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PAK-TA Slon [Elephant] TsAGI - Design

The new model transport aircraft is proposed to be built according to the normal aerodynamic scheme and equipped with a highly located wing of large elongation and a tail with one keel. Almost the entire length of the fuselage should occupy a cargo compartment. This compartment is designed taking into account the experience of the An-124 project. In particular, it is planned to use the bow and tail loading ramps, as well as the possibility of placing an additional deck. The power plant should consist of four dual-circuit turbojet engines. During the construction of the airframe, it is proposed to use modern metals and alloys, as well as composite materials. On-board equipment must also meet current requirements and provide a solution to all the necessary tasks.

The proposed machine will be able to take on board cargo weighing up to 150-180 tons and deliver them to a distance of up to 7 thousand km at a speed of 850 km / h. Such characteristics will make TTS "Elephant" a world leader in its category and ensure commercial success. The aircraft will have a length of 82.3 meters, wingspan - 88.3 meters. The machine is designed for the currently developed PD-35 engines with a thrust of 35,000 kgf. It is planned to install four of these engines, in which the aircraft will be able to transport up to 180 tons of cargo over a distance of up to 7 thousand km at a speed of 850 km / h.

From the point of view of the design and layout of the fuselage, the “Elephant” resembles the “Ruslan”, however, significant differences are provided. So, the fuselage of a promising aircraft should have a cross section formed by the intersection of circular arcs. Due to this, it was possible to keep the floor width of the cargo compartment at the required level, while the ceiling height increases to 5.2 m (with the hoist lifting the hoists to 4.01 m). The upper arcs of the section form a kind of gargrot suitable for placing two salons at once.

The main part of the fuselage of the TTS "Elephant" is given over to the cargo compartment. Front and rear, it provides hinged ramps with hermetic shutter functions. In the flight position, the ramps are closed by movable fairings. Two configurations of the cargo compartment and, accordingly, two versions of the fuselage of different widths are offered. In the first case, the cabin has a width of 5.3 m, optimized for the use of standard containers and pallets. In the second case, the width is 6.4 m, which makes it possible to transport automobile and other equipment with its double row placement.

Under the ceiling of the cargo compartment, it is proposed to place two rail rails for hoists. It is planned to install an additional deck, which allows placing the payload “on two floors”. In particular, this will ensure the simultaneous transportation of containers of various types or the transport of goods and people.

In the bow of the fuselage, above the cargo compartment behind the lifting fairing, is the cockpit. Behind this, it is proposed to place a cabin or cabins for a shift crew. Behind the center wing, it is proposed to be used for similar cabins by accompanying personnel. The internal compartments are divided into two so-called boost zones. The cabin and cabins would be supported at more pressure than in the cargo compartment.

From the point of view of the design and layout of the fuselage, the “Elephant” resembles the “Ruslan”, however, significant differences are provided. So, the fuselage of a promising aircraft should have a cross section formed by the intersection of circular arcs. Due to this, it was possible to keep the floor width of the cargo compartment at the required level, while the ceiling height increases to 5.2 m (with the hoist lifting the hoists to 4.01 m). The upper arcs of the section form a kind of gargrot suitable for placing two salons at once.

The main part of the fuselage of the TTS "Elephant" is given over to the cargo compartment. Front and rear, it provides hinged ramps with hermetic shutter functions. In the flight position, the ramps are closed by movable fairings. Two configurations of the cargo compartment and, accordingly, two versions of the fuselage of different widths are offered. In the first case, the cabin has a width of 5.3 m, optimized for the use of standard containers and pallets. In the second case, the width is 6.4 m, which makes it possible to transport automobile and other equipment with its double row placement.

Under the ceiling of the cargo compartment, it is proposed to place two rail rails for hoists. It is planned to install an additional deck, which allows placing the payload “on two floors”. In particular, this will ensure the simultaneous transportation of containers of various types or the transport of goods and people. In the bow of the fuselage, above the cargo compartment behind the lifting fairing, is the cockpit. Behind her, it is proposed to place a cabin or cabins for a shift crew. Behind the center wing, it is proposed to be used for similar cabins by accompanying personnel. The internal compartments are divided into two so-called boost zones. The cabin and cabins should be supported more pressure than in the cargo compartment.

The overall, weight and other characteristics of the “Elephant” depend, first of all, on the type of the fuselage and the dimensions of the cargo compartment. Calculations show that the use of a larger cockpit leads to the need to use a wing with a span of 88.32 m instead of the original 87.1-meter. The wing area increases accordingly from 764.5 sq.m to 789.8 sq.m. An empty aircraft with a "narrow" fuselage, according to calculations, has a mass of 214.31 tons, with a "wide" one - 222.3 tons. The payload is defined as 150 tons. Fuel capacity is 124-125 tons. Maximum weight for two versions of the aircraft reaches 490.2 tons (with a narrow cabin) and 499.14 tons (with a wide one).

The flight speed is determined at the level of 800-850 km / h. With a load of 150 tons, the maximum flight range can be 7700 km. When the load increases to 180 tons, the range drops to 4900 km. Ferry range with a maximum fuel supply and without cargo - at least 18.6 thousand km. In all cases, the aircraft requires a runway of no more than 3000 m in length.