Suchoj Su-17M [kód NATO: Fitter-C]

Su-17M

The new version of the fighter bomber aircraft, derived from the Su-17, with a provisional designation Su-21, began the design of the office P. About. Sukhoi to develop in 1969. Since the beginning of the development of the Su-17, it was clear that it is necessary to replace the engine AL-7F1 for more modern. Consider the various types, eventually was elected the engine AL-21F, which began design bureau Archipa Ljulky develop in 1965 and in 1969 was supposed to be launched its serial production. But he was preferably designed for the future of the Su-24. The first version of the engine but not the thrust and the start of production was moved to the year 1970. After long twists and turns and a few air disasters was finally developed by the new engine AL-21F3, whose design reflected the information from the engine J79-GE, captured in Vietnam.

The new engine was not only more economical in fuel consumption, but it also had smaller dimensions and weight. In the project of the new aircraft, with the factory designation S-32M, called later Su-17M, therefore, reflected a few changes. The dividing plane between the front and rear parts of the fuselage is moved about 1500 mm in the back of the counter no. 28 counter no. 34. The total length of the hull remained the same, so the front of the engine to make room for another fuel tank. The rear part of the fuselage had a slightly smaller diameter, so to reduce the margin of a floating stabilizer and the height of the vertical vertical fin. Due to the anticipated smaller landing speed was dvoukopulový parachute mistaken for jednokopulový in the box under the directional rudder, which was taken from the Su-15. Under the rudder has moved from the top of the keel, for better access, and the rear antenna of the Pion. On the front of the fuselage disappeared ribbed openings ventilation přepouštěcích passports protipumpážního system of the engine AL-7F1 and also two small covers wiring, which has been moved under the main trupový the cover on the upper side of the fuselage. The first prototype was still a backup PVD-7 on the right side of the bow of the hull, the second prototype and production aircraft it already had on the left side of the bow. The first serial aircraft should be under the hull just two pylons for armament.

On the wing only minor changes were made. The first prototype had only one aerodynamic ridge on the end of the fixed part of the wings, the second prototype and production aircraft were on the upper side of each half of the solid part of the wings of the two aerodynamic ridges. Using higher quality steel for the production of stringers of the wing to increase the maximum permissible overload at the angle of the arrow 63° to 7 g. Adjusted was also the synchronization shaft between the two halves of the movable parts of the wings. The use of higher quality steel to increase the load carrying capacity of the inner wing pylons 500 kg each, so the total bearing capacity of the equipment in the first series increased to 3000 kg.

The cone of the input system had been pushed more to the vzduchvého channel, thereby to reduce the flow rate of air to the engine. Its running at nadzvukovém flight shortened to one-third.

During the tests it turned out that moving the engine back and adding another fuel tank centráž of the aeroplane greatly shifted to the back. Partly managed to compensate for the addition of armour plates on the inner wall of the air channel on the sides of the cockpit. On the first serial aircraft was still possible in the operation of swapping the wheels on the main chassis for the steel skis on the later batches since this was dropped.

Fuel system the airplane has been modified. Fuel tank no. 1, 2 and 4 were now constructed as an integral, only collection tank no. 3 remained soft gumotextilní. The contents of the fuselage tank is thereby increased more than about 1000 liters. Hydrofoil sections have remained the same.

Considerably has changed and the hydraulic system of the airframe. Instead of the three circuits were installed only two, which are mutually fully backed-up. Originally assumed and the modernization of the avionics, that eventually was taken over from the older Su-17.

The military commission called for the arming of an aeroplane new protizemními missile. You were in the armament of the aeroplane included in the course of production.

The manufacturing documentation of the new Su-17M was in 1970 moved to the factory in Komsomolsku-on-Amur and in September 1971 was completed production of the first prototype (předsériového aeroplane) WITH-32M-1. He was once again flown to the airport in the city Žukovskoje u Moscow, where the first prototype has done 28. December 1971 the first years. I 30. December 1971 was to joukowski theorem taken and the second prototype S-32M-2. During the tests of the two prototypes was the second S-32M-2 is lost in a crash in June 1972. During the tests there was an increase in range by 60%, in small and large heights increased up to about 1000 km(!).

Production of the Su-17M began in factory in Komsomolsku-on-Amur in 1972. It was for them, elected a new numbering series, the first serial aircraft had the serial number 5201. The first serial aircraft had a new power steering system, the maximum allowable instrument speed with the wing 63° was increased up to 1350 km/hr. From 63. the series has increased the number of pylons on the fuselage at four and the total carrying capacity of weaponry has increased to 4,000 kg. The configuration of the pylons on the fuselage could be changed on only two pylons (marked 1S and 2S), especially when the hanging auxiliary fuel tanks and the use of missile armament. To streamline the bombing, the plane was equipped with up to 4, associated hangers, MBD-3, so that the aircraft could carry up to 20 bombs caliber 100 kg or 10 bombs caliber 250 kg. The armament of the aircraft were included unguided rockets S-8 and hard S-25. The other loose cannon, and there the armament remained the same as on the Su-17.

Since the 70's. production of the series the plane could carry two protizemní missile CH-23 (later CH-23M). Radio homing equipment Delta was placed into the input of the cone on the bow of the hull instead of the radar range finder SRD-5M. On the later series was placed into a container that hung on the right inner wing pylon.

Since 1974 was the armament of the aeroplane included a heavy protiradiolokační shot CH-28, which was hanging up on the central pylon under the fuselage. Due to the kapalinovému missile engine had but the range is only about 35-40 km according to the height of the swing. The control apparatus of the projectile with the designation of Mětěl was placed in a container which is hung on the right inner pylon. The requirement for the introduction of laser-guided missiles CH-25 failed to fill in one of the serial aircraft were tested. About the possibility of carrying anti-aircraft missiles R-3S among the publicists are in dispute, even though he's known photos of the Su-17M "blue 80" with four R-3S. The aircraft could under the fuselage to hang the two nuclear bombs of small caliber, in contrast to the Su-17, which can carry just one.

The total was in the years 1972 to 1975 produced 251 units of Su-17M. They have become the foundation for the first export version of the Su-20.

Source:
Victor J. Markovskij, Igor In. Prichodčenko: Istrebitěl-bombardirovščik Su-17, ubijca "of",publishing Jauza, Eksmo 2013
Yefim Gordon, Dmitry Komisarov "Sukhoi Su-7/Su17", Midland Publishing 2011;
Victor J. Markovskij, Igor In. Prichodčenko: Istrebitěl-bombardirovščik Su-17, Aviacia i kosmonavtika yesterday, segodnya i zavtra no 10/2011.

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The first prototype of the S-32M-1 with armament.

Source: see above

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http://www.airwar.ru/enc/fighter/su17m.html

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