Antonov An-8 Camp - Design

According to its design, the AN-8 is an all-metal monoplane with a high wing, an elevated tail section of the fuselage, a single-keystone vertical tail and a three-legged chassis with a nose wheel. The fuselage is a semi-monocoque with a working casing of alloy D16AT. In the cross section, it has basically the shape of a rectangle (overall dimensions in the middle part: width - 3.6 m, height - 3.8 m) with rounded bottom corners and a rounded upper part. The fuselage length of 30.74 m has 59 frames mainly Z-shaped section of sheet duralumin and 90 stringers made of extruded profiles. The shelling of the sides in the rotation zone of the propellers during operation is additionally reinforced with external straps.

The fuselage is divided into four compartments: the front with crew cabs and accompanying vehicles, cargo, hatch and stern with a cockpit arrow. The anterior and aft compartments are hermetic. The floors of the cabins are covered with stamped corrugated duralumin panels. The crew of the aircraft consists of six people: two pilots, a navigator (located in the glazed front of the fuselage), an airborne, airborne and stern arrow.

The floor and sides of the pilot cabin in the area of the pilots' workplaces are equipped with 8 mm thick armor. The pilots' armchairs have 16 mm armored pins and 25 mm armored headbands.

To exclude the possibility of a flat corkscrew and improve the characteristics of the exit of the aircraft from a steep corkscrew on the upper surface of the fuselage behind the wing, antishock spoilers are installed, which were later dismantled because of low efficiency. The wing is 37 m wide and has an area of 117.2 m 2 of caisson type, free-bearing, trapezoidal in shape without geometric twist. The wing consists of five parts: a center wing, two middle and two cantilever parts. The wing profile is variable in scope: profile C-5-18 along the symmetry axis of the airplane (center wing), profile C-3-16 at 0.675 semi-spacing and C-3-14 at the ends of the wing. The wing extension is 11.7; narrowing is 2.75; the angle of the transverse V wing is 0; angle of installation 4°; Wing sweep of 1/4 chords 6°50'.

On each half-wing in the middle part there is a double-slit flap with a deflector, in the console part - an aileron, consisting of two parts. Ailerons with an area of 7.84 m2 have aerodynamic compensation and weight balancing. The ailerons have servocompensators (trimmers), the area of which is 0.84 m2. The ailerons deviate upward by 25° downwards by 15°. Flaps are deflected downwards: on takeoff - to 25°, on landing - to 45°.

Control of rudders and ailerons - mechanical, by means of links; flaps - electro-remote; locking system - cable.

The power plant includes two TVA AI-20D with a maximum power of 5180 e. The dry weight of the engine is 1080 kg. Propeller has four-blade, pulling (left rotation), vane and variable in flight step. The propeller pitch change actuator is hydraulic. The engines are started by two starter generators. Later on in the process of operation to increase the autonomy of the aircraft in the left fairing of the chassis the turbo unit TG-16 was installed.

The fuel system is divided into left and right parts, which include five groups of tanks, united by pipelines of ringing. The total capacity of the tanks is 13,080 liters. The fuel system is equipped with fuel consumption control and a neutral gas system. The aircraft is equipped with a fire protection system consisting of four 8-liter cylinders, pipelines and control units.

The chassis consists of a front two-wheel support and two main supports with four-wheeled carts. The track of the chassis along the axes of the amortization racks is 3.8 m, the base is 8.65 m. The wheels of the main bearings are 950x350 mm, the brakes, the front ones - 900x300 m, non-brake. Low pressure in the tires of the wheels allows the aircraft to operate on unpaved airfields. The chassis supports are retracted on the flight: the front is in the fuselage, the main ones are in the fairings along the sides of the fuselage.

The hydraulic system consists of the main and emergency. It provides for cleaning and releasing the chassis, braking the wheels and turning the front support, opening and closing the chassis and cargo door flaps, the operation of the autopilot and wiper steering machines. The electrical system is designed to supply the on-board consumers with constant, alternating single-phase and three-phase currents. This system ensures the operation of devices and radio equipment, the start-up of engines and the feeding of fuel system units, the release and cleaning of flaps, as well as the functioning of small, bomber, airborne and other equipment.

Pilot-navigational and radio equipment allows you to fly in different weather conditions day and night, including in automatic mode using autopilot. High-altitude and oxygen equipment provides normal working conditions for the crew on all flight modes. The anti-icing system consists of air-heating system (heating of the front edges of the wing and air intakes of engines, tunnels of oil coolers and side windows of cab lights), electrothermal (heating of the front edges of the keel and stabilizer, windshields of the pilot's cockpit and the receiver of air pressure (PVD) and liquid systems.

Control of rudders and ailerons is carried out by means of rigid rods and cable wiring. Control flaps, trim tabs aileron and rudder direction - electro-remote.

The structure of cannon armament includes: a stern tower with two 23-mm AM-23 guns, an electro-remote tower control system and a sighting and computing unit. Bomber weapons include illuminating aerial bombs: four PHOTAB-100-80 on cassette holders in the nose of the fairings of the chassis and six TSOSAB-10 on the holders in the tail section.

The landing and transport equipment ensures the deployment of airborne personnel in the cargo cabin and parachute landing, as well as the fastening of cargo and equipment and their dumping. Loading and unloading of self-propelled machinery is carried out in its own way with the use of cargo ladders (carried on board), non-self-propelled vehicles - using a cable system using a tractor or an electric winch located outside the aircraft.