 km/h. Ascent rate 9,000 m/min. Landing speed 280 km/h. Range of 3,000 km, without refueling in the air. Ceiling 17,500 m. Takeoff roll 1,100 – 1,200 m. Landing roll 1,000 – 1,100 m with the use of braking parachutes.
drive unit; two AL-21 F-3 A single-flow engines with a thrust of 2 x 75.00 kN without afterburning and 2 x 109.80 kN with the use of afterburners. The jet engine have a blade adjustment system between the compressor stages.
Written by Karol Placha Hetman