RU2694478C1 - Wing with variable aerodynamic characteristics and aircraft (versions) - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aircraft engineering. Aircraft wing with variable aerodynamic characteristics includes main wing profile and additional extended wing shaped elements, which are made in form of rams and / or in the form of extendable under wing. In the extended position the distance between the main wing profile and the ram is not less than 0.5Ci (maximum thickness of the main profile). Said rams extend under main wing profile backward and downward. In the extended position the distance between the main wing profile and the underwing fender is not less than 0.5Ci. When the rams are extended, the lap value between the main wing flap and the ram tail part is Ci. With the extended wing position extended, the lap value between the toe wing tip and the main wing tail is Ci. Value of overlap between tip of second wing rake and tail part of first wing trunk makes Ci. Extendable shaped elements of wing in extended position to change angle of attack can turn about longitudinal axis. Versions of aircraft are characterized by wing shape and location of engines.

EFFECT: group of inventions is aimed at improvement of aerodynamic characteristics of aircraft wing.

3 cl, 95 dwg

Description

The invention relates to the field of aviation, namely, devices designed to change the aerodynamic characteristics of the wing of the aircraft and can be used for aircraft of various types.

Known design study S.A. Chaplygin (“The Theory of the Lattice Wing”, Selected Works on the Theory of the Wing., Leningrad, State Publishing House of Technical and Theoretical Literature, 1949), which proved that the lifting force of the wing of the multi-wing wing included in the composition considerably exceeds the lifting force of a similar separate wing . A well-known study of the multi-cut wing S.А. Chaplygin ("Experimental Aerodynamics", Martynov AK, State. Publishing House of Defense Industry., 1949, see Fig. 8.56, p. 312), which contains data on a significant increase in the lifting force of a multi-wing wing. The disadvantage of the above structures of the wing is high aerodynamic resistance during horizontal cruising flight mode. There is also known a method of changing the aerodynamic characteristics of an aircraft wing (RF patent N 2250859, OJSC “Central Committee of FPG“ Russian Aviation Consortium ”, authors VV Artemyev, Kanukov M.I., Klimov V.T., and others, publ. 04/27/2005) that the wing is made of a composite of small and large elements of a close profile, while in the retracted position a single profile is formed of both elements, and when released, a small element is moved away from the large profile to increase the thickness of the composite wing, at the same time a small element is diverted from large th profile equidistant, and the ratio of the areas of large and small profile of the composite wing is chosen to be 1: 0.3. It is also known the technical solution of the aircraft, (RF patent N 2670161, author Soushentsev B.N., publication 10/18/018), including the fuselage, the power plant of several engines, composite wings containing the main wing profile and additional retractable profile elements of the wing eaves and vodkrylkov, with the horizontal cruise mode of flight, the main profile of the wing and additional pull-out elements form a single streamlined profile of the wing, while the flow past the flow of the outflowing jet of engines with p zlichnyh flight regimes occurs at the upper and lower surfaces of the main and additional airfoil profile put forward wing elements. This decision was made as a prototype. The disadvantages of this technical solution include the lack of an optimal scheme for the nomination of additional extended profile elements of the composite wing. The purpose of this invention is to optimize the design of the nomination of additional retractable e-fenders and wing flaps of the transformed multi-wing wing to improve the aerodynamic characteristics of the wing of the aircraft in various flight modes of the aircraft associated with takeoff, acceleration, climb, descent, maneuvering and landing. This goal is achieved by performing an aircraft wing with variable aerodynamic characteristics, including the main wing profile and additional retractable wing profile elements, while the additional retractable wing wing elements are made in the form of one or several wing wings retractable above the upper surface of the wing wing profile, or in one either several wing flaps nominated under the lower surface of the main wing profile, either simultaneously as one or several Some wing flaps extended above the upper surface of the main wing profile and one or several wing flaps extended below the lower surface of the wing main profile, while in the horizontal cruising flight mode the main wing profile and additional profile elements form a single streamlined wing profile, while apparatus associated with take-off, acceleration, climb, descent, maneuvering and landing to change the aerodynamic characteristics of the wing At the same time, in the extended position, the distance ΔHn between the main wing profile and the wing ejector, or between the extended wing wings is at least 0.5Ci (where Ci is the maximum thickness of the main wing in the vertical plane of flow), while the retractable wing flaps retract under the main wing profile back and down, while in the extended position, the distance ΔHn between the main wing profile and the wing liner, or between the extended wing liner and is not less than 0.5Ci, while with the e-wing position extended, the amount of overlap Δ Ln between the nose of the main wing and the tail portion of the e-fender is not less than Ci, while with the wing flaps extended, the amount of overlap Δ Ln between the tip of the wing-liner and the tail part of the main wing, is not less than Ci, while the amount of overlap Δ Ln between the toe of the second fender liner and the tail part of the first fender liner is at least Ci, while the retractable wing profile elements, in the extended position, to change the angle of attack, hav e the ability to rotate about the longitudinal axis. This goal is achieved for an aircraft (option 1) which includes the fuselage, power plant with propeller-powered, or turboprop, or turboprop-fan, or twin-turbojet engines, with a degree of unbalance of more than 2 engines, a control cabin, an integral control system, composite wings, containing the main wing profile and additional extended profile elements, while in the horizontal cruise mode of flight the main wing profile and additional profile elements form a single streamlined n the wing profile, while the composite wings are located in the area of the incident flow of the outgoing jet from the propeller or turboprop or turboprop-fan engines, while the oncoming flow around the outflow jet from the propeller-motor, or turboprop, or turboprop-fan, or turbojet-powered dual-contour, or turboprop, or turboprop-fan, or turbojet-powered dual-contour, or turboprop, or turboprop-fan, or turbojet, are two-contour, or turboprop, or turboprop-fan, or turbojet-powered dual-projectile, or turboprop, or turboprop-fan, or turbojet-powered dual-projectile, or turboprop, or turboprop-fan, or turbojet, two-contour, turbo-screw, or turboprop-fan, or turbojet, two-contour, turbo-screw, or turboprop-fan, or turbojet-powered two-motion, turboprop engines, or turboprop-fan, or turbojet, or dual-turbofan, turboprop engines more than 2, the engines occur along the upper and lower surfaces of the main wing profile and additional extended wing profile elements, with additional advances Wing profile elements of the wing are made either in the form of one or several e-fins extended above the upper surface of the main wing profile, or in the form of one or more fenders under the lower surface of the main section of the wing, or jointly in the form of one or more fenders and fenders, at various flight modes of the aircraft associated with take-off, acceleration, climb, descent, maneuvering and landing for optimal changes in the aerodynamic characteristics of the wing the extended device extends over the main wing profile forward and up, while in the extended position the distance ΔHn between the main wing profile and the wing ejector, or between the extended wing ejector plates is at least 0.5Ci, while the retractable wing flaps slide back under the main wing profile and down, while in the extended position, the distance ΔHn between the main wing profile and the fender liner, or between the extended fender flaps is at least 0.5Ci, while at the extended position of the fender flaps, Lesta Δ Ln between the toe of the main wing and the tail part of the e-fender is not less than Ci, while with the wing flaps extended, the amount of overlap Δ Ln between the toe of the fender liner and the tail part of the main wing is not less than Ci, and the amount of overlap Δ Ln between the toe of the second fender and the tail part of the first fender liner is not less than Ci, while the retractable wing profile elements, in the extended position to change the angle of attack, have the ability to rotate around the longitudinal axis.

This goal is achieved for an aircraft (option 2) which includes the fuselage, a power plant with propeller-driven, or turboprop, or turboprop-fan, or twin-turbojet engines, with a degree of unbalance of more than 2 engines, a control cabin, an integral control system, composite wings, containing the main wing profile and additional extended profile elements, while in the horizontal cruise mode of flight the main wing profile and additional profile elements form a single streamlined n the wing profile, while the composite wings are located in the area of the incident flow of the outgoing jet from the propeller or turboprop or turboprop-fan engines, while the oncoming flow around the outflow jet from the propeller-motor, or turboprop, or turboprop-fan, or turbojet-powered dual-contour, or turboprop, or turboprop-fan, or turbojet-powered dual-contour, or turboprop, or turboprop-fan, or turbojet, are two-contour, or turboprop, or turboprop-fan, or turbojet-powered dual-projectile, or turboprop, or turboprop-fan, or turbojet-powered dual-projectile, or turboprop, or turboprop-fan, or turbojet, two-contour, turbo-screw, or turboprop-fan, or turbojet, two-contour, turbo-screw, or turboprop-fan, or turbojet-powered two-motion, turboprop engines, or turboprop-fan, or turbojet, or dual-turbofan, turboprop engines more than 2, the engines occur along the upper and lower surfaces of the main wing profile and additional extended wing profile elements, with additional advances Wing profile elements of the wing are made either in the form of one or several e-fins extended above the upper surface of the main wing profile, or in the form of one or more fenders under the lower surface of the main section of the wing, or jointly in the form of one or more fenders and fenders, at various flight modes of the aircraft associated with take-off, acceleration, climb, descent, maneuvering and landing for optimal changes in the aerodynamic characteristics of the wing the extended device extends over the main wing profile forward and up, while in the extended position the distance ΔHn between the main wing profile and the wing ejector, or between the extended wing ejector plates is at least 0.5Ci, while the retractable wing flaps slide back under the main wing profile and down, while in the extended position, the distance ΔHn between the main wing profile and the fender liner, or between the extended fender flaps is at least 0.5Ci, while at the extended position of the fender flaps, Lesta Δ Ln between the toe of the main wing and the tail part of the e-fender is not less than Ci, while with the wing flaps extended, the amount of overlap Δ Ln between the toe of the fender liner and the tail part of the main wing is not less than Ci, and the amount of overlap Δ Ln between the toe of the second fender and the tail part of the first fender liner is not less than Ci, while the extended wing profile elements, in the extended position, to change the angle of attack, have the ability to rotate around the longitudinal axis, while stable total balanced power reactive moment relative to the center of gravity of the aircraft in the mode of vertical lifting, lagging and landing; three directions.

The illustrative examples of the present invention show versions of a transformable wing of an aircraft:

in fig. 1 - section A1.1-A1.1, shows a scheme for blowing a transformed composite wing profile of an aircraft by an incoming flow of atmospheric air in cruise flight mode, including the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, with all the elements of the wing pos. 1, 4, 5, 6, are in the folded position;

in fig. 2 - section A1.2-A1.2, shows a scheme for blowing the transformed composite profile of an airplane wing by an incoming flow of atmospheric air in the climb mode, which includes the main wing profile of pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, while in the rotated position is a rotary flap pos. 4, and the flap pos. five;

in fig. 3 - section A1.3-A1.3, shows a scheme for blowing a transformed composite wing profile of an aircraft by an incoming flow of atmospheric air in the mode of take-off or deceleration, including the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, while in the rotated position is a rotary flap pos. 4, and the flap pos. 5, as well as in the extended position, the nodus is pos. 6; in fig. 4 - section A2.1-A2.1, shows a scheme for blowing the transformed composite profile of an airplane wing by an incoming flow of atmospheric air in cruise flight mode, including the main wing profile pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, with all the elements of the wing pos. 1, 4, 6 are in the folded position;

in fig. 5 - section A2.2-A2.2, shows a scheme for blowing a transformed composite wing profile of an aircraft by an incoming flow of atmospheric air in the mode of take-off or climb, including the main wing profile pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the flap pos. 4 and nadrylok pos. 6;

in fig. 6 - section A2.3-A2.3, shows a scheme for blowing a transformed composite wing profile of an aircraft by an incoming flow of atmospheric air in the mode of take-off, maneuvering or braking, including the main wing profile pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the noduck pos. 6, liner pos. 4, while the fender flap and liner have the ability to rotate around the longitudinal axis to change the angle of attack;

in fig. 7 - section А3.1-А3.1, a diagram of the blowing of a transformed composite wing profile of an airplane by an incoming flow of atmospheric air in cruise flight mode is shown, including the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, with all the elements of the wing pos. 1, 2, 3 are in the folded position;

in fig. 8 - section A3.2-A3.2, shows a scheme for blowing a transformed composite wing profile of an airplane by an incoming flow of atmospheric air in acceleration and climb mode, including the main wing profile of pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended paired position are the fenders pos. 2 and 3;

in fig. 9 - section A3.3-A3.3, shows a scheme for blowing a transformed composite wing profile of an aircraft by an incoming flow of atmospheric air in the mode of take-off or braking, including the main wing profile of pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3;

in fig. 10 - section A3.4-A3.4, shows a scheme for blowing a transformed composite wing profile of an airplane by an incoming flow of atmospheric air in the mode of take-off, maneuvering or braking, including the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, the second retractable liner asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3, while the fenders have the ability to rotate around the longitudinal axis to change the angle of attack;

in fig. 11 - section A4.1-A4.1, shows a scheme for blowing the transformed composite profile of an airplane wing by an incoming flow of atmospheric air in cruise flight mode, including the main wing profile of pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, with all the elements of the wing pos. 1, 2, 3, 6 are in the folded position;

in fig. 12 - section A4.2-A4.2, shows a scheme for blowing a transformed composite wing profile of an aircraft by an incoming flow of atmospheric air in the acceleration and climb regime, including the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended paired position are the fenders pos. 2 and 3, as well as in the extended position, is the noduck pos. 6;

in fig. 13 - section A4.3-A4.3, shows a scheme for blowing the transformed composite profile of an airplane wing by an incoming flow of atmospheric air in the mode of take-off or deceleration, including the main profile of the wing pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3, as well as in the extended position, is the noduck pos. 6;

in fig. 14 - section A4.4-A4.4, shows a scheme for blowing a transformed composite wing profile of an aircraft by an incoming flow of atmospheric air in the mode of take-off, maneuvering or braking, including the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, the second retractable liner asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3, while the fender flap have the ability to rotate around the longitudinal axis to change the angle of attack;

in fig. 15 - section B1.1-B1.1, shows a scheme for blowing a convertible composite profile of an airplane’s wing by a flowing stream of a stream from a double-circuit turbojet engine with a degree of contour more than 2, while the stream flowing around by a stream of stream from a turbojet engine pos. 7 occurs on the upper and lower surfaces of the main profile of the composite wing in cruise flight mode, while the composite wing includes the main profile of the wing pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, with all the elements of the wing pos. 1, 4, 5, 6, are in the folded position;

in fig. 16 is a section B1.2-B1.2; a diagram shows the blowing of a convertible composite profile of an airplane’s wing by the oncoming flow of a stream from a double-circuit turbojet engine with a degree of contour more than 2; the main profile of the composite wing and additional retractable elements of the composite wing in acceleration and climb mode, while the composite wing includes the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, while in the rotated position is a rotary flap pos. 4, and the flap pos. five;

in fig. 17 - section B1.3-B1.3, shows the flow pattern of the transformed composite airframe of the aircraft, the oncoming flow of a stream from a double-circuit turbojet engine with a degree of contour more than 2, while the flow of the stream flowing out of the turbojet engine occurs on the upper and lower surfaces the main profile of the composite wing and additional retractable elements of the composite wing in takeoff or braking mode, while the composite wing includes the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, while in the rotated position is a rotary flap pos. 4, and the flap pos. 5, as well as in the extended position, the nodus is pos. 6;

in fig. 18 is a section of B2.1-B2.1; a diagram shows the blowing of a convertible composite profile of an airplane’s wing by a flowing stream of a stream from a double-circuit turbojet engine with a degree of contour more than 2, while the flow of a stream flowing from a turbojet engine pos. 7 occurs on the upper and lower surfaces of the main profile of the composite wing in cruise flight mode, while the composite wing includes the main profile of the wing pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, with all the elements of the wing pos. 1, 4, 6 are in the folded position;

in fig. 19 - section B2.2-B2.2, shows a scheme for blowing a convertible composite profile of an airplane wing by a flowing stream of a stream from a double-circuit turbojet engine with a degree of contour more than 2, while the stream flowing around a stream of engines from the turbojet occurs along the upper and lower surfaces the main profile of the composite wing and additional retractable elements of the composite wing in the mode of take-off, acceleration and climb, while the composite wing includes the main wing profile pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the flap pos. 4 and nadrylok pos. 6;

in fig. 20 - section B2.3-B2.3, shows a scheme for blowing a convertible composite profile of an airplane’s wing by the oncoming flow of a stream from a double-circuit turbojet engine with a degree of contour more than 2, while the flow around the oncoming stream of the stream from the turbojet engine occurs along the upper and lower surfaces the main profile of the composite wing and additional retractable elements of the composite wing in takeoff or braking mode, while the composite wing includes the main wing profile pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the noduck pos. 6, liner pos. 4, while the fender flap and liner have the ability to rotate around the longitudinal axis to change the angle of attack;

in fig. 21 - section В3.1-В3.1, shows the scheme of blowing the convertible composite profile of an airplane wing by the oncoming flow of a stream from a double-circuit turbojet engine with a degree of contour more than 2, while the flow around the oncoming stream of a stream flowing from a turbojet engine pos. 7 occurs on the upper and lower surfaces of the main profile of the composite wing in cruise flight mode, while the composite wing includes the main profile of the wing pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, with all the elements of the wing pos. 1, 2, 3 are in the folded position;

in fig. 22 - section В3.2-В3.2, shows the scheme of blowing the convertible composite profile of an airplane wing by the oncoming flow of a stream from a double-circuit turbojet engine with a degree of contour more than 2, while the flow around the oncoming stream of the stream flowing from a turbojet engine occurs along the upper and lower surfaces the main profile of the composite wing and additional retractable elements of the composite wing in acceleration and climb mode, while the composite wing includes the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended paired position are the fenders pos. 2 and 3;

in fig. 23 is a section B3.3-B3.3; a diagram shows the blowing of a convertible composite profile of an airplane’s wing by the oncoming flow of a stream from a double-circuit turbojet engine with a degree of contour more than 2; the main profile of the composite wing and additional retractable elements of the composite wing in takeoff or braking mode, while the composite wing includes the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3;

in fig. 24 is a section B3.4-B3.4; a diagram shows the blowing of a convertible composite profile of an airplane’s wing by the oncoming flow of a stream from a double-circuit turbojet engine with a degree of contour more than 2; the main profile of the composite wing and additional retractable elements of the composite wing in takeoff or braking mode, while the composite wing includes the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3, while the fenders have the ability to rotate around the longitudinal axis to change the angle of attack;

in fig. 25 is a section B4.1-B4.1; a diagram shows the blowing of a convertible composite airframe of an aircraft with an incident stream of a stream from a double-circuit turbojet engine with a degree of contour more than 2, while the stream of stream flowing out of a turbojet engine pos. 7 occurs on the upper and lower surfaces of the main profile of the composite wing in cruise flight mode, while the composite wing includes the main profile of the wing pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, with all the elements of the wing pos. 1, 2, 3, 6 are in the folded position;

in fig. 26 is a section B4.2-B4.2; a diagram shows the blowing of a convertible composite airframe of an aircraft by the oncoming flow of a stream from a double-circuit turbojet engine with a degree of contour more than 2; the main profile of the composite wing and additional retractable elements of the composite wing in acceleration and climb mode, while the composite wing includes the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended paired position are the fenders pos. 2 and 3, as well as in the extended position, is the noduck pos. 6;

in fig. 27 is a section B4.3-B4.3; a diagram shows the blowing of a convertible composite profile of an airplane’s wing by the oncoming flow of a stream from a double-circuit turbojet engine with a degree of contour more than 2; the main profile of the composite wing and additional retractable elements of the composite wing in takeoff or braking mode, while the composite wing includes the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3, as well as in the extended position, is the noduck pos. 6;

in fig. 28 is a section B4.4-B4.4; a diagram shows the blowing of a convertible composite airframe of an aircraft by the oncoming flow of a stream from a double-circuit turbojet engine with a degree of contour more than 2; the main profile of the composite wing and additional extended elements of the composite wing in the mode of take-off, braking or maneuvering, while the composite wing includes the main profile of the wing Lake. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3, as well as in the extended position, is the noduck pos. 6, while the fenders and the fender have the ability to rotate around the longitudinal axis to change the angle of attack;

in fig. 29 is a section C1.1-C1.1; a diagram shows the blowing of a convertible composite wing profile of an aircraft by the oncoming flow of a jet stream from a turboprop-fan engine with tail arrangement of screws; the composite wing in cruise flight mode, while the composite wing includes the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, with all the elements of the wing pos. 1, 4, 5, 6, are in the folded position;

in fig. 30 is a section C1.2-C1.2; a diagram shows the blowing of a convertible composite wing profile of an aircraft by the oncoming flow of a jet stream from a turboprop-fan engine with tail arrangement of screws; composite wing and additional sliding elements of the composite wing in acceleration and climb, while the composite wing includes the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, while in the rotated position is a rotary flap pos. 4, and the flap pos. five;

in fig. 31 is a section C1.3-C1.3; a diagram shows the blowing of a convertible composite profile of an airplane wing with an incident stream of a jet stream from a turboprop-fan engine with a tail arrangement of screws; composite wing and additional retractable wing flaps and eaves in the take-off, braking or maneuvering mode, the composite wing including the main wing profile h 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, while in the rotated position is a rotary flap pos. 4, and the flap pos. 5, as well as in the extended position, the nodus is pos. 6;

in fig. 32 is a section C2.1-C2.1; a diagram shows the blowing of a convertible composite profile of an airplane’s wing by a running stream of a jet stream from a turboprop-fan engine with a tail arrangement of screws; composite wing and additional retractable wing flaps and eaves in the cruise flight mode, while the composite wing includes the main wing profile pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, with all the elements of the wing pos. 1, 4, 6 are in the folded position;

in fig. 33 is a section C2.2-C2.2; a diagram shows the blowing of a convertible composite profile of an airplane wing by the oncoming flow of a jet stream from a turboprop-fan engine with tail arrangement of screws; composite wing and additional retractable wing flaps and eaves in the mode of take-off, acceleration, climb, while the composite wing includes the main wing profile pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the flap pos. 4 and nadrylok pos. 6;

in fig. 34 is a section C2.3-C2.3; a diagram shows the blowing of a convertible composite wing profile of an aircraft with an incident flow of a jet stream from a turboprop-fan engine with tail arrangement of screws; composite wing and additional retractable wing flaps and eaves in the mode of take-off, braking, maneuvering, while the composite wing includes the main profile of the wing pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the noduck pos. 6, liner pos. 4, while the fender flap and liner have the ability to rotate around the longitudinal axis to change the angle of attack;

in fig. 35 is a section C3.1-C3.1; a diagram shows the blowing of a convertible composite profile of an airplane wing by the oncoming flow of a jet stream from a turboprop-fan engine with tail arrangement of screws; the composite wing in cruise flight mode, while the composite wing includes the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, with all the elements of the wing pos. 1, 2, 3 are in the folded position;

in fig. 36 is a section of C3.2-C3.2; a diagram shows the blowing of a convertible composite profile of an airplane wing by the oncoming flow of a jet stream from a turboprop-fan engine with a tail arrangement of screws; composite wing and additional retractable wing flaps and eaves in acceleration mode and climb, while the composite wing includes the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended paired position are the fenders pos. 2 and 3;

in fig. 37 is a section of C3.3-C3.3; a diagram shows the blowing of a convertible composite profile of an airplane wing by the oncoming flow of a jet stream from a turboprop-fan engine with a tail arrangement of screws; composite wing and additional retractable wing flaps and eaves in the take-off mode, braking, while the composite wing includes the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3;

in fig. 38 is a section C3.4-C3.4, showing the flow pattern of a transformable composite wing profile of an aircraft with an incident flow of a jet stream from a turboprop-fan engine with a tail arrangement of screws; composite wing and additional retractable wing flaps and eaves in the take-off, braking or maneuvering mode, the composite wing including the main wing profile h 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3, while the fenders have the ability to rotate around the longitudinal axis to change the angle of attack;

in fig. 39 is a section C4.1-C4.1; a diagram shows the blowing of a convertible composite profile of an airplane wing with a running stream of a jet stream from a turboprop-fan engine with a tail arrangement of screws, while the stream flowing around a running stream of a turboprop-fan engine occurs along the upper and lower surfaces of the main profile the composite wing in cruise flight mode, while the composite wing includes the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, with all the elements of the wing pos. 1, 2, 3, 6 are in the folded position;

in fig. 40 is a cross section of C4.2-C4.2; a diagram shows the blowing of a convertible composite profile of an airplane’s wing by a running stream of a flowing jet from a turboprop-fan engine with tail arrangement of screws; composite wing and additional retractable wing flaps and eaves in acceleration mode, climb, while the composite wing includes the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended paired position are the fenders pos. 2 and 3, as well as in the extended position, is the noduck pos. 6;

in fig. 41 is a section C4.3-C4.3; a diagram shows the blowing of a convertible composite profile of an airplane wing by the oncoming flow of a jet stream from a turboprop-fan engine with a tail arrangement of screws; a composite wing and additional retractable wing flaps and eaves in the take-off, braking mode, while the composite wing includes the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3, as well as in the extended position, is the noduck pos. 6;

in fig. 42 is a cross section of C4.4-C4.4; a diagram shows the blowing of a convertible composite profile of an airplane wing by the oncoming flow of a jet stream from a turboprop-fan engine with tail arrangement of screws; composite wing and additional retractable wing flaps and eaves in the take-off, braking or maneuvering mode, the composite wing including the main wing profile h 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3, as well as in the extended position, is the noduck pos. 6, while the fenders and the fender have the ability to rotate around the longitudinal axis to change the angle of attack;

in fig. 43 is a section D1.1-D1.1, shows a scheme for blowing a convertible composite profile of an airplane’s wing by the oncoming stream of a jet stream from a turboprop engine of a high-pressure propulsion engine or by a propeller-jet engine of AMD, while the stream of an outgoing jet flows around the upper and lower engines. the surfaces of the main profile of the composite wing in cruise flight mode, while the composite wing includes the main profile of the wing pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, with all the elements of the wing pos. 1, 4, 5, 6, are in the folded position;

in fig. 44 is a cross section of D1.2-D1.2; a diagram shows the blowing of a convertible composite profile of an airplane’s wing by the oncoming stream of a jet stream from a turboprop engine of a high-pressure propulsion engine or a propeller-jet engine of AMD, while the stream of an outgoing stream from an engine flows along the upper and lower the surfaces of the main profile of the composite wing and additional extended elements of the composite wing in acceleration and climb mode, the composite wing including the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, while in the rotated position is a rotary flap pos. 4, and the flap pos. five;

in fig. 45 is a cross section of D1.3-D1.3, shows a scheme for blowing a convertible composite profile of an airplane wing with a running stream of a jet stream from a turboprop-fan engine with a tail arrangement of screws from a turboprop engine of a turboprop engine or a screw-motor engine of AMD, with a stream flowing around the jet stream of the engines occurs on the upper and lower surfaces of the main profile of the composite wing and additional retractable wing flaps and e-fenders in the mode of take-off, braking or maneuvering, while e wing includes a main wing profile key. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, while in the rotated position is a rotary flap pos. 4, and the flap pos. 5, as well as in the extended position, the nodus is pos. 6;

in fig. 46 is a section D2.1-D2.1; a diagram shows the blowing of a convertible composite profile of an airplane wing by the oncoming flow of a jet stream from a turboprop engine of a high-pressure propulsion engine or a propeller-jet engine of AMD, while the flow of a running stream from the engines occurs along the upper and lower the surfaces of the main profile of the composite wing and additional retractable wing flaps and eaves in the cruise flight mode, while the composite wing includes the main profile of the wing pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, with all the elements of the wing pos. 1, 4, 6 are in the folded position;

in fig. 47 is a cross section of D2.2-D2.2; a diagram shows the blowing of a convertible composite profile of an airplane wing by the oncoming flow of a jet stream from a turboprop engine of a high-pressure propulsion engine or a propeller-drive engine of AMD, while the flow of a running stream from the engines occurs along the upper and lower the surfaces of the main profile of the composite wing and additional retractable wing flaps and eaves in the mode of take-off, acceleration, climb, while the composite wing includes the main profile of the wing pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the flap pos. 4 and nadrylok pos. 6;

in fig. 48 - section D2.3-D2.3, shows a scheme for blowing a convertible composite profile of an airplane’s wing by a flowing stream of a jet stream from a turboprop engine of a TVD or a AMD motor screw-motor engine; the surfaces of the main profile of the composite wing and additional retractable wing flaps and eaves in the take-off, braking, maneuvering mode, while the composite wing includes the main wing profile pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the noduck pos. 6, liner pos. 4, while the fender flap and liner have the ability to rotate around the longitudinal axis to change the angle of attack;

in fig. 49 is a section D3.1-D3.1, shows a scheme for blowing a convertible composite profile of an airplane’s wing by a flowing stream of a jet stream from a turboprop engine of a high-pressure propulsion engine or a propeller-drive engine of AMD, while flowing a stream of jet stream from an engine occurs along the upper and lower the surfaces of the main profile of the composite wing in cruise flight mode, while the composite wing includes the main profile of the wing pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, with all the elements of the wing pos. 1, 2, 3 are in the folded position;

in fig. 50 - section D3.2-D3.2, shows a scheme for blowing a convertible composite profile of an airplane wing by the oncoming flow of a jet stream from a turboprop engine of a high-pressure propulsion engine or a propeller-drive engine of AMD, while flowing a stream of a stream of engines from the upper and lower the surfaces of the main profile of the composite wing and additional retractable wing flaps and eaves in the acceleration mode and climb, while the composite wing includes the main profile of the wing pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended paired position are the fenders pos. 2 and 3;

in fig. 51 is a section D3.3-D3.3; a diagram shows the blowing of a transformed composite wing profile of an aircraft by the oncoming flow of a jet stream from a turboprop engine of a high-pressure propulsion engine or an AMD propeller motor; the surfaces of the main profile of the composite wing and additional retractable wing flaps and eaves in the take-off, braking mode, while the composite wing includes the main profile of the wing pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3;

in fig. 52 is a section D3.4-D3.4; a diagram shows the blowing of a convertible composite profile of an airplane wing with a running stream of a jet stream from a turboprop-fan engine with a tail arrangement of screws from a turboprop engine of a turboprop engine or a screw-motor engine of AMD, with a stream flowing around the jet stream of the engines occurs on the upper and lower surfaces of the main profile of the composite wing and additional retractable wing flaps and e-fenders in take-off, braking or maneuvering mode, while e wing includes a main wing profile key. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3, while the fenders have the ability to rotate around the longitudinal axis to change the angle of attack;

in fig. 53 - section D4.1-D4.1, shows the scheme of blowing the transformed composite profile of an airplane wing by the oncoming flow of a jet stream from a turboprop engine of a high-pressure propulsion engine or a propeller-drive engine of AMD, while the flow of a running stream from the jet flows through the upper and lower the surfaces of the main profile of the composite wing in cruise flight mode, while the composite wing includes the main profile of the wing pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, with all the elements of the wing pos. 1, 2, 3, 6 are in the folded position;

in fig. 54 - section D4.2-D4.2, shows a scheme for blowing a convertible composite profile of an airplane wing by a flowing stream of a jet stream from a turboprop engine of a high-pressure turbine engine or an AMD motor screw-motor engine; the surfaces of the main profile of the composite wing and additional retractable wing flaps and eaves in the acceleration mode, climb, while the composite wing includes the main profile of the wing pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended paired position are the fenders pos. 2 and 3, as well as in the extended position, is the noduck pos. 6;

in fig. 55 - section D4.3-D4.3, shows a scheme for blowing a convertible composite profile of an airplane’s wing by the oncoming stream of a jet stream from a turboprop engine of a high-pressure propulsion engine or a propeller-drive engine of AMD, while the stream of a stream flowing from the engines overflows through the upper and lower the surfaces of the main profile of the composite wing and additional retractable wing flaps and eaves in the take-off, braking mode, while the composite wing includes the main profile of the wing pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3, as well as in the extended position, is the noduck pos. 6;

in fig. 56 is a cross section of D4.4-D4.4, shows a scheme for blowing a convertible composite profile of an airplane’s wing by the oncoming stream of a jet stream from a turboprop engine of a high-pressure propulsion engine, or by an AMD motor screw-motor engine; the surfaces of the main profile of the composite wing and additional retractable wing flaps and eaves in the take-off, braking or maneuvering mode, the composite wing including the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2 and 3, as well as in the extended position, is the noduck pos. 6, while the fenders and the fender have the ability to rotate around the longitudinal axis to change the angle of attack;

in fig. 57 - section B * 1.3-B * 1.3, shows a scheme for blowing a convertible composite wing profile of an aircraft with an incident flow of a stream from a double-circuit turbojet engine with a degree of loophole of more than 2, for example, a turbofan engine with flow mixing (TRD), with a stream flowing around the flowing stream from the engine of the turbofan engine occurs on the upper and lower surfaces of the main profile of the composite wing and additional extended elements of the composite wing in the mode of vertical takeoff by creating an equal hanging reactive torque relative to the center of gravity of the aircraft, while the composite wing includes the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 3, while in the rotated position is a rotary flap pos. 4, the flap of pos. Is in the extended position. 5, as well as in the extended position, the nodus is pos. 6 at optimal angles of attack;

in fig. 58 - section B * 2.3-B * 2.3, shows a scheme for blowing a convertible composite wing profile of an aircraft with an incident stream of a stream from a double-circuit turbojet engine with a degree of loophole of more than 2, for example, a turbofan engine with mixing of streams of turbofan engines, while flowing a stream of exhaust stream from the engine TRD occurs on the upper and lower surfaces of the main profile of the composite wing and additional extended elements of the composite wing in the mode of vertical takeoff by creating equilibrium The accelerated reactive moment relative to the center of gravity of the aircraft, while the composite wing includes the main wing profile pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the noduck pos. 6 and liner pos. 4, at optimal angles of attack;

in fig. 59 - section B * 3.4-B * 3.4, shows a scheme for blowing a convertible composite wing profile of an aircraft with an incident flow of a stream from a double-circuit turbojet engine with a degree of contour more than 2, for example, a turbofan engine with mixing of streams of turbofan, while flowing around an incident stream of exhaust stream from the engine TRD occurs on the upper and lower surfaces of the main profile of the composite wing and additional extended elements of the composite wing in the vertical take-off mode by creating equilibrium The accelerated reactive moment relative to the center of gravity of the aircraft, while the composite wing includes the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2, 3, at optimal angles of attack;

in fig. 60 - section B * 4.4-B * 4.4, shows a scheme for blowing a convertible composite wing profile of an aircraft with an incident flow of a stream from a double-circuit turbojet engine with a degree of loophole of more than 2, for example, a turbofan engine with mixing of streams of turbofan, while flowing an incident stream of jet outflow from the engine TRD occurs on the upper and lower surfaces of the main profile of the composite wing and additional extended elements of the composite wing in the vertical take-off mode by creating equilibrium The accelerated reactive moment relative to the center of gravity of the aircraft, while the composite wing includes the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the noduck pos. 6 and fenders pos. 2, 3, at optimal angles of attack;

in fig. 61 - section C * 1.3-C * 1.3, shows a scheme for blowing a convertible composite profile of an airplane’s wing by a running stream of a jet stream from a turboprop-fan engine with tail arrangement of screws; wing and additional extended elements of the composite wing in the mode of vertical takeoff by creating a balanced reactive moment relative to the center of gravity of the aircraft paraparata, while the composite wing includes the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, while in the rotated position is a rotary flap pos. 4, the flap of pos. Is in the extended position. 5, as well as in the extended position, the nodus is pos. 6 at optimal angles of attack;

in fig. 62 is a section C * 2.3-C * 2.3; a diagram shows the blowing of a convertible composite profile of an airplane’s wing by a running stream of a jet stream from a turboprop-fan engine with tail arrangement of screws, while the stream flowing around a running stream of jet stream from a high-pressure jet engine wing and additional extended elements of the composite wing in the mode of vertical takeoff by creating a balanced reactive moment relative to the center of gravity of the aircraft paraparata, while the composite wing includes the main wing profile pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the noduck pos. 6 and liner pos. 4, at optimal angles of attack;

in fig. 63 - section C * 3.4-C * 3.4; shows a scheme for blowing a transformed composite wing profile of an aircraft with an incident flow of a jet stream from a turboprop-fan engine with tail arrangement of screws; wing and additional extended elements of the composite wing in the mode of vertical takeoff by creating a balanced reactive moment relative to the center of gravity of the aircraft paraparata, while the composite wing includes the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2, 3, at optimal angles of attack;

in fig. 64 shows a section C * 4.4-C * 4.4; shows a diagram of blowing a convertible composite wing profile of an aircraft with an incident stream of a jet stream from a turboprop-fan engine with tail arrangement of screws; wing and additional extended elements of the composite wing in the mode of vertical takeoff by creating a balanced reactive moment relative to the center of gravity of the aircraft paraparata, while the composite wing includes the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the noduck pos. 6 and fenders pos. 2, 3, at optimal angles of attack;

in fig. 65 - section D * 1.3-D * 1.3, shows a scheme for blowing a transformed composite wing profile of an aircraft with an incident flow of a jet stream from a turboprop engine or a screw-motor engine of AMD, while the stream of jet stream flows around the upper and lower surfaces the main profile of the composite wing and additional extended elements of the composite wing in the vertical take-off mode by creating a balanced reactive torque relative to the center of gravity of the aircraft, however, the composite wing includes the main wing profile pos. 1, the retractable eavement of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, rotary flap pos. 4, retractable flap pos. 5, while in the rotated position is a rotary flap pos. 4, the flap of pos. Is in the extended position. 5, as well as in the extended position, the nodus is pos. 6 at optimal angles of attack;

in fig. 66 - section D * 2.3-L * 2.3, shows a scheme for blowing a transformed composite wing profile of an aircraft with an incident flow of a jet stream from a turboprop engine or a propeller-jet engine of AMD, while the flow of a jet stream around the upper and lower surfaces the main profile of the composite wing and additional extended elements of the composite wing in the vertical take-off mode by creating a balanced reactive moment relative to the center of gravity of the aircraft, however, the composite wing includes the main wing profile pos. 1, retractable liner asymmetric streamlined drop-shaped section of a double-convex profile pos. 4, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the noduck pos. 6 and liner pos. 4, at optimal angles of attack;

in fig. 67 - section D * 3.4-D * 3.4, shows a scheme for blowing a transformed composite wing profile of an aircraft with an incident flow of a jet stream from a turboprop engine or a propeller-jet engine of AMD, while the stream with jet stream flows around the upper and lower surfaces the main profile of the composite wing and additional extended elements of the composite wing in the vertical take-off mode by creating a balanced reactive moment relative to the center of gravity of the aircraft, however, the composite wing includes the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, while in the extended position are the fenders pos. 2, 3, at optimal angles of attack;

in fig. 68 - section D * 4.4-D * 4.4, shows a scheme for blowing a transformed composite wing profile of an aircraft with an incident flow of a jet stream from a turboprop engine or a propeller-jet engine of AMD, while the flow of a jet stream flows around the upper and lower surfaces the main profile of the composite wing and additional extended elements of the composite wing in the vertical take-off mode by creating a balanced reactive moment relative to the center of gravity of the aircraft, however, the composite wing includes the main wing profile pos. 1, the first retractable liner asymmetric streamlined drop-shaped section of the concave-convex profile pos. 2, the second retractable flap asymmetric streamlined drop-shaped section of a convex profile pos. 3, retractable eaves of the asymmetric streamlined drop-shaped section of the concave-convex profile pos. 6, while in the extended position, the noduck pos. 6 and fenders pos. 2, 3, at optimal angles of attack;

in fig. 69 is an aircraft layout in terms of a cigar-shaped fuselage with two turbojet turbojet engines with a turbojet of more than 2 located on the supporting horizontal arms in front of the toe of the lateral straight wings of the composite profile;

in fig. 70 is an airplane layout in plan with a cigar-shaped fuselage, with two TVVD turboprop engines with tail arrangement of screws placed on the supporting horizontal cantilevers in front of the toe of the side wings of the composite profile;

in fig. 71 is an aircraft layout in terms of a cigar-shaped fuselage, with two turboprop engines or one or two AMD VMD engines mounted on supporting horizontal cantilevers in front of the toe of the side straight wings of the composite profile;

in fig. 72 - in vertical take-off, hang-up and landing mode, the aircraft layout is shown with vertical take-off and landing in terms of a cigar-shaped fuselage, with two rotary double-circuit turbojet engines of turbofan with a degree of contour 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 the two front turbofan engines and sections of the front segment swivel wings of the composite profile in the front section fuselage, as well as with two turbojet two-circuit turbojet engines with a degree of contour more than 2, placed on the supporting horizontal cantilevers in front of the toe of the rear side straight wings of the composite profile, while the toes of all the wings of the composite profile with variable aerodynamic characteristics are located in the area of the incident flow of the outflowing jet TRDD’s two-circuit jet engines, while in the mode of vertical lifting, hovering and landing, the resulting traction efforts to create vertical th reactive torque by lifting combi turbofan jet engines are directed radially in three directions;

in fig. 73 is a plane layout with a vertical take-off and a landing in the plane of FIG. 72 when the position of the rotary engine turbofan and rotary wings composite profile in horizontal flight mode;

in fig. 74 - in vertical take-off, hang-up and landing mode, the aircraft layout is shown with vertical take-off and landing in terms of a cigar-shaped fuselage, with two rotary double-circuit turbojet engines of turbofan with a degree of contour more than 2, for example, turbofan engines with flow mixing placed on horizontal consoles with a turntable for the possibility of rotation of the two front turbofan engines in front of the fuselage, while the lateral platforms are located along the radius of the side turntables Segment ring wings of a composite profile with variable aerodynamic characteristics, as well as with two turbofan turbojet engines with a turbidity of more than 2 placed on the supporting horizontal cantilevers in front of the toe of the rear side straight wings of the composite profile, while the toes of the composite wings are located in the area of the flow of the exhausting stream of turbofan jet engines of turbofan engines, while in the mode of vertical lifting, hovering and landing, the resulting traction forces the creation of a vertical lifting reactive moment from turbofan jet engines TRDD directed radially in three directions;

in fig. 75 is the layout of an aircraft with a vertical take-off and a landing in the plane of FIG. 74 when the position of the rotary engine turbofan and rotary wings composite profile in horizontal flight mode;

in fig. 76 - in vertical take-off, hang-up and landing mode, the aircraft layout of the aircraft with vertical take-off and landing in the plane with a disc-shaped fuselage shape, with three rotary double-circuit turbojet engines of turbofan engines with a contour degree of more than 2, such as turbofan engines with flow mixing, located on horizontal horizontal support guides for the possibility of joint rotation of the engines of turbofan engines and sections of the swivel wings of the composite profile around the vertical axis, while the nose and all sections of the swivel wings of the composite profile with variable aerodynamic characteristics are located in the flow area of the outflowing jet from the turbofan engines, while in the vertical lifting mode, freezing and landing, the resulting traction efforts to create a vertical lifting torque from the turbofan engines radially in three directions;

in fig. 77 is the layout of an aircraft with a vertical take-off and a landing in the plane of FIG. 76 when the position of the rotary engines of turbofan engines and sections of the rotary wings of the composite profile in the mode of horizontal flight;

in fig. 78 - in vertical take-off, hang-up and landing mode, the aircraft layout of the aircraft with vertical take-off and landing in the plan with a disc-shaped fuselage is shown, with three rotary double-circuit turbojet engines of turbofan with a degree of contour more than 2, for example, turbofan engines with flow mixing, placed on horizontal horizontal supporting rotary platforms for the possibility of joint rotation of turbofan engines and sections of the rotary wings of the composite profile around the vertical axis, with e Volume of socks of all sections of the swivel wings of a composite profile with variable aerodynamic characteristics are located in the area of the oncoming flow of the outflowing jet from the turbofan engines ;

in fig. 79 is the layout of an aircraft with a shortened or vertical take-off and landing in the plan of FIG. 78 at the position of rotary engines of turbofan engines and sections of the rotary wings of the composite profile in horizontal flight mode

in fig. 80 - in vertical take-off, hang-up and landing mode, the layout of the aircraft with vertical take-off and landing in terms of a cigar-shaped fuselage, with two rotary turboprop-and-fan TVVD engines with tail arrangement of screws placed on horizontal consoles with a turntable, is shown to enable the two front to jointly rotate TVVD and sections of the front segment rotary wings of the composite profile in the front part of the fuselage, as well as with two turbopropfan engines T VD with tail arrangement of screws placed on the supporting horizontal cantilevers in front of the toe of the rear side straight wings of the composite profile, while the socks of all the wings of the composite profile with variable aerodynamic characteristics are located in the area of the oncoming flow of the outflowing jet from the TVWD engines, while in the mode of vertical lifting, hanging and landing the resulting traction efforts to create a vertical lifting reactive torque from the engines TWVD radially directed in three directions;

in fig. 81 is an aircraft layout layout with vertical take-off and landing in the plane of FIG. 80 with the position of the TVVD rotary engines and the swivel wings of the composite profile in the horizontal flight mode;

in fig. 82 - in vertical take-off, hang-up and landing mode, the layout of the aircraft with vertical take-off and landing in terms of a cigar-shaped fuselage, with two rotating turboprop-and-ventilation TVVD engines with tail arrangement of screws placed on horizontal consoles with a turning platform for the ability to rotate two front TVVDs is shown. in the front part of the fuselage, while along the radius of the side turntables are located the side segment annular wings of the composite profile with variable aerodynamics amicable characteristics, as well as with two turbopropfan engines of TVVD with tail arrangement of screws placed on supporting horizontal cantilevers in front of the toe of the rear lateral straight wings of the composite profile, while the toes of composite wings are located in the area of the incident flow of the outflowing jet of two-contour jet engines of TWRD, while vertical lift, freeze and landing mode, the resulting traction efforts to create a vertical lifting reactive torque from jet engines Ateli TVVD directed radially in three directions;

in fig. 83 is the layout of an aircraft with vertical take-off and landing in the plane of FIG. 82 when the position of the TVVD rotary engines and the swivel wings of the composite profile in the horizontal flight mode;

in fig. 84 - in vertical take-off, hang-up and landing mode, the aircraft layout of the aircraft with vertical take-off and landing in the plan with a disc-shaped fuselage, with three rotary turbopropfan engines of TVVD with tail arrangement of screws placed on the annular horizontal support guides for the possibility of joint rotation of TVVD engines and sections of the swivel wings of the composite profile around the vertical axis, as well as with two turbopropfan engines with a tail HPVD screws mounted on the supporting horizontal consoles in front of the toe of the side straight wings of the composite profile, while the socks of all sections of the swivel wings of the composite profile with variable aerodynamic characteristics are located in the area of the oncoming flow of the outflowing jet from the TVWD engines, while in the vertical lifting, hanging and landing mode the resulting traction efforts to create a vertical lifting reactive torque from the engines of the turbofan engines are radially directed in three directions;

in fig. 85 is the layout of an aircraft with vertical take-off and landing in the plane of FIG. 84 at the position of the TVVD rotary engines and sections of the rotary wings of the composite profile in the horizontal flight mode;

in fig. 86 - in vertical take-off, hang-up and landing mode, an aircraft vertical-takeoff and landing planes are shown with a disc-shaped fuselage shape, with three rotating turbopropfan-powered TVWD engines with tail arrangement of screws placed on annular horizontal supporting rotary platforms for the possibility of joint rotation of TVVD engines and sections of the swivel wings of the composite profile around the vertical axis, while the socks of all the sections of the swivel wings of the composite profile with yaemymi aerodynamic arranged in the incoming flow of the outflowing jet engines TVVD, wherein a vertical lifting mode, hovering and landing resulting tractive effort to create a vertical lifting moment from TVVD jet engines are directed radially in three directions;

in fig. 87 is a layout diagram of an aircraft with a shortened or vertical take-off and landing in the plane of FIG. 86 at the position of the TVVD rotating engines and sections of the rotating wings of the composite profile in the horizontal flight mode

in fig. 88 - in the vertical take-off, freeze and landing mode, the aircraft layout is shown with vertical take-off and landing in terms of a cigar-shaped fuselage, with two turboprop rotary TVD engines, or AMD propeller-motor engines placed on horizontal consoles with a turntable to allow joint rotation of the two front turboprop engines of the turboprop engines, or AMD screw-motor engines and sections of the front segment rotary wings of the composite profile in the front part of the fuselage, and t Also with two turboprop engines or one of two AMD turboprop engines placed on supporting horizontal cantilevers in front of the toe of the rear side straight wings of the composite profile, while the socks of all the wings of the composite profile with variable aerodynamic characteristics are located in the area of the incident flow of the outgoing jet of turboprop engines TVD or AMD motor scooters, while in the mode of vertical lifting, hovering and landing, the resulting traction efforts to create vertical thrust lifting torque from turboprop engines TVD or AMD screw-motor engines directed radially in three directions;

in fig. 89 is a plane layout with a vertical take-off and a landing in the plane of FIG. 88 at the position of rotary turboprop engines TVD, or AMD screw-motor engines and rotary wings of the composite profile in the mode of horizontal flight;

in fig. 90 - in vertical take-off, hang-up and landing mode, the aircraft layout is shown with vertical take-off and landing in terms of a cigar-shaped fuselage, with two turboprop rotary TVD engines, or AMD screw-motor engines placed on horizontal consoles with a turntable for turning two front turboprop engines of a turboprop engine, or a VMD screw-motor engines, in the front part of the fuselage, as well as with two turboprop engines of a turboprop engine, or two screw-motor engines AMD located on the supporting horizontal consoles in front of the toe of the rear side straight wings of the composite profile, while along the radius of the side turntables are located the side segment ring wings of the composite profile with variable aerodynamic characteristics, while the toes of the composite wings are located in the region of the incident flow of the outgoing jet of turboprop TVD engines or AMD engines, while in the vertical lift, freeze and landing mode, the resulting tractive effort on the creation of a vertical lifting reactive moment from turboprop engines of a turboprop engine, or AMD screw-motor engines, directed radially in three directions;

in fig. 91 is the layout of an aircraft with a vertical take-off and a landing in the plane of FIG. 90 at the position of rotary turboprop engines TVD, or AMD screw-motor engines and rotary wings of the composite profile in the mode of horizontal flight;

in fig. 92 - in vertical take-off, hang-up and landing mode, the aircraft layout of the vertical take-off and landing planes is shown with a disc-shaped fuselage shape, with three turbo-propeller turboprop thrusters, or AMD propeller-mounted engines, placed on the annular horizontal support rails for joint rotation turboprop engines TVD, or screw-motor engines AMD and sections of the rotary wings composite profile around the vertical axis, while the socks of all sections of the rotary the snails of the composite profile with variable aerodynamic characteristics are located in the area of the oncoming flow of the outflowing jet from turboprop engines TVD, or AMD screw-motor engines, while in the mode of vertical lifting, lagging and landing, the resulting traction efforts to create a vertical lifting torque from turboprop engines TVD, either AMD motor engines are radially directed in three directions;

in fig. 93 is the layout of an aircraft with a vertical take-off and a landing in the plane of FIG. 92 when the position of the TVVD rotary engines and sections of the rotary wings of the composite profile in the mode of horizontal flight;

in fig. 94 - in vertical take-off, hang-up and landing mode, the aircraft layout of the aircraft with vertical take-off and landing in the plan with a disc-shaped fuselage, with three turboprop turboprop engines of the turboprop engine or propeller-mounted AMD engines placed on the annular horizontal supporting rotary platforms for the possibility of joint rotation is shown TVD turboprop engines, or AMD screw-motor engines and sections of the rotary wings of the composite profile around the vertical axis, while the socks of all sections are turning company wings of a composite profile with variable aerodynamic characteristics are located in the area of the oncoming flow of the jet stream from turboprop engines TVD, or AMD screw-motor engines, while in the mode of vertical lifting, lagging and landing, the resulting traction efforts to create a vertical lifting torque from turboprop engines TVD , or AMD motor-screw engines are directed radially in three directions;

in fig. 95 is a plane layout with a shortened or vertical take-off and a landing in the plane of FIG. 94 at the position of rotary turboprop engines TVD, or AMD screw-motor engines and sections of the rotary wings of the composite profile in the mode of horizontal flight;

On the submitted drawings positions indicated:

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

pos. 2 - the first retractable liner;

pos. 3 - the second retractable liner;

pos. 4 - rotary flap;

pos. 5 - retractable flap;

pos. 6 - retractable e-flap;

pos. 7 - dual-circuit turbojet engine with a degree of contour of more than 2, for example, turbofan engines with mixture of flows (TRD);

pos. 8 - turbopropfan engine with tail arrangement of screws (TVVD);

pos. 9 - jet turboprop engine (TVD), or propeller engine (AMD);

pos. 10 - cigar-shaped fuselage;

pos. 11 - disc-shaped fuselage;

pos. 12 - lateral straight wing composite profile;

pos. 13 - swivel wing composite profile;

pos. 14 is a lateral segmental annular wing of a composite profile;

pos. 15 - bearing horizontal console for mounting engines;

pos. 16 - carrying horizontal console with a turntable for the possibility of rotation of the engine around the vertical axis;

pos. 18 - annular horizontal support guides for turning interlocked engines with portions of composite wings.

- вертикальный реактивный момент относительно центра тяжести летательного аппарата;

- vertical reactive moment relative to the center of gravity of the aircraft;

ΔHn is the distance between the main wing profile and the fender flap, or between the extended wing flaps, or the distance between the main wing profile and the fender flap;

Δ Ln is the amount of overlap between the tip of the main wing and the tail portion of the euron, or the amount of overlap between the tip of the fender liner and the tail section of the main wing, or the amount of overlap between the tip of the second fender liner and the tail portion of the first fender liner;

Ci is the maximum thickness of the main wing in the vertical plane of the air flow.

Claims (3)

1. The wing of the aircraft with variable aerodynamic characteristics, including the main profile of the wing and additional extending profile elements of the wing, while the additional extendable profile elements of the wing are made in the form of one or several e-wings extending above the upper surface of the main profile of the wing, or in the form of one or several wing flaps, under the lower surface of the main wing profile, or simultaneously in the form of one or several wing wings, extended above the upper surface of the main wing profile and one or several wing flaps extended under the lower surface of the main wing profile, while in the horizontal cruising flight mode the main wing profile and additional profile elements form a single streamlined wing profile, characterized in that for different flight modes of the aircraft associated with take-off, acceleration, climb, lowering, maneuvering and landing to change the aerodynamic characteristics of the wing of the aircraft, push The upper wings of the wing profile extend forward and upwards, while in the extended position the distance ΔHn between the main wing profile and the wing wings or between the extended wing wings is at least 0.5Ci (where Ci is the maximum thickness of the main wing in the vertical plane of the air flow), with This retractable wing flaps extend back and down below the main wing profile, while in the extended position, the distance ΔHn between the wing wing main profile and the wing flap or between the extended wing flaps is at least 0.5Ci, while at the extended position of the e-fenders, the amount of overlap ΔLn between the toe of the main wing and the tail part of the e-fender is not less than Ci, while with the extended position of the fenders, the amount of overlap ΔLn between the toe of the fender and the tail of the main wing is not less than Ci, while the amount of overlap ΔLn between the toe of the second fender liner and the tail part of the first fender liner is at least Ci; pyr longitudinal axis. 2. The aircraft, including the fuselage, power plant with propeller, or turboprop, or turboprop-fan, or twin-turbojet, with a degree of contour more than 2, engines, control cabin, integral control system, composite wings, containing the main profile of the wing and additional extended profile elements, at the same time, in the horizontal cruise flight mode, the main wing profile and additional profile elements form a single streamlined wing profile, while the composite wings are located in the free-stream region of the outflowing jet from propeller or turboprop engines or turboprop fans; the main profile of the wing and additional extending profile elements of the wing, with additional extending profile elements of the wing performed Yena either in the form of one or several e-fins extending above the upper surface of the main section of the wing, or in the form of one or several fenders extending below the lower surface of the main section of the wing, or together in the form of one or several e-fenders and fenders, characterized in flight modes of the aircraft associated with take-off, acceleration, climb, lowering, maneuvering and landing, for optimal changes in the aerodynamic characteristics of the wing of the aircraft The ellipses pulled forward and upward over the main wing profile, while in the extended position, the distance ΔHn between the wing’s main profile and the wing ejector or between the extended wingnings is at least 0.5Ci, while the retractable wing flaps push back and down below the main wing profile, while in the extended position, the distance ΔHn between the main wing profile and the fender liner, or between the extended wing flaps is at least 0.5Ci; of the wing and tail portion of the fender is not less than Ci, while with the wing flaps extended, the amount of overlap ΔLn between the toe of the fender and the tail part of the main wing is not less than Ci, while the amount of overlap ΔLn between the toe of the second fender and tail section of the first fender is not less Ci, while extending the wing profile elements in the extended position to change the angle of attack have the ability to rotate around the longitudinal axis. 3. The aircraft, including the fuselage, the propulsion system with propeller or turboprop, or turboprop-fan, or twin-turbojet, with a degree of contour more than 2, engines, control cabin, integral control system, composite wings, containing the main wing profile and additional extended profile elements, at the same time, in the horizontal cruise flight mode, the main wing profile and additional profile elements form a single streamlined wing profile, while the composite wings are located in the free-stream region of the outflowing jet from propeller or turboprop engines or turboprop fans; the main profile of the wing and additional extending profile elements of the wing, with additional extending profile elements of the wing performed Yena either in the form of one or several e-fins extending above the upper surface of the main wing profile, or in the form of one or several fenders extending below the lower surface of the main section of the wing, or together in the form of one or more fenders and fenders, characterized in that flight modes of the aircraft associated with take-off, acceleration, climb, descent, maneuvering and landing, for optimal changes in the aerodynamic characteristics of the wing of the aircraft The ellipses pulled forward and upward over the main wing profile, while in the extended position, the distance ΔHn between the wing’s main profile and the wing ejector or between the extended wingnings is at least 0.5Ci, while the retractable wing flaps push back and down below the main wing profile, while in the extended position, the distance ΔHn between the main wing profile and the fender liner, or between the extended wing flaps is at least 0.5Ci; of the wing and tail portion of the wing-flap is not less than Ci, while with the wing flaps extended, the amount of overlap ΔLn between the toe of the fender and the tail part of the main wing is not less than Ci, and the amount of overlap less Ci, while the extended wing wing elements in the extended position to change the angle of attack have the ability to rotate around the longitudinal axis, while being able to create a stable total equation hinged power reactive moment relative to the center of gravity of the aircraft in the mode of vertical lifting, freezing and landing; .

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