RU2670161C1 - Aircraft (options) - Google Patents

Abstract

FIELD: aviation.SUBSTANCE: group of inventions refers to aircraft engineering. Aircraft includes a fuselage, power unit, control cabin, integral control system and composite wings. In the first variant, the aircraft includes a power plant with bypass turbojet engines (BTJE) with a degree of contour grater than 2. Composite wings are located in the region of the incident flow of an expiring jet from the BTJE. There are additional extendable profile elements of the wing. Exhaust part of the BTJE nozzle is located at a distance from the toe of the composite wing at a distance not less than ΔL = C * max, where C * max is the maximum thickness of the wing in the vertical plane along the axis of the jet engine. Second, third and fourth versions of the aircraft are distinguished by the use of a power plant with different types of engines for different types of aircraft.EFFECT: group of inventions is aimed at improving aerodynamic characteristics.8 cl, 85 dwg

Description

The invention relates to the field of aviation, namely to aircraft using a wing with variable aerodynamic characteristics and can be used for aircraft of various types.

The most prominent representative of the optimal combination of technical solutions to improve the flight characteristics of the aircraft is the An-70 aircraft (Wings of the Motherland, 1994, N 8, p. 7-9). From the point of view of creating the aircraft lifting force, this aircraft used blowing over most of the upper and lower wing surfaces with powerful jets from D-27 turboprop engines that are installed in the front of the wings. Due to this factor, in combination with the advanced mechanization of the wing, the wing's lift is doubled. The aim of the present invention is the use of blowing the upper and lower parts of the wing with a free flow of various types of engines to increase the lifting force of the wing of the aircraft.

Known design study S.A. Chaplygina (“The Theory of the Lattice Wing”, Selected Works on the Theory of Wing., Leningrad, State Publishing House of Technical and Theoretical Literature, 1949) in which it was proved that the lifting force of a wing of a multidimensional wing significantly exceeds the lifting force of a similar individual wing . The study of a multi-sectional wing S.A. Chaplygina (“Experimental aerodynamics”, Martynov AK, State Publishing House of the Defense Industry., 1949, see Fig. 8.56, p. 312), which presents data on a significant increase in the lifting force of a multi-sectional wing. The disadvantage of the above wing designs is the high aerodynamic drag in horizontal cruising flight mode. There is also a method of changing the aerodynamic characteristics of an aircraft wing (RF patent N2250859, OJSC “CC FPG“ Russian Aviation Consortium ”, authors Artemyev VV, Kanukov MI, Klimov VT, et al., Publ. 27.04 .2005) consisting in the fact that the wing is made of composite of small and large elements of close profile, while in the retracted position of both elements form a single profile, and when released, the small element is diverted from the large profile to increase the thickness of the composite wing, when this small element is diverted from the large Profile of equidistantly, and the area ratio of the large and small composite wing profile is selected to be 1: 0.3. This decision was made as a prototype. The disadvantages of this technical solution include the occurrence of a non-streamlined cavity on the upper plane of the main wing profile with the extended position of the small profile wing. The aim of this invention is the use of a transformable multifaceted wing to improve the aerodynamic characteristics of the wing of an aircraft with different flight modes of the aircraft associated with takeoff, acceleration, climb, descent and landing.

This goal is achieved for an aircraft comprising a fuselage, a multiple engine propulsion system, a control cabin, an integrated control system, composite wings containing the main wing profile and additional extendable profile elements, while in the horizontal cruising flight mode the main wing profile and additional profile elements form a single streamlined the wing profile, while the engines are made of double-circuit turbojet (turbofan) with a degree of contour of more than 2, while the composite wings are positioned in the region of the flowing stream of the outflowing jet from the turbofan engines with a contour degree of more than 2, while additional extendable wing profile elements are made either in the form of one or more wing liners extended above the upper surface of the main wing profile, or in the form of one or more wing liners extended under the lower surface of the main wing profile, or together in the form of one or more elytra and wing liners, while the wing profile is made in the form of a flat-convex or concave a convex segment profile, while the profile of the wing flaps is made in the form of a flat-convex or biconvex segment profile, while the main profile of the wing with extended wing flaps and wing flaps has a streamlined profile shape, while the flow of the outflowing jet from the nozzles of one or more engines of the turbofan engine with a contour degree of more than 2 occurs along the upper and lower surfaces of the main wing profile and additional extendable wing profile elements, while the exhaust part of the nozzle is one more than a few engines with a contour of more than 2 are located at a distance from the toe of the composite wing at a distance of not less than Δ L = C * max, where C * max is the maximum thickness of the composite profile of the wing, taking into account extended wing liners and wing liners in the vertical plane along the axis of the engine . This goal is also achieved for an aircraft with vertical take-off and landing, which includes a fuselage, a multi-engine powerplant, a control cabin, an integrated control system, composite wings containing the main wing profile and additional extendable profile elements, while in the horizontal cruising flight mode the main wing profile , flaps and additional profile elements form a single streamlined wing profile, while the engines are double-thrust turbofan engines with a degree of contour more than 2, while the composite wings are located in the region of the incoming flow of the outflowing jet from the turbofan engines with a contour degree of more than 2, while the additional extendable wing profile elements are made either in the form of one or more wing flaps extended over the upper surface of the main wing profile, or in the form of one or more wing flaps extended under the lower surface of the main wing profile, or together in the form of one or more wing flaps and wing flaps, with the profile of one or more x wing flaps made in the form of a flat-convex or concave-convex segment profile, while the profile of one or more of the wing flaps is made in the form of a flat-convex or biconvex segment profile, while the main wing profile with the wing flaps extended and the wing flaps has a streamlined profile shape, in this case, a free-stream flowing out of a flowing jet from the nozzles of one or several engines of a turbofan engine with a degree of contour greater than 2 occurs along the upper and lower surfaces of the main wing profile and additional extended wing elements, while the exhaust part of the nozzle of one or more engines of a turbofan engine with a contour degree of more than 2 is located at a distance from the toe of the composite wing at a distance of not less than Δ L = C * max, where C * max is the maximum thickness of the composite wing profile with taking into account the extended wing slats and wing liners in a vertical plane along the axis of the engine, while for the possibility of creating a stable total balanced power reactive moment relative to the center of gravity of the aircraft in the vertical mode odema, hovering and landing resultant driving forces from single or groups turbojet bypass engines with the degree Outlined 2 directed in at least three directions. This goal is also achieved for an aircraft comprising a fuselage, a propulsion system with propeller, or turboprop, or turboprop engines, a control cabin, an integral control system, composite wings containing the main wing profile and additional extendable profile elements, while in the horizontal cruising flight mode the main wing profile and additional profile elements form a single streamlined wing profile, while the composite wings are located in the current flowing from a rotary engine, or turboprop, or turbofan engine, while the free-flowing flow of a flowing jet of rotor, or turboprop, or turbofan engine occurs on the upper and lower surfaces of the main wing profile and additional extendable wing profile elements, with additional extendable profile wing elements are made either in the form of one or more elytra, extended over the upper surface of the main profile to it came either in the form of one or more wing flaps extended under the lower surface of the main wing profile, or together in the form of one or several wing flaps and wing flaps, while the wing profile was made in the form of a plano-convex or concave-convex segment profile, while the profile of the wing flaps made in the form of a plano-convex or biconvex segment profile, while the main wing profile with extended wings and wing liners has a streamlined profile shape. This goal is also achieved for an aircraft with vertical take-off and landing, which includes a fuselage, a power plant with propeller, or turboprop, or turbofan engines, a control cabin, an integrated control system, composite wings containing the main wing profile and additional extendable profile elements, while In horizontal cruising flight mode, the main wing profile and additional profile elements form a single streamlined wing profile, while the composite wings they are located in the free-stream region of the outflowing jet of propeller, or turboprop, or turbofan engines, while the free-flowing of the outflowing jet of propeller, or turboprop, or turbofan engines occurs on the upper and lower surfaces of the main wing profile and additional retractable wing profile elements, wherein additional retractable wing profile elements are made either in the form of one or more elytra wing wings with the upper surface of the main wing profile, either in the form of one or more wing flaps extended under the lower surface of the main wing profile, or together in the form of one or more wing flaps and wing flaps, while the profile of one or more wing flaps is made in the form of a plano-convex or concave-convex segment profile, while the profile of one or more of the wing flaps is made in the form of a plano-convex or biconvex segment profile, while the main wing profile with extended wing liners and underwing lkah has a streamlined profile shape, while for the possibility of creating a stable total balanced power reactive moment relative to the center of gravity of the aircraft in the vertical lift, hover and landing mode, the resulting traction forces from single or groups of rotor, turboprop or turbofan engines are directed in at least three directions .

Additional extendable profile elements in the extended position have the ability to rotate to change the angle of attack.

The illustrative examples of this invention show the versions of the transformable wing of the aircraft, as well as variants of the aircraft using the options of the transformable wing:

in FIG. 1 - section A 1.1 - A 1.1, a diagram of the airflow blowing of a transformable wing profile of an aircraft with extended slotted flaps and with an extended wing liner located at the front of the wing at the moment the airplane takes off from the ground is shown, while the chord size of the ejected wing liner is 0.3 the size of the chord of the entire wing, while the wing profile is made in the form of a concave-convex segment profile, while the main wing profile, with the wing wing extended, has a streamlined profile;

in FIG. 2 is a section A1.2-A1.2, a diagram of a free-air blowing of a transformable wing profile of an airplane with a deflected flap, with an extended slat and with an extended slat located in front of the wing at the time of acceleration of the aircraft and climb is shown, with the size the chords of the elytra being ejected is 0.3 of the size of the chord of the entire wing, while the profile of the wing is made in the form of a concave-convex segment profile, while the main wing profile, when the wing is extended, has a streamlined profile;

in FIG. 3 is a section A1.3-A1.3, a diagram of a free-air blowing of a transformable airplane wing profile of FIG. 1, 2 in the horizontal cruise flight mode;

in FIG. 4 - section A1.2-A1.2, shows a diagram of a free flow of atmospheric air of a transformable wing profile of an airplane with extended slotted flaps and with extended wing flaps located in the front and rear of the main wing profile at the time of the plane's separation from the ground, while the size of the chord issued elytra is 0.2 of the size of the chord of the entire wing, while the front profile of the elytra is made in the form of a concave-convex segment profile, and the rear profile of the elytra is made in the form of a biconvex segment segment ofilya, with the main wing profile when nominated nadkrylkah has a streamlined profile;

in FIG. 5 - section A2.2-A2.2, shows a diagram of the free flow of atmospheric air of a transformable wing profile of an aircraft with a deflected flap, with an extended slat and with extended wing slats located in the front and rear of the main wing profile at the time of acceleration and climb the size of the chord of the elytra being ejected is 0.2 of the size of the chord of the entire wing, while the front profile of the elytra is made in the form of a concave-convex segment profile, and the rear profile of the elytra is made in the form of a double a convex segment profile, while the main wing profile, with extended wing slats, has a streamlined profile;

in FIG. 6 is a section A3.2-A3.2, there is shown a diagram of blowing by a free flow of atmospheric air of a transformable profile of an airplane wing of FIGS. 4, 5 in a horizontal cruise flight mode;

in FIG. 7 - section A1.3-A1.3, shows a diagram of a free flow of atmospheric air of a transformable wing profile of an aircraft with extended slotted flaps and with extended wing slats located in the front and rear of the main wing profile at the time of the plane's separation from the ground, the size the chords of the elytra wings are 0.2 of the size of the chord of the entire wing, while the front profile of the elytra is made in the form of a concave-convex segment profile, and the rear profile of the elytra is made in the form of a biconvex segment segment profile, while the front elytra is extended to a greater height than the rear, while the main wing profile with extended elytra has a streamlined profile;

in FIG. 8 - section A2.3-A2.3, shows a diagram of the free flow of atmospheric air of a transformable airplane wing profile with a deflected flap, with an extended slat and with extended wing slats located in the front and rear of the main wing profile at the time of acceleration and climb the size of the chord of the elytra being ejected is 0.2 of the size of the chord of the entire wing, while the front profile of the elytra is made in the form of a concave-convex segment profile, and the rear profile of the elytra is made in the form of a double a convex segment profile, while the anterior elytra is extended to a greater height than the posterior one, while the main wing profile, with the elytra extended, has a streamlined profile;

in FIG. 9 is a section A3.3-A3.3, a diagram of a free-stream airflow of a transformable profile of an airplane wing of FIG. 7, 8 in the horizontal cruise flight mode;

in FIG. 10 is a section A1.4-A1.4, shows a diagram of a free flow of atmospheric air of a transformable wing profile of an airplane with extended slotted flaps, with an extended wing liner located in the front of the wing and with an extended wing liner located in the tail of the main wing profile at the time of separation from the ground, while the chord size of the ejected wing liner and the wing liner is 0.3 of the size of the chord of the entire wing, and the wing profile is made in the form of a concave-convex segment profile, while the wing flap is made in the form of a biconvex segment profile, while the main wing profile, with the wing and wing liner extended, has a streamlined profile;

in FIG. 11 - section A2.4-A2.4, shows a diagram of a free flow of atmospheric air of a transformable wing profile of an aircraft with a deflected flap, with an extended slat and with an extended slat located in the front of the wing and with an extended wing in the tail section of the main wing profile in the moment of acceleration of the aircraft and climb, while the chord size of the extended wing liner and the wing liner is 0.3 of the size of the chord of the entire wing, while the wing profile is made in the form of a concave-convex segment pro For this, the wing profile is made in the form of a biconvex segment profile, while the main wing profile, with the wing and wing liner extended, has a streamlined profile;

in FIG. 12 is a section A3.4-A3.4, a diagram of a free-stream airflow of a transformable profile of an airplane wing of FIG. 10, 11 in the horizontal cruise flight mode;

in FIG. 13 is a section A1.5-A1.5, shows a diagram of a free flow of atmospheric air of a transformable wing profile of an aircraft with extended slotted flaps, with an extended wing liner located in the front of the wing and with an extended wing liner located in the tail of the main wing profile at the time of separation from the ground, while the chord size of the elyser and the wing liner is 0.2 of the size of the chord of the entire wing, while the wing profile is made in the form of a concave-convex segment profile, while the wing flap is made in the form of a biconvex segment profile, while the main wing profile, with the wing and wing liner extended, has a streamlined profile;

in FIG. 14 - section A2.5-A2.5, shows a diagram of a free flow of atmospheric air of a transformable profile of an airplane wing with a deflected flap, with an extended slat and with an extended slat located in the front of the wing and an extended fender located in the tail of the main wing profile at the moment acceleration of the aircraft and climb, while the chord size of the ejected wing liner and the wing liner is 0.2 of the size of the chord of the entire wing, while the wing profile is made in the form of a concave-convex segment profile , The profile with the fender liner is formed as a bi-convex profile of the segment, with the main wing profile, and when extended nadkrylke fender liner has a streamlined profile;

in FIG. 15 is a section A3.5-A3.5; there is shown a diagram of a free-stream airflow of a transformable profile of an airplane wing of FIG. 13, 14 in the horizontal cruise flight mode;

in FIG. 16 is a section A1.6-A1.6, shows a diagram of a free flow of atmospheric air of a transformable wing profile of an aircraft with extended slotted flaps, with two extended wing flaps located in the front and rear of the main wing profile and with an extended wing in the tail of the main the wing profile at the time of the plane’s tearing off the ground, while the chord size of the elytra wing and wing liner is 0.2 of the size of the chord of the entire wing, while the profile of the front wing liner is concave Clog segment profile and a rear profile nadkrylka configured as a bi-convex profile of the segment, the slat profile is designed as a bi-convex profile of the segment, with the main wing profile when nominated nadkrylkah and the fender liner has a streamlined profile;

in FIG. 17 is a section A2.6-A2.6, shows a diagram of a free flow of atmospheric air of a transformable wing profile of an aircraft with a deflected flap, with an extended slat and two extended wing flaps located in the front and rear of the main wing profile and with an extended wing flap located in the tail part of the main wing profile at the time of acceleration of the aircraft and climb, the size of the chord of the elyers and the wing liner being 0.2 of the size of the chord of the entire wing, while the profile of the front wing liner is flax in the form of a concave-convex segment profile, and the rear profile of the wing liner is made in the form of a biconvex segment profile, while the wing profile is made in the form of a biconvex segment profile, while the main wing profile, with the wing liners and the wing liner extended, has a streamlined profile ;

in FIG. 18 is a section A3.6-A3.6, a diagram of a free-air blowing of a transformable profile of an airplane wing of FIG. 16, 17 in the horizontal cruise flight mode;

in FIG. 19 is a section A1.7-A1.7, shows a diagram of a free flow of atmospheric air of a transformable wing profile of an aircraft with extended slotted flaps, with two extended wing flaps located in the front and rear of the main wing profile and with an extended wing in the tail of the main profile wing at the time of the plane’s takeoff from the ground, while the chord size of the ejected wing flaps is 0.2 of the size of the chord of the entire wing, while the size of the chord of the wing flap is 0.3 of the size of the chord in this case, the wing profile is made in the form of a concave-convex segment profile, and the rear wing profile is made in the form of a biconvex segment profile, while the wing profile is made in the form of a biconvex segment profile, while the front wing liner is extended higher than the rear, with the main wing profile, with extended wings and wing liner, has a streamlined profile;

in FIG. 20 is a section A2.7-A2.7, shows a diagram of a free flow of atmospheric air of a transformable wing profile of a plane with a deflected flap, with an extended slat and two extended wing flaps located in the front and rear of the main wing profile and an extended wing flap located in the tail section the main wing profile at the time of acceleration of the aircraft and climb, while the size of the chord of the released wing flaps is 0.2 of the size of the chord of the entire wing, while the size of the chord of the wing flap is composed of t 0.3 of the size of the chord of the entire wing while the profile of the front wing liner is made in the form of a concave-convex segment profile, and the rear profile of the wing liner is made in the form of a biconvex segment profile, while the wing profile is made in the form of a biconvex segment profile, with this front elytra is extended to a greater height than the rear, while the main wing profile, with extended elytra and wing liner, has a streamlined profile;

in FIG. 21 is a section A3.7-A3.7, a diagram of a free-stream airflow of a transformable profile of an airplane wing of FIG. 19, 20 in the horizontal cruise flight mode;

in FIG. 22 is a section B1.1-B1.1, a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft with extended slotted flaps, with an extended wing liner located in the front part of the wing at the time of separation of the aircraft from of land, while the chord size of the elytra is equal to 0.3 of the size of the chord of the entire wing, while the profile of the wing is made in the form of a concave-convex segment profile, while the main profile of the wing, when extended m nadkrylke has a streamlined profile;

in FIG. 23 is a section B1.2-B1.2, a diagram of a free-stream blowing of an outgoing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of an aircraft with a deflected flap and with an extended wing liner located in front of the wing at the time of acceleration of the aircraft and is shown climb, the chord size of the elytra being ejected is 0.3 of the size of the chord of the entire wing, while the wing profile is made in the form of a concave-convex segment profile, with the main wing profile being extended om liner, has a streamlined profile;

in FIG. 24 is a section B1.3-B1.3, a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft of FIG. 22, 23 in the horizontal cruise flight mode;

in FIG. 25 is a section B1.2-B1.2, a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft with extended slotted flaps and with extended wing flaps located in the front and rear of the main wing profile in the moment the plane takes off from the ground, while the chord size of the elytra is equal to 0.2 of the size of the chord of the entire wing, while the front profile of the elytra is made in the form of a concave-convex segment profile, and the aft wing profile is made in the form of a biconvex segment profile, while the main wing profile, with the wing wings extended, has a streamlined profile;

in FIG. 26 is a section B2.2-B2.2, a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft with a deflected flap and with extended wing flaps located in the front and rear parts of the main wing profile in the moment of acceleration of the aircraft and climb, while the chord size of the elytra wing is 0.2 of the size of the chord of the entire wing, while the front wing profile is made in the form of a concave-convex segment profile, and Nij nadkrylka profile is formed as a bi-convex profile of the segment, with the main wing profile when nominated nadkrylkah has a streamlined profile;

in FIG. 27 is a section B3.2-B3.2, a diagram of a free-stream blowing of an outflowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft of FIG. 25, 26 in the horizontal cruise flight mode;

in FIG. 28 is a section B1.3-B1.3, a diagram of a free-stream blowing of an outgoing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft with extended slotted flaps and with extended wing flaps located in the front and rear of the main wing profile is shown at the moment the plane takes off from the ground, while the chord size of the elytra is equal to 0.2 of the size of the chord of the entire wing, while the front profile of the wing liner is made in the form of a concave-convex segment profile, and the rear wing profile is made in the form of a biconvex segment profile, while the front wing liner is extended to a higher height than the rear one, while the main wing profile with the wing wings extended has a streamlined profile;

in FIG. 29 is a section B2.3 - B2.3, a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft with a deflected flap and with extended wing flaps located in the front and rear of the main wing profile in the moment of acceleration of the aircraft and climb, while the size of the chord of the elytra is equal to 0.2 of the size of the chord of the entire wing, while the front profile of the wing liner is made in the form of a concave-convex segment profile, and adny nadkrylka profile is formed as a bi-convex profile of the segment, the front nadkrylok promoted to a greater height than the rear, with the main wing profile when nominated nadkrylkah has a streamlined profile;

in FIG. 30 is a section B3.3-B3.3, there is shown a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft of FIG. 28, 29 in the horizontal cruise flight mode;

in FIG. 31 is a section B1.4-B1.4, a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a degree of contour of more than 2 transformable wing profiles of the aircraft with extended slotted flaps and with an extended wing liner located in front of the wing and with an extended wing liner located in the tail section of the main wing profile at the moment the plane takes off from the ground, while the chord size of the released wing flap and wing flap is 0.3 of the size of the chord of the entire wing, while the wing flap ying a concavo-convex profile of the segment, the profile with the fender liner is formed as a bi-convex profile of the segment, with the main wing profile, and when extended nadkrylke fender liner has a streamlined profile;

in FIG. 32 is a section B2.4-B2.4, a diagram of a free-stream blowing out of a flowing jet from turbofan engines with a contour of more than 2 transformable wing profiles of the aircraft with a deflected flap and with an extended wing liner located in the front part of the wing and an extended wing liner located in the tail part of the main wing profile at the time of acceleration and climb, while the size of the chord of the extended wing liner and the wing liner is 0.3 of the size of the chord of the entire wing, while the wing profile is made in the form of a concave-convex segment profile, wherein the wing profile is made in the form of a biconvex segment profile, while the main wing profile, with the wing and wing liner extended, has a streamlined profile;

in FIG. 33 is a section B3.4-B3.4, a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft of FIG. 31, 32 in the horizontal cruise flight mode;

in FIG. 34 is a section B1.5-B1.5, a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles with extended slotted flaps and with an extended wing liner located in the front part of the wing and an extended wing liner located in the tail section of the main wing profile at the time of the plane’s separation from the ground, while the chord size of the elyser and wing flap is 0.2 of the size of the chord of the entire wing, yen in the form of a concave-convex segment profile, while the wing profile is made in the form of a biconvex segment profile, while the main wing profile, with the wing and wing liner extended, has a streamlined profile;

in FIG. 35 is a section B2.5-B2.5, a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable airplane wing profiles with a deflected flap and with an extended wing liner located in the front part of the wing and with an extended wing liner located in the tail of the main wing profile at the time of acceleration of the aircraft and climb, while the size of the chord of the elyser and wing flap is 0.2 of the size of the chord of the entire wing, while the wing profile is made n a concavo-convex profile of the segment, the profile with the fender liner is formed as a bi-convex profile of the segment, with the main wing profile, and when extended nadkrylke fender liner has a streamlined profile;

in FIG. 36 is a section B3.5-B3.5, a diagram of a free-stream blowing of a flowing-out jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft of FIG. 34, 35 in the horizontal cruise flight mode;

in FIG. 37 - section B1.6-B1.6, shows a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft with extended slotted flaps and with two extended wing flaps located in the front and rear of the main wing profile and an extended wing flap located in the rear of the main wing profile at the time of the plane’s takeoff from the ground, while the chord size of the elyser wings and the wing liner is 0.2 of the total chord size It turned out that the profile of the front wing liner is in the form of a concave-convex segment profile, and the rear profile of the wing liner is made in the form of a biconvex segment profile, while the wing profile is made in the form of a biconvex segment profile, while the main wing profile, with the wing liners and the wing liner extended, has a streamlined profile;

in FIG. 38 is a section B2.6-B2.6, a diagram of a free-stream blowing of a flowing jet from turbofan engines with a contour of more than 2 transformable airplane wing profiles with a deflected flap and with two extended wing flaps located in the front and rear parts of the main wing profile and an extended wing flap located in the rear part of the main wing profile at the time of acceleration of the aircraft and climb, while the chord size of the emitted wing flaps and the wing liner is 0.2 of the total chord size la, the profile of the front wing liner is made in the form of a concave-convex segment profile, and the rear profile of the wing liner is made in the form of a biconvex segment profile, while the profile of the wing liner is made in the form of a biconvex segment profile, while the main wing profile, with the wing liners extended and Locker, has a streamlined profile;

in FIG. 39 is a section B3.6-B3.6, a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft of FIG. 37, 38 in the horizontal cruise flight mode;

in FIG. 40 is a section B1.7-B1.7, there is shown a diagram of a free-stream blowing out of a flowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft with extended slotted flaps and with two extended wing flaps located in the front and rear of the main wing profile and with an extended wing liner located in the tail of the main wing profile at the time of the plane’s takeoff from the ground, while the chord size of the elytra wing wings is 0.2 of the size of the chord of the entire wing, when ohm, the size of the chute of the ejected wing flap is 0.3 of the size of the chord of the entire wing, while the profile of the front wing of the wing is made in the form of a concave-convex segment profile, and the rear profile of the wing of the wing is made in the form of a biconvex segment profile, while the wing profile is made in the form of a biconvex segment profile, while the front elytra is extended to a greater height than the rear, while the main wing profile, with the extended elytra and wing liner, has a streamlined profile;

in FIG. 41 is a section B2.7-B2.7, there is shown a diagram of a free-stream blowing out of a flowing jet from turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft with a deflected flap and with two extended wing flaps located in the front and rear parts of the main wing profile and with an extended wing liner located in the rear of the main wing profile at the time of acceleration of the aircraft and climb, while the chord size of the elytra wing is 0.2 of the size of the chord of the entire wing, the size of the chute of the ejected wing flap is 0.3 of the size of the chord of the entire wing, while the profile of the front wing of the wing is made in the form of a concave-convex segment profile, and the rear profile of the wing of the wing is made in the form of a biconvex segment profile, while the wing profile is made in the form of a biconvex segmented profile, while the front wing liner is extended to a greater height than the rear, while the main wing profile, with the wing liners and the wing liner extended, has a streamlined profile;

in FIG. 42 is a section B3.7-B3.7, a diagram of a free-stream blowing of an outflowing jet from turbofan turbofan engines with a contour degree of more than 2 transformable wing profiles of the aircraft of FIG. 40, 41 in the horizontal cruise flight mode;

in FIG. 43 is a layout diagram of an aircraft in plan with a cigar-shaped fuselage with two turbojet engines located in the rear of the fuselage, while the swept wings of a composite profile with variable aerodynamic characteristics are located in the middle of the aircraft with a free flow of atmospheric air;

in FIG. 44 is a layout diagram of an aircraft in plan with a cigar-shaped fuselage, with two turbofan turbofan engines with a contour degree of more than 2, for example, turbofan engines with flow mixing, placed on forward consoles in front of the toe of the side straight wings of a composite profile and one turbofan turbofan engine with degree of contour more than 2, for example, a turbofan engine with flow mixing located in the rear of the fuselage in front of the trapezoid the wing of the composite profile, while the socks of all wings of the composite profile with variable aerodynamic characteristics are located in the alignment of the incoming flow of the outflowing jet from turbofan jet engines, while the exhaust part of the nozzles of all jet engines with a degree of contour more than 2 is located at a distance from the nose of the composite wing at a distance of not less than ΔL = C * max, where C * max is the maximum thickness of the wing of the composite profile of the wing, taking into account extended wing flaps and wing flaps.

in FIG. 45 is a layout diagram of an airplane in plan with a cigar-shaped fuselage shape, with four turbofan turbofan engines with a contour degree of more than 2, for example turbofan engines with flow mixing, placed on horizontal consoles in front of the fuselage and one turbofan turbofan engine with a contour of more than 2 , for example, a turbofan engine with flow mixing located in the rear of the fuselage, while the side straight wings of the composite profile with and interchangeable aerodynamic characteristics are located behind the front turbofan jet engines in the direction of flight, and behind the turbofan engine in the rear of the fuselage there is a trapezoidal wing of a composite profile with variable aerodynamic characteristics, while the socks of all wings of a composite profile with variable aerodynamic characteristics are located in the jet from turbofan turbofan engines, the exhaust part of the nozzles of all jet engines STUDIO turbofan having a degree Outlined 2 located at a distance from the nose of the composite wing at a distance less than ΔL = C * max, where C * max - maximum thickness of the wing with the wing flaps and nakrylkov nominated.

in FIG. 46 - in the vertical take-off, hover and landing mode, the layout diagram of an aircraft with a shortened or vertical take-off and landing in plan with a cigar-shaped fuselage shape, with two rotary turbofan turbofan engines with a degree of contour of more than 2, for example, turbofan engines with flow mixing, placed on horizontal consoles with a rotary platform for the possibility of joint rotation of two front turbofan engines and sections of the front segment rotary wings of a composite ofilia in the front of the fuselage and one turbofan turbofan engine with a degree of contour more than 2, for example a turbofan engine with flow mixing, located in the rear of the fuselage, while behind the turbofan engine in the rear of the fuselage there is a trapezoidal wing of a composite profile, while all wings are worn of a composite profile with variable aerodynamic characteristics are located in the alignment of the incoming flow of the outflowing jet from the turbofan turbofan engines the exhaust part of the nozzles of all jet engines with a contour degree of more than 2 is located at a distance from the toe of the composite wing at a distance of at least ΔL = C * max, where C * max is the maximum thickness of the wing, taking into account extended wings and fenders, while in the vertical mode lifting, hovering and landing resulting traction forces from turbofan turbofan engines are directed radially in three directions;

in FIG. 47 is a layout diagram of an airplane with a shortened or vertical take-off and landing in the plan of FIG. 46, with the position of the rotary engines of the turbofan engine and the rotary wings of the composite profile in the horizontal flight mode;

in FIG. 48 - in the vertical take-off, hover and landing mode, an airplane layout with a shortened or vertical take-off and landing in plan with a cigar-shaped fuselage shape, with two rotary turbofan turbofan engines with a contour degree of more than 2, for example, turbofan engines with flow mixing, placed on horizontal consoles with a rotary platform for the possibility of joint rotation of two front turbofan engines and sections of the front rotary wings of a composite profile in the front days of the fuselage part and two rear turbofan turbofan engines with a contour degree of more than 2, for example, turbofan engines with flow mixing, placed on forward consoles in front of the toe of the side straight wings of the composite profile in the rear of the fuselage, while the socks of all wings of the composite profile with variable aerodynamic the characteristics are located in the alignment of the incoming flow of the outflowing jet from the turbofan engines of the turbofan engine, while the exhaust part l of all jet engines with a contour degree of more than 2 is located at a distance from the toe of the composite wing at a distance of not less than ΔL = C * max, where C * max is the maximum thickness of the wing, taking into account extended wings and fenders, while in vertical lift mode, hovering and landing resulting traction forces from turbofan turbofan engines are directed radially in three directions;

in FIG. 49 is a layout diagram of an airplane with a shortened or vertical take-off and landing in the plan of FIG. 49, with the position of the rotary engines of the turbofan engine and sections of the rotary wings of the composite profile in the horizontal flight mode;

in FIG. 50 - in the vertical take-off, hover and landing mode, the layout diagram of an aircraft with a shortened or vertical take-off and landing in plan with a cigar-shaped fuselage shape, with four turbofan engines with four turbofan engines with a degree of contour of more than 2, for example, turbofan engines with a mixture of flows placed on forward consoles in front of the toe of the rotary wings of a composite profile with variable aerodynamic characteristics, and one twin-circuit turbojet engine A turbofan engine with a contour degree of more than 2, for example, a turbofan engine with flow mixing, located in the tail of the fuselage, while behind the engine of the turbofan engine in the rear of the fuselage there is a trapezoidal wing of a composite profile, while the socks of all wings of a composite profile with variable aerodynamic characteristics are located in the alignment the flow of a flowing jet from turbofan turbofan engines, while the exhaust part of the nozzles of all turbofan jet engines with a degree of contour its 2 is located at a distance from the toe of the composite wing at a distance of not less than ΔL = C * max, where C * max is the maximum thickness of the wing, taking into account extended wings and fenders, while the rotary wings of the composite profile are rotated on the rotary segments made at the edge sections rotary wings of a composite profile and fixed in the rear to the fuselage, while in the vertical lift, hover and landing mode, the resulting traction forces from the turbofan turbofan engines are directed radially in directions;

in FIG. 51 is a layout diagram of an airplane with a shortened or vertical take-off and landing in the plan of FIG. 50, with the position of the rotary engines of the turbofan engine and the rotary wings of the composite profile in the transition from hovering to horizontal flight;

in FIG. 52 is a layout diagram of an airplane with a shortened or vertical take-off and landing in the plan of FIG. 52, with the position of the rotary engines of the turbofan engine and the rotary wings of the composite profile in the horizontal flight mode;

in FIG. 53 - in the mode of vertical take-off, hovering and landing, the layout diagram of an aircraft with a shortened or vertical take-off and landing in plan with a disk-shaped fuselage shape, with three rotary turbofan turbofan engines with a contour degree of more than 2, for example, turbofan engines with flow mixing, placed on annular horizontal support rails for the possibility of joint rotation of the turbofan engine and sections of the rotary wings of the composite profile around the vertical axis, at socks of all sections of the rotary wings of a composite profile with variable aerodynamic characteristics are located in the alignment of the incoming flow of a flowing jet from turbofan jet engines, while the exhaust part of the nozzles of all jet engines of a turbofan engine with a degree of contour more than 2 is located at a distance from the toe of the composite wing at a distance of not less than than ΔL = C * max, where С * max is the maximum thickness of the wing, taking into account extended wings and wing flaps, while in vertical lifting, hovering and landing cut light traction forces from turbofan turbofan engines are directed radially in three directions;

in FIG. 54 is a layout diagram of an airplane with a shortened or vertical take-off and landing in the plan of FIG. 53, with the position of the rotary engines of the turbofan engine and sections of the rotary wings of the composite profile in the horizontal flight mode,

in FIG. 55 is a section C1.1-C1.1, a diagram of a free flow blowing of a flowing jet from a turbofan engine with a rear location of the screws of the transformable profile of the wing of the aircraft with extended slotted flaps and with an extended wing liner located in front of the wing of the composite profile at the time of the plane's separation from the ground is shown the size of the chord of the elytra being ejected is 0.3 of the size of the chord of the entire wing, while the profile of the elytra is made in the form of a concave-convex segment profile, while the main wing profile, with extended wing liner, has a streamlined profile;

in FIG. 56 is a section C1.2-C1.2, shows a diagram of a free flow blowing out of a flowing jet from a turbofan engine with a rear location of the screws of the transformable profile of the wing of the aircraft with a deflected flap and with an extended wing liner located in front of the wing of the composite profile at the time of acceleration of the aircraft and set height, the chord size of the elytra being ejected is 0.3 of the size of the chord of the entire wing, while the wing profile is made in the form of a concave-convex segment profile, while the main wing profile, p nadkrylke extended and has a streamlined profile;

in FIG. 57 is a section C1.3-C1.3; there is shown a diagram of a free-stream blowing out of a flowing jet from a turbofan engine with a rear arrangement of screws of the transformable profile of the wing of the aircraft of FIG. 55, 56 in the horizontal cruise flight mode;

in FIG. 58 is a section C1.2-C1.2, shows a diagram of a free flow blowing out of a flowing jet from a turbofan engine with a rear arrangement of screws of the transformable profile of the wing of the aircraft with extended slotted flaps and with extended wing flaps located in the front and rear of the main wing profile at the time of separation from the ground, while the size of the chord of the elytra is equal to 0.2 of the chord of the entire wing, while the front profile of the wing is made in the form of a concave-convex segment profile, and the rear ofil nadkrylka configured as a bi-convex profile of the segment, with the main wing profile when nominated nadkrylkah has a streamlined profile;

in FIG. 59 is a section C2.2-C2.2, shows a diagram of a free flow blowing out of a flowing jet from a turbofan engine with a rear location of the screws of the transformable profile of the wing of the aircraft with a deflected flap and with extended wing flaps located in the front and rear of the main profile of the wing at the time of acceleration and climb, while the chord size of the elytra wings is 0.2 of the chord size of the entire wing, while the front profile of the wing panel is made in the form of a concave-convex segment profile, and the rear side the wing liner is made in the form of a biconvex segment profile, while the main wing profile, with the wing liners extended, has a streamlined profile;

in FIG. 60 is a section C3.2-C3.2, a diagram of a free-stream blowing out of a flowing jet from a turbofan engine with a rear arrangement of screws of the transformable profile of the wing of the aircraft of FIG. 58, 59 in the horizontal cruise flight mode;

in FIG. 61 is a section C1.3-C1.3, a diagram of a free-stream blowing out of a flowing jet from a turbofan engine with a rear arrangement of screws of a transformable wing profile of an airplane with extended slotted flaps and with extended wing flaps located in the front and rear of the main wing profile at the time of separation is shown the plane from the ground, while the chord size of the elytra is equal to 0.2 of the chord of the entire wing, while the front profile of the wing is made in the form of a concave-convex segment profile, and the rear the wing profile is made in the form of a biconvex segment profile, while the front wing wing is extended to a greater height than the rear wing, while the main wing profile with the wing wings extended has a streamlined profile;

in FIG. 62 is a section C2.3-C2.3, a diagram of a free-stream blowing out of a flowing jet from a turbofan engine with a rear location of the screws of the transformable profile of the wing of the aircraft with a deflected flap and with extended wing flaps located in the front and tail of the main profile of the wing at the time of acceleration and climb, the size of the chord of the elytra being ejected is 0.2 of the size of the chord of the entire wing, while the front profile of the elytra is made in the form of a concave-convex segment profile, and the rear ofil elytron is made in the form of a biconvex segmented profile, while the front elytra is extended to a greater height than the rear, while the main wing profile, with extended elytra, has a streamlined profile;

in FIG. 63 is a section С3.3-С3.З, there is shown a diagram of a free-stream blowing out of a flowing jet from a turbofan engine with a rear arrangement of screws of the transformable profile of the wing of the aircraft of FIG. 61, 62 in the horizontal cruise flight mode;

in FIG. 64 is a section C1.4-C1.4, shows a diagram of a free-stream blowing out of a flowing jet from a turbofan engine with a rear location of the screws of the transformable profile of the wing of the aircraft with extended slotted flaps and with an extended wing liner located in the front of the wing and the extended wing liner located in the rear of the main the wing profile, at the time of the plane’s takeoff from the ground, while the chord size of the ejected wing liner and the wing liner is 0.3 of the size of the chord of the entire wing, while the wing profile is made in e concavo-convex profile of the segment, the profile with the fender liner is formed as a bi-convex profile of the segment, with the main wing profile, and when extended nadkrylke fender liner has a streamlined profile;

in FIG. 65 is a section C2.4-C2.4, shows a diagram of a free flow blowing out of a turbo-fan engine with a rear location of the screws of the transformable profile of the wing of the aircraft with a deflected flap and with an extended wing liner located in the front of the wing and the extended wing liner located in the rear of the main profile wing at the time of acceleration of the aircraft and climb, while the size of the chord of the extended wing liner and the wing liner is 0.3 of the size of the chord of the entire wing, while the wing profile is made in the form ognuto convex profile of the segment, the slat profile is designed as a bi-convex profile of the segment, with the main wing profile, and when extended nadkrylke fender liner has a streamlined profile;

in FIG. 66 is a section C3.4-C3.4, a diagram of a free-stream blowing out of a flowing jet from a turbofan engine with a rear arrangement of screws of the transformable profile of the wing of the aircraft of FIG. 64, 65 in the horizontal cruise flight mode;

in FIG. 67 is a section C1.5-C1.5, shows a diagram of a free flow blowing outflow of a jet from a turbofan engine with a rear location of the screws of the transformable profile of the wing of the aircraft with extended slotted flaps and with an extended wing liner located in the front of the wing and extended wing liner located in the rear of the main the wing profile at the time of the plane’s takeoff from the ground, while the chord size of the elyser and wing flap is 0.2 of the size of the chord of the entire wing, while the wing profile is e concave-convex segment profile, while the wing profile is made in the form of a biconvex segment profile, while the main wing profile, with the extended wing liner and wing liner, has a streamlined profile;

in FIG. 68 is a section C2.5-C2.5, a diagram of a free-stream blowing out of a flowing jet from a turbofan engine with a rear arrangement of screws of a transformable profile of an airplane wing with a deflected flap and with an extended wing liner located in the front part of the wing and with an extended wing liner located in the rear of the main the wing profile at the time of acceleration of the aircraft and climb, the size of the chord of the elyser and the wing liner being 0.2 of the size of the chord of the entire wing, while the wing profile is made in the form concavo-convex profile of the segment, the profile with the fender liner is formed as a bi-convex profile of the segment, with the main wing profile, and when extended nadkrylke fender liner has a streamlined profile;

in FIG. 69 is a section C3.5-C3.5, a diagram of a free-stream blowing out of a flowing jet from a turbofan engine with a rear location of the screws of the transformable profile of the wing of the aircraft of FIG. 67, 68 in the horizontal cruise flight mode;

in FIG. 70 is a section C1.6-C1.6, a diagram of a free flow blowing out of a flowing jet from a turbofan engine with a rear arrangement of screws of the transformable wing profile of the aircraft with extended slotted flaps and with two extended wing flaps located in the front and rear of the main wing profile and extended wing liner located in the rear part of the main wing profile at the time of the plane’s takeoff from the ground, while the chord size of the elytra wing and wing liner is 0.2 of the size of the entire wing chord, etc. the profile of the front wing liner is made in the form of a concave-convex segment profile, and the rear profile of the wing liner is made in the form of a biconvex segment profile, while the wing profile is made in the form of a biconvex segment profile, while the main wing profile, with the wing liners and the wing liner extended has a streamlined profile;

in FIG. 71 is a section C2.6-C2.6, a diagram of a free flow blowing out of a flowing jet from a turbofan engine with a rear location of the screws of the transformable wing profile of the aircraft with a deflected flap and with two extended wing flaps located in the front and rear of the main wing profile and the extended wing flap located in the tail section of the main wing profile at the time of acceleration of the aircraft and climb, while the size of the chord of the elyers and the wing liner is 0.2 of the size of the chord of the entire wing, when The profile of the front wing liner is made in the form of a concave-convex segment profile, and the rear profile of the wing liner is made in the form of a biconvex segment profile, while the wing profile is made in the form of a biconvex segment profile, while the main wing profile, with the wing liners and the wing liner extended has a streamlined profile;

in FIG. 72 is a section C3.6-C3.6, a diagram of a free-stream blowing out of a flowing jet from a turbofan engine with a rear arrangement of screws of the transformable profile of the wing of the aircraft of FIG. 70, 71 in the horizontal cruise flight mode;

in FIG. 73 is a section C1.7-C1.7, there is shown a diagram of a free flow blowing out of a flowing jet from a turbofan engine with a rear arrangement of screws of a transformable wing profile of an airplane with extended slotted flaps and with two extended wing flaps located in the front and rear of the main wing profile and extended wing liner located in the rear part of the main wing profile at the time of the plane’s separation from the ground, while the chord size of the elytra wings is 0.2 of the size of the chord of the entire wing, with this size the chisels of the ejected wing liner is 0.3 of the size of the chord of the entire wing; the profile of the front wing liner is in the form of a concave-convex segment profile, and the rear profile of the wing liner is made in the form of a biconvex segment profile, while the wing profile is made in the form of a biconvex segment profile, while the front wing liner is extended to a greater height than the rear, while the main wing profile, with the wing liners and the wing liner extended, has a streamlined profile;

in FIG. 74 is a section C2.7-C2.7, a diagram of a free-stream blowing of a flowing jet from a turbofan engine with a rear arrangement of screws of a transformable wing profile of an aircraft with a deflected flap and with two extended wing flaps located in the front and rear of the main wing profile and with an extended wing flap located in the rear of the main wing profile at the time of acceleration of the aircraft and climb, while the size of the chord of the elytra is 0.2 of the size of the chord of the entire wing, while the chisels of the ejected wing liner is 0.3 of the size of the chord of the entire wing; the profile of the front wing liner is in the form of a concave-convex segment profile, and the rear profile of the wing liner is made in the form of a biconvex segment profile, while the wing profile is made in the form of a biconvex segment profile, while the front wing liner is extended to a greater height than the rear, while the main wing profile, with the wing liners and the wing liner extended, has a streamlined profile;

in FIG. 75 is a section C3.7-C3.7, a diagram of a free-stream blowing out of a flowing jet from a turbofan engine with a rear arrangement of screws of the transformable profile of the wing of the aircraft of FIG. 73, 74 in the horizontal cruise flight mode;

in FIG. 76 - in the mode of vertical take-off, hovering and landing, the layout diagram of an aircraft with a shortened or vertical take-off and landing in plan with a disco-shaped fuselage shape, with three rotary turbofan engines with a rear screw arrangement (TVVD), placed on the annular horizontal support rails for the possibility of joint rotation of the fuel injection engine and sections of the rotary wings of the composite profile around the vertical axis, while the socks of all sections of the rotary wings of the composite profile with aerodynamic characteristics are located in the alignment of the flowing stream of the exhaust jet from the fuel engines, while in the vertical lift, hover and landing mode, the resulting traction forces from turbofan engines with a rear screw arrangement are directed radially in three directions;

on Fig - layout diagram of an airplane with a shortened or vertical take-off and landing in the plan of Fig. 76, with the position of the rotary engines of the fuel injection engine and sections of the rotary wings of the composite profile in the horizontal flight mode;

on Fig - in the mode of vertical take-off, hovering and landing shows the layout of the aircraft with a shortened or vertical take-off and landing in plan with a cigar-shaped fuselage, with three rotary turbofan engines with a rear arrangement of propellers (TVVD) placed on the horizontal horizontal support guides for the possibility of joint rotation of the fuel injection engine and sections of the rotary wings of the composite profile around the vertical axis, while the socks of all sections of the rotary wings of the composite profile with interchangeable aerodynamic characteristics are located in the alignment of the flowing stream of the exhaust jet from the fuel engines, while in the vertical lift, hover and landing mode, the resulting traction forces from turbofan engines with rear screw arrangement are directed radially in three directions;

in FIG. 79 is a layout diagram of an airplane with a shortened or vertical take-off and landing in the plan of FIG. 78, with the position of the rotary engines of the fuel injection engine and sections of the rotary wings of the composite profile in the horizontal flight mode;

in FIG. 80 - in the mode of vertical take-off, hovering and landing, the layout diagram of the aircraft is shown with a shortened or vertical take-off and landing in plan with a disk-shaped fuselage, with three rotary turbofan engines with a rear arrangement of propellers (TVVD) placed on the ring horizontal support rotary platforms for the possibility of joint rotation of the fuel injection engine and sections of the rotary wings of the composite profile around the vertical axis, while the socks of all sections of the rotary wings of the composite profile with zmenyaemymi aerodynamic arranged in an alignment of the incident flow of the outflowing jet engines TVVD, wherein a vertical lifting mode, hovering and landing resulting from traction motors turbvintoventilyatornyh with rear screws oriented radially in three directions;

in FIG. 81 is a layout diagram of an airplane with a shortened or vertical take-off and landing in the plan of FIG. 80, with the position of the rotary engines of the fuel injection engine and sections of the rotary wings of the composite profile in the horizontal flight mode;

in FIG. 82 - in the mode of vertical take-off, hovering and landing, the layout diagram of the aircraft is shown with a shortened or vertical take-off and landing in plan with a cigar-shaped fuselage, with two rotary turbofan engines with a rear arrangement of propellers (TVVD) placed on the ring horizontal supporting rotary platforms in the front part of the fuselage for the possibility of joint rotation of the fuel injection engine and sections of the rotary wings of the composite profile around the vertical axis and one turbofan engine and with a rear arrangement of propellers (TVVD) located in the rear of the fuselage, while the socks of all sections of the rotary wings of the composite profile with variable aerodynamic characteristics and the tail straight wing of the composite profile are located in the alignment of the flow of the outflowing jet from the engines of the fuel engine, in the vertical mode lifting, hovering and landing resulting traction forces from three turbofan engines with rear propellers are directed radially in three directions;

in FIG. 83 is a layout diagram of an airplane with a shortened or vertical take-off and landing in the plan of FIG. 82, with the position of the rotary engines of the fuel injection engine and sections of the rotary wings of the composite profile in the horizontal flight mode;

in FIG. 84 - in the mode of vertical take-off, hovering and landing, the layout diagram of an aircraft with a shortened or vertical take-off and landing in plan with a cigar-shaped fuselage, with two rotary turbofan engines with a rear screw arrangement (TVVD) located on the ring horizontal support rotary platforms in the front of the fuselage for the possibility of joint rotation of the high-pressure fuel pump and sections of the rotary wings of the composite profile around the vertical axis and with two rear turbofan with rear-mounted propeller engines (TWF) located in front of the toe of the side straight wings of the composite profile in the rear of the fuselage, while the socks of all sections of the rotary wings of the composite profile and the tail straight wing of the composite profile with variable aerodynamic characteristics are located in the alignment of the incoming flow of the outgoing jet from the engines TVVD, while in the mode of vertical lifting, hovering and landing, the resulting traction forces from four turbofan engines with a rear by laying screws directed radially in three directions;

in FIG. 85 is a layout diagram of an airplane with a shortened or vertical take-off and landing in the plan of FIG. 84, with the position of the rotary engines of the fuel injection engine and sections of the rotary wings of the composite profile in the horizontal flight mode.

In the drawings, the positions indicated:

pos. 1 - the main profile of the composite wing;

pos. 2 - extendable front wing liner with a chord length of 0.2 of the size of the chord of the entire wing;

pos. 3 - extendable front wing liner with a chord length of 0.3 of the size of the chord of the entire wing;

pos. 4 - extendable rear wing liner with a chord length of 0.2 of the size of the chord of the entire wing;

pos. 5 - a retractable rear wing liner with a chord length of 0.2 of the size of the chord of the entire wing;

pos. 6 - extendable rear wing liner with a chord length of 0.3 of the size of the chord of the entire wing;

pos. 7 - flap;

pos. 8 - slat;

pos. 9 - turbofan turbofan engine with a degree of contour more than 2, for example a turbofan engine with flow mixing;

pos. 10 - cigar-shaped fuselage;

pos. 11 - side straight wing of a composite profile;

pos. 12 - side swept wing of a composite profile;

pos. 13-trapezoidal tail wing of a composite profile;

pos. 14 - rotary wing of a composite profile;

pos. 15 -carrier horizontal console for mounting a turbofan engine;

pos. 16 - remote horizontal console in front of the toe of the composite wing for mounting the turbofan engine;

pos. 17 - supporting horizontal console with a rotary platform for the possibility of rotation of the turbofan engine around a vertical axis;

pos. 18 - air intake channel for the tail turbofan;

pos. 19 - slotted streamlined air intake;

pos. 20 - tail unit;

pos. 21 - a rotary segment;

pos. 22 - wing of the front stabilizer;

pos. 23 - annular horizontal support rails;

pos. 24 - fuselage disk-shaped, or streamlined volume of a circular shape in plan;

pos. 25 - turbofan engine (TVVD) with rear screw arrangement;

pos. 26 - tail straight wing of the composite profile;

ΔL is the distance between the exhaust part of the nozzle of turbofan jet engines with a degree of contour greater than 2 and the wing tip of the composite profile located in the alignment of the incoming flow of the exhaust jet from the turbofan engine;

ΔNkd - offset of the nozzle axis of a turbofan engine with a contour degree of more than 2, or a turbofan engine (HPH) with a rear arrangement of screws relative to the horizontal of the composite profile passing through the nose of the wing.

Claims (8)

1. Aircraft comprising a fuselage, a multiple engine propulsion system, a control cabin, an integral control system, composite wings containing the main wing profile and additional extendable profile elements, while in the horizontal cruise flight mode the main wing profile and additional profile elements form a single streamlined wing profile, characterized in that the engines are made of turbofan dual-circuit (turbofan) with a degree of contour more than 2, while the composite wings are located in areas of the flowing stream of the outflowing jet from the turbofan engines with a contour degree of more than 2, while the additional extendable wing profile elements are made either in the form of one or more wing liners extended over the upper surface of the main wing profile, or in the form of one or more wing liners extended under the lower surface the main wing profile, or together in the form of one or more elytra and wing flaps, while the wing profile is made in the form of a plano-convex or concave-convex seg profile, while the profile of the wing flaps is made in the form of a plano-convex or biconvex segment profile, while the main profile of the wing with extended wings and wing flaps has a streamlined profile shape, while the flow of a flowing stream from the nozzles of the nozzles of one or more turbojet engines with a degree of contour more than 2 occurs on the upper and lower surfaces of the main wing profile and additional extendable wing profile elements, while the exhaust part of the nozzle of one or more of engines of a turbofan engine with a contour degree of more than 2 is located at a distance from the toe of the composite wing at a distance of not less than ΔL = C * max, where C * max is the maximum thickness of the composite wing profile in the vertical plane along the axis of the jet engine, taking into account the extended fenders and fenders. 2. The aircraft under item 1, characterized in that the additional retractable profile elements in the extended position have the ability to rotate to change the angle of attack. 3. An airplane comprising a fuselage, a multiple engine propulsion system, a control cabin, an integral control system, composite wings containing the main wing profile and additional extendable profile elements, while in the horizontal cruise flight mode the main wing profile, flaps and additional profile elements form a single streamlined wing profile, characterized in that the engines are double-thrust turbofan engines with a degree of contour more than 2, while the composite wings are located in the region n the outflowing stream of the outflowing jet from the engines of the turbofan engine with a contour degree of more than 2, while the additional retractable wing profile elements are made either in the form of one or more wing liners extended over the upper surface of the main wing profile, or in the form of one or more wing liners extended under the lower surface of the main wing profile, or together in the form of one or more elytra and wing liners, while the profile of one or more elytra is made in the form of a convex or concave convex segment profile, while the profile of one or more of the wing flaps is made in the form of a flat convex or biconvex segment profile, while the main wing profile with extended wings and wing flaps has a streamlined profile shape, while the flow of the outflowing jet from the nozzles of one or more turbofan engines a degree of contour of more than 2 occurs along the upper and lower surfaces of the main wing profile and additional extendable wing profile elements, while the exhaust h part of the nozzle of one or several engines of a turbofan engine with a degree of contour greater than 2 is located at a distance from the toe of the composite wing at a distance of not less than ΔL = C * max, where C * max is the maximum thickness of the composite wing profile in the vertical plane along the axis of the jet engine, taking into account extended wing flaps and wing flaps, while for the possibility of creating a stable total balanced power reactive moment relative to the center of gravity of the aircraft in the vertical lift, hover and landing mode, resulting traction efforts from single or groups of turbofan engines with a degree of contour more than 2 are directed in at least three directions. 4. Aircraft under item 3, characterized in that the additional retractable profile elements in the extended position have the ability to rotate to change the angle of attack. 5. Aircraft, including the fuselage, a power plant with propeller, or turboprop, or turbofan engines, a control cabin, an integral control system, composite wings containing the main wing profile and additional extendable profile elements, while in the horizontal cruising flight mode the main wing profile and additional profile elements form a single streamlined wing profile, characterized in that the composite wings are located in the region of the incoming flow of the flowing stream and from rotor motors, or turboprops, or turbofan engines, while the free-flowing flow of the outflowing jet from rotor motors, or turboprops, or turboprop engines occurs along the upper and lower surfaces of the main wing profile and additional extendable wing profile elements, with additional extendable wing profile elements made either in the form of one or more elytra, extended over the upper surface of the main wing profile, or in the form of one th or several wing flaps extended under the lower surface of the main wing profile, or together in the form of one or several wing flaps and wing flaps, the wing profile is made in the form of a plano-convex or concave-convex segment profile, while the profile of the wing flaps is made in the form of a plano-convex or biconvex segment profile, while the main profile of the wing with extended fenders and fenders has a streamlined profile shape. 6. The aircraft under item 5, characterized in that the additional retractable profile elements in the extended position have the ability to rotate to change the angle of attack. 7. Aircraft, including the fuselage, a power plant with propeller, or turboprop, or turbofan engines, a control cabin, an integral control system, composite wings containing the main wing profile and additional extendable profile elements, while in the horizontal cruise flight mode, the main wing profile and additional profile elements form a single streamlined wing profile, characterized in that the composite wings are located in the region of the incoming flow of the flowing stream and from rotor motors, or turboprops, or turbofan engines, while the free-flowing flow of the outflowing jet from rotor motors, or turboprops, or turboprop engines occurs along the upper and lower surfaces of the main wing profile and additional extendable wing profile elements, with additional extendable wing profile elements made either in the form of one or more elytra, extended over the upper surface of the main wing profile, or in the form of one of one or several wing flaps extended under the lower surface of the main wing profile, or together in the form of one or several wing flaps and wing flaps, the profile of one or several wing flaps made in the form of a plano-convex or concave-convex segment profile, while the profile of one or more wing flaps is made in the form of a plano-convex or biconvex segment profile, while the main wing profile with extended wings and wing liners has a streamlined profile shape, while for possible creating a stable total balanced power reactive moment relative to the center of gravity of the aircraft in the vertical lift, hover and landing mode, the resulting traction forces from single or groups of rotor engines, or turboprops, or turboprops are directed in at least three directions. 8. Aircraft according to claim 7, characterized in that the additional retractable profile elements in the extended position have the ability to rotate to change the attack angle.

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