RU2297368C1 - Twin-engine multi-purpose aircraft "cholod-1" (versions) - Google Patents

Abstract

FIELD: aeronautical engineering.

SUBSTANCE: proposed aircraft has fuselage, wing, power plant, tail unit and three-leg landing gear with nose controllable leg. Solar batteries mounted on fuselage and on wing are connected with storage batteries and engines of drives of first stage of hybrid jet engines. Leading edge and rear part of wing, as well as side parts of fuselage are made from fabric impregnated with aircraft dope, painted with cold-resistant enamel and reinforced with longitudinal and transversal tubes made from cold-resistant rubber, filled with water and cooled to low temperature. Fuel is kept in wing torsion-box and in center-wing section. Aircraft is provided with one entry door on the left-hand side of fuselage, two emergency exits, type I and two emergency exits, type III. In passenger version, aircraft has seats arranged in pairs if three rows. Cargo compartment located in rear fuselage has hatch on starboard side for two containers LD-3; it is separated from passenger saloon. According to second version, provision is made for carrying pallets and cargo ramp in tail section of fuselage.

EFFECT: low cost of manufacture of aircraft.

7 cl, 8 dwg, 1 tbl

Description

The invention relates to aircraft and relates to the creation of twin-engine multi-purpose aircraft for operation at t up to -70 ° C, using the conditions and features of the regions of Siberia, the Far North, the North and South Poles, can be used to develop the colder space of the planet, to develop the Arctic and Antarctic, monitoring the atmosphere and the earth’s surface, aerial photography and geological exploration.

A well-known normal aerodynamic scheme aircraft containing the fuselage, plumage, landing gear, power plant, control panel (See G.I. Zhitomirsky. "Aircraft Design", p. 7,11,17,350, M .: Engineering, 1991).

However, this aircraft is not adapted to the conditions of the Far North.

A well-known aircraft adopted for the prototype, a normal aerodynamic design with a low wing, tail unit with two spaced keels 3-way retractable landing gear with nose bow support. The aircraft consists of an airtight fuselage with an oval cross-section, a low wing, two turbojet bypass engines placed on top in the rear of the fuselage, horizontal and vertical tail units made separate (Patent for industrial design RU No. 49560 dated 04/19/2000).

Although this aircraft can be operated at t up to -70 ° C, it is not adapted to the conditions of the Far North, expensive to manufacture, has low economy, and is also not suitable for air based.

The problem that the invention solves is to use unconventional materials in the design of the aircraft, using features characteristic of the latitudes of the Far North, North and South Poles, to reduce the cost of manufacturing aircraft using these materials in its power structures and reduce the weight of the aircraft structure, and also improve technical and operational characteristics and reduce fuel consumption for aircraft operation at t to -70 ° C.

The technical result from the implementation of the described invention is to reduce the cost of manufacturing an aircraft and operating it at a flight altitude of up to 20 km using solar energy.

This is achieved by the fact that the twin-engine multipurpose aircraft “Kholod-1” of a normal aerodynamic design, containing a sealed fuselage with an oval-shaped cross section, a wing, a power plant consisting of two engines and placed on top in the rear of the fuselage, horizontal and vertical tail with two separate and spaced keels, a 3-pole retractable landing gear with a bow driven support, while the engines are combined jet engines, and solar panels are installed on the fuselage and wings and electrically connected to the batteries located at the bottom of the nose of the fuselage, and the drive motors of the first stages of the combined jet engines, and the toe with the rear of the wing of the aircraft and the sides of the fuselage are made of fabric coated with aircraft varnish, painted with frost-resistant enamel, and reinforced with longitudinal and transverse tubes of frost-resistant rubber, filled with water and cooled to low temperatures, while fuel is placed in the wing box and in the center section, while the aircraft has one inlet ry located on the left side of the fuselage, and two emergency exits of type I and two emergency exits of type III, while in the passenger compartment, which has a height of 2.25 m, a length of 9.97 m, the seats are arranged in pairs in three rows, and in the rear of the fuselage has a cargo compartment with a side hatch on the starboard side, accommodating two LD-3 containers, and is separated from the passenger compartment by a fire barrier.

In this case, the sock with the back of the wing and the side parts of the fuselage are made of “500” fabric, and the longitudinal and transverse tubes are glued to each other and the fabric with VK-22-2 glue.

At the same time, the aircraft is equipped with a system of refueling in the air, for which purpose a fuel receiver rod is located in the nose of the fuselage.

At the same time, under the fuselage there are nodes for installing it on flying launch complexes, which can be used as An-225 Mriya and ZM Atlant.

At the same time, the seats are arranged in two rows of 9 pairs, in the third row there are 8 pairs, the step of the chairs is 810 mm, and the width of the aisles between the rows is 450 mm.

At the same time, the cabin is designed for 52 passengers.

This is achieved by the fact that the twin-engine multipurpose aircraft “Kholod-1” of a normal aerodynamic design, containing a sealed fuselage with an oval-shaped cross section, a wing, a power plant consisting of two engines and placed on top in the rear of the fuselage, horizontal and vertical tail with two separate and spaced keels, a 3-pole retractable landing gear with a bow driven support, while the engines are combined jet engines, and solar panels are installed on the fuselage and wings and electrically connected to the batteries located at the bottom of the nose of the fuselage and the drive motors of the first stages of the combined jet engines, and the toe with the rear of the wing of the aircraft and the sides of the fuselage are made of fabric coated with aircraft varnish, painted with frost-resistant enamel and reinforced with longitudinal and transverse tubes made of frost-resistant rubber, filled with water and cooled to low temperatures, while fuel is placed in the wing box and in the center section, while the aircraft has one inlet two ry located on the left side of the fuselage, two emergency exits of type I and two emergency exits of type III, while in the cargo version, where a cargo compartment is provided with a height of 2.4 m, a width of 4 m, 12 PGS-500 pallets are placed, and for loading the aircraft uses a cargo ramp located in the rear of the fuselage, an additional seat can be installed in the cockpit to accommodate the accompanying cargo or security guard.

The invention is illustrated by drawings, which schematically depict:

figure 1 - shows a side view of the aircraft;

figure 2 is a top view of the aircraft;

figure 3 is a front view of the aircraft;

figure 4 - wing design in a perspective view;

figure 5 - remote element I (enlarged and rotated);

figure 6 - design of the wing box in a perspective view;

Fig.7 - design of the fuselage compartment in a perspective view.

on Fig is a view in plan for the layout of the aircraft.

The described aircraft has a normal aerodynamic design with a high wing, tail, with two spaced keels, a 3-way retractable landing gear with a bow-mounted support, with two combined jet engines.

The aircraft consists of a sealed fuselage 1 (see figure 1), a center wing 2, two wing consoles 3 with ailerons 4 and flaps 5 (see figure 2), two combined jet engines 6 located on top in the rear of the fuselage (see Fig. .3), horizontal plumage 7 and vertical plumage 8. Solar panels 9 are mounted on the fuselage, and solar panels 10 on the wings (see figure 2). The batteries 11 (see figure 1) are located in the nose of the fuselage and feed the electric motors of the drives of the first stages of the combined jet engines.

The wing of the aircraft consists of a sock 12, a caisson 13, the rear of the wing 14 (see Fig. 4). The toe of the wing 12 is made of fabric “500” 15 impregnated with aviation varnish (see FIG. 5), painted outside with frost-resistant enamel, reinforced with longitudinal 16 and transverse 17 tubes made of frost-resistant rubber, which are glued (VK-22-2 glue) to the fabric, filled with water and cooled to low temperatures. A ground installation is used to fill the tubes with water. Ailerons 18 and two-section flaps 19 are located at the trailing edge of the wing (see Fig. 4).

The wing box 13 is made of aluminum alloys, consists of a front 20 (see Fig.6) and a rear 21 side members, upper 22 and lower 23 panels. A caisson is used to store fuel. Mounting units of 24 solar panels 10 are installed on the upper part of the side members.

The rear part of the wing 14 is made of the same materials 15, 16 and 17 as the wing toe (see figure 4).

The fuselage 1 has a rigid frame 25 (see Fig. 7) made of frames and stringers, the upper and lower skin of aluminum alloys, the side parts of the fuselage made of fabric "500" 15, impregnated with aircraft varnish, painted with frost-resistant enamel. The fabric is reinforced with longitudinal 16 and transverse 17 tubes of frost-resistant rubber, which are glued (glue VK-22-2) to fabric "500" 15, filled with water and cooled to low temperatures (see figure 5).

The aircraft is equipped with a system for refueling in the air, for which purpose a fuel receiver rod (not shown) is located in the nose of the fuselage. Fuel in tanks is located in the wing caissons and the center section.

For the possibility of air-based under the fuselage, there are nodes for installing the described aircraft on the flying launch complexes, which can be used as An-225 "Mriya" and ZM "Atlant" (not shown).

The wing of the aircraft in the central part is rigidly connected to the fuselage 1, the wing consoles have easily detachable connections (not shown).

The main landing gears have the ability to be cleaned in external sealed fairings. The front strut retracts against flight into a sealed niche in the nose of the fuselage. Niches for cleaning the landing gear are made with the possibility of heating them from the heating system of the passenger compartment with warm air (not shown).

In the cockpit (see Fig. 8) are located: commander’s seat 26, 11th pilot’s seat 27, dashboard, remotes 28, flight and navigation and radio equipment. The cockpit glazing is made of bird-resistant tinted glass with a heating system that provides the crew with a wide view of the entire front hemisphere and lateral space. The crew cabin is separated from the passenger compartment by a partition with a sliding door.

The aircraft is made with one entrance door located on the left side of the fuselage. Two emergency exits of type I and two emergency exits of type III are provided for emergency exit.

The aircraft can be made both in passenger and cargo versions. In the first case, the passenger compartment is 9.97 m long, in the front of the passenger compartment there are wardrobes 29, toilets 30, a kitchen 31 and folding cabin attendants 32. The cabin is equipped with passenger seats 33 arranged in pairs in three rows, in two rows of 9 pairs, in the third row 8 pairs. In total, the cabin is designed for 52 passengers. The step of the seats is 810 mm, the width of the aisles between the rows is 450 mm. At the rear of the fuselage is a cargo compartment 34, accommodating two LD-3 containers. A hatch is provided for loading containers on the starboard side of the aircraft. The cargo compartment is separated from the passenger compartment by a firewall.

In the cargo version, the aircraft has a cargo compartment 2.4 m high, 4 m wide, which houses 12 PGS-500 pallets. To load the aircraft, a cargo ramp located in the rear of the fuselage is used. To accommodate the accompanying cargo or security guard in the cockpit can be installed an additional chair.

The aircraft control system is electro-remote.

The aircraft can reach speeds of up to 850 km / h and, through the use of solar panels, make non-stop flights over a distance of 18,000 km.

The characteristics of the aircraft and the main dimensions of the aircraft are shown in table No. 1.

Table number 1
Aircraft characteristics Take-off weight, t 23 Fuel mass, t 7 Engines: Type Application No. 2005116581 dated 05/31/05 number × thrust 2x Number of passengers 52 Practical range, km 18000 Cruising speed, km / h 850 Flight altitude, km twenty Fuel efficiency, g / pass-km fifteen Runway length, m 1100 Price, mln. USD 10.0 The main dimensions of the aircraft Wing span, mm 28480 Aircraft length mm 19900 Aircraft height, mm 6625

Claims (7)

1. A twin-engine, multi-purpose aircraft of normal aerodynamic design, containing a sealed fuselage with an oval cross-section, a wing, a power plant consisting of two engines placed on top in the rear of the fuselage, horizontal and vertical tail with two separate and spaced keels, a three-leg retractable landing gear with nasal controlled support, characterized in that the engines are combined jet engines, and on the fuselage and wings are installed solar panels, electrically United with batteries located at the bottom of the nose of the fuselage and the drive motors of the first stages of the combined jet engines, and the nose with the rear of the wing of the aircraft and the sides of the fuselage are made of fabric coated with aircraft varnish, painted with frost-resistant enamel and reinforced with longitudinal and transverse tubes made of frost-resistant rubber filled with water and cooled to low temperatures, while fuel is placed in the wing box and in the center section, and the aircraft has one entrance door located south on the left side of the fuselage, two emergency exits of type I and two emergency exits of type III, while in the passenger compartment, which has a height of 2.25 m and a length of 9.97 m, the seats are arranged in pairs in three rows, and in the rear of the fuselage there is a cargo compartment with a side hatch on the starboard side, accommodating two LD-3 containers and separated from the passenger compartment by a fire barrier. 2. The aircraft according to claim 1, characterized in that the sock with the back of the wing and the side parts of the fuselage are made of "500" fabric, and the longitudinal and transverse tubes are glued to each other and to the fabric with VK-22-2 glue. 3. The aircraft according to claim 1, characterized in that it is equipped with a fuel refueling system in the air, for which purpose a fuel receiver rod is located in the nose of the fuselage. 4. The aircraft according to claim 1, characterized in that under the fuselage there are nodes for installing it on flying launch complexes, which can be used as An-225 "Mriya" and ZM "Atlant". 5. The aircraft according to claim 1, characterized in that the seats are arranged in two rows of 9 pairs, in the third row of 8 pairs, and the pitch of the seats is 810 mm, and the width of the aisles between the rows is 450 mm. 6. The aircraft according to claim 1, characterized in that the cabin is designed for 52 passengers. 7. A twin-engine, multi-purpose aircraft of normal aerodynamic design, containing a sealed fuselage with an oval cross-section, a wing, a power plant consisting of two engines placed on top of the rear of the fuselage, horizontal and vertical tail with two separate and spaced keels, a three-leg retractable landing gear with nasal controlled support, characterized in that the engines are combined jet engines, and on the fuselage and wings are installed solar panels, electrically United with batteries located at the bottom of the nose of the fuselage and the drive motors of the first stages of the combined jet engines, and the nose with the rear of the wing of the aircraft and the sides of the fuselage are made of fabric coated with aircraft varnish, painted with frost-resistant enamel and reinforced with longitudinal and transverse tubes made of frost-resistant rubber filled with water and cooled to low temperatures, while fuel is placed in the wing box and in the center section, and the aircraft has one entrance door, located the left side of the fuselage, two emergency exits of type I and two emergency exits of type III, while in the cargo version, where a cargo compartment is provided with a height of 2.4 m, a width of 4 m, 12 PGS-500 pallets are placed, and for loading the aircraft An additional seat can be installed in the cargo ramp located in the rear of the fuselage to accommodate the accompanying cargo or security guard in the cockpit.

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