Suchoj Su-7 B. 1992 - Construction

Category: Airplanes Last change: August 2019 History Construction Tally

Kraków 2017-05-08

197 Section 1964-06-01

OKB Suchoj Su-7 B (BM, BKŁ, U)

Poland

Construction

Su-7 BM nb 06. Czyżyny 2009. Photo by Karol Placha Hetman
Su-7 BM nb 06. Czyżyny 2009. Photo by Karol Placha Hetman

The KS-2 catapult chair (Kresło Suchowo) developed in OKB Suchoj, used in Su-7 BKŁ nb 807 No. 7807. Czyżyny 2009. Photo by Karol Placha Hetman
The KS-2 catapult chair (Kresło Suchowo) developed in OKB Suchoj, used in Su-7 BKŁ nb 807 No. 7807. Czyżyny 2009. Photo by Karol Placha Hetman

The KS-3 catapult chair (Kresło Suchowo) developed in OKB Suchoj, used in Su-7 BKŁ. Dęblin 2017. Photo by Karol Placha Hetman
The KS-3 catapult chair (Kresło Suchowo) developed in OKB Suchoj, used in Su-7 BKŁ. Dęblin 2017. Photo by Karol Placha Hetman

The 30 mm NR-30 cannon used on Su-7 B aircraft. 2009. Photo by Karol Placha Hetman
The 30 mm NR-30 cannon used on Su-7 B aircraft. 2009. Photo by Karol Placha Hetman

Su-7 B with a catch designed for 7 unguided missiles. Czyżyny 2008. Photo by Karol Placha Hetman
Su-7 B with a catch designed for 7 unguided missiles. Czyżyny 2008. Photo by Karol Placha Hetman

The powder launch rocket SPRD-110 used in Su-7 B. 2009. Photo by Karol Placha Hetman
The powder launch rocket SPRD-110 used in Su-7 B. 2009. Photo by Karol Placha Hetman

Su-7 BKŁ. The skid-wheel chassis. 2008. Photo by Karol Placha Hetman
Su-7 BKŁ. The skid-wheel chassis. 2008. Photo by Karol Placha Hetman

Construction Suchoj Su-7 BM

The Su-7 BM is a single-engine, single-seat, medium wing aircraft with an oblique wing. Not equipped with a radar station, but capable of performing operations in difficult weather conditions. All-metal construction, mainly made of aluminum and steel.

Double-girder wings with two auxiliary girders. The bevel angle of the leading edge is 60 degrees. Mounted at 0 wedge angle and has a negative rise of 2 degrees. The wings are equipped with two-piece, one-slot flaps with a sliding axis of rotation. "Flap wideners", ailerons and two pairs of aerodynamic steering wheels. Two 30 mm cannons were mounted at the base of the wings. Fuel tanks were placed in the wings. One armament hitch is mounted under the wings.

The circular fuselage begins with a central air grip, with a movable cone regulating the air supply to the engine. Single cabin. It protrudes from the fuselage outline. The cabin glazing consists of a permanent windscreen equipped with three windows (bullet-proof front with a flat glass) and a movable wind deflector manually moved back and equipped with a periscope to observe the rear hemisphere. Fire protection windows were used. KS-2 pilot seat, class 0/150. Behind the cab there is a compartment for equipment and fuel tanks. An engine was placed at the end of the fuselage. Four aerodynamic brakes of a rectangular shape are located at the rear of the fuselage. In the background of the fuselage a space for one braking parachute has been made. The rear of the fuselage is subtracted to replace the engine.

Plane tail horizontal plate, with a skew angle of 55 degrees and a relative thickness of 6 to 7%. Anti-flutter masses were added at the ends. The halves of the tail are interchangeable. Vertical plane of the aircraft divided into rudder and ballast.

Three-support chassis. Chassis with front wheel. Retracted and released hydraulically. The front shin is equipped with a vibration damper, which also acts as a steering (turning) wheel. All wheels single. Oil-pneumatic shock absorbers. The front landing gear retracts towards the front and is covered by two symmetrical flaps. The main landing gear retracts towards the hull. The tires have a large diameter for the possibility of using ground airports and are high pressure. The main chassis distance is 3.83 m.

Su-7 BM drive

The propulsion of the aircraft is a turbojet, single-flow, single-shaft A. Lulki AL.-7 F-1 engine with 1 x 68.65 kN thrust. (1 x 7,000 kG.) With afterburning of 1 x 98.10 kN. (1 x 10,000 kg). It consists of a 9-stage axial compressor, ring-pitcher combustion chamber, 2-stage turbine, afterburner and adjustable nozzle. The engine is equipped with an oxygen system to facilitate starting on the ground at low temperatures or high in the air. The fuel installation is located in the wings and the fuselage and amounts to 2,940 liters. You can also hang 2 fuel tanks with a capacity of 2 x 600 liters under the fuselage or wings.

Initially, the AL.-7 F-1 (TRD-31) engine with 1 x 66.64 kN thrust was used. (1 x 6 800 kG.) With post-combustion 1 x 94.08 kN (1 x 9 600 kG.).

The aircraft may use SPRD-110 launch powder rockets with 2 x 29.40 kN thrust. (2 x 3,000 kG.).

Utilities Su-7 BM

Two 30 mm NR-30 cannons.

The 4 arms hanging nodes (2 under the hull and 2 under the wings). The basic means of combat are UB-16-57U or UB-32-56U tanks with 16 or 32 57 mm S-5 shells, respectively. The machine can take up to 750 kg. bombs. The effects of the use of armament are recorded with a camera mounted in the right wing, near the fuselage.

Nuclear bombs were stored in Soviet warehouses for Polish aircraft in Poland.

Su-7 BKŁ version

Changes compared to Su-7 BM.

Aerodynamic steering wheels are reinforced on the wings. Under the wings appeared assembled since 1969, two additional hooks with a lifting capacity of 2 x 250 kg. A new KS-4 thrown chair, class 0-140, was used in the cabin. The front armored windscreen in the cabin is thinner for better visibility. Internal fuel supply increased. Aerodynamic brakes have been strengthened. The vertical arrangement has been slightly redesigned and strengthened. The main landing gear received skids. Landing is supported by two, not one braking parachute. The parachutes were placed in the container at the base of the vertical tail.

Su-7 BKŁ drive

The drive unit is the AL.-7 F-1-250 engine, whose service life has been extended to 250 hours. The engine weight is 2 103 kg. Fuel consumption 0.9 kg / kG / h. The drive unit is supported by SPRD-110 start accelerators with 2 x 29.40 kN (2 x 2 998 kG).

Construction Su-7 U

The basic difference between airplanes is the use of a two-person cabin in a tandem arrangement. The hull is 0.20 m longer. A superstructure was placed on the fuselage in which equipment moved from behind the pilot's cabin was placed. Despite the reconstruction of fuselage fuel tanks, its quantity is almost identical to the Su-7 BM version.

Individual cabin covers are lifted up to the rear pneumatically. The rear cabin is equipped with a folding periscope. Its mirrors are made of polished metal. The periscope can be used up to a speed of 600 km / h. (The reinforced version of the periscope is used up to a speed of 850 km / h).

The crew received a special version of KS-4 U-22 ejection seats, the first pilot's seat and then the instructor's seat always fired, regardless of who initiated leaving the plane.

The chassis (often treated badly by young pilots, especially during landings) and its brakes were strengthened. The front shin of the chassis was equipped with brakes and could be controlled hydraulically. The chassis braking system has received a system that sprinkles alcohol with wheel hubs for more efficient cooling.

The increase in the weight of the aircraft caused restrictions in the armament carried, the maximum suspension capacity was limited to 2,500 kg, some machines did not receive a left-wing 30 mm cannon. However, the possibility of carrying nuclear bombs was left. The sight used on the school plane is a modification with Su-7 BM marked as ASP-5ND-7U replaced from 12 production series by a newer ASP-PF-7U.

Data Suchoj Su-7 B

Data Su-7
Data Su-7

Written by Karol Placha Hetman