RU2712708C1 - Aircraft with short or vertical take-off and landing - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft with short or vertical takeoff and landing. Airplane with short or vertical take-off and landing includes a cigar-shaped airframe-shaped fuselage, wings with mechanization elements to change aerodynamic characteristics of the wing, power plant of four or more propeller motors, or turboprops, or turbo-fan engines, integral control system. In vertical lifting, hovering and landing mode, total balanced balance of lifting reactive moments is created, created by means of flows of outflowing jets from screw-type, or turboprops, or turbo-fan engines, directed to sections of wings with elements of mechanization. To create lifting torque moments in at least two directions in fuselage nose part, two support wings of integral wings are provided on both sides of fuselage, consisting of frontal section, angular section with mechanization elements, longitudinal side section with mechanization elements. Connections of adjacent sections of integral wing are streamlined.

EFFECT: fuselage fore wing shape is optimized for vertical take-off, hovering and landing.

1 cl, 20 dwg

Description

The invention relates to the field of aviation, in particular to aircraft with shortened or vertical take-off and landing. Known technical solutions of aircraft with the possibility of vertical take-off and landing using a flowing jet of engines along the perimeter of an annular or circular wing with a change in thrust vector (RF patent N2005660, author Bratin SF, publ., January 15, 1994, RF patent N2406650, author Andreev Yu.P., publ., December 20, 2010, RF patent N 2491206, author Anserov D.O., Anserov A.D., publ., 05.20.2013). With many layout and structural drawbacks of the above technical solutions, it is worth noting the rationality of using the outgoing jet of engines along the upper and lower wing surfaces around the perimeter of the aircraft to create a total balanced reactive moment relative to the center of gravity of the aircraft with a maximum eccentricity in the size of the radius of a ring or circular wing in the mode vertical lift, hovering and landing. Implemented technical solutions of aircraft with shortened and vertical take-off and landing are also known (see book E. Ruzhitsky, “European Vertical Take-Off Aircraft”, LLC publishing house “Astrel”, LLC publishing house ACT, 2000) Yak-38 , Zh-141 and a series of modifications of the aircraft HARRIER GR.Mk.3. This aircraft is made according to the monoplane scheme with one lift-marching engine Bristol-Sidpi "Pegasus", with rotary nozzles mounted on the sides of the fuselage. Side unregulated air intakes. All four nozzles rotate synchronously with a maximum nozzle rotation angle of 98.5 degrees. The disadvantage of this technical solution with the location of the nozzles near the center of gravity of the aircraft is its instability in the vertical lift, hover and landing modes, as well as in the intermediate mode of transition from hovering to horizontal flight. Also known is a plane with a shortened or vertical take-off and landing, including the fuselage, wings with mechanization elements for changing the wing profile, an integrated control system, a power plant with turboprop or turbofan engines, while the fuselage is made disk-shaped or cigar-shaped, while the power plant consists of three or more turboprop or turbofan engines, while at least two turboprop or turbofan engines have rotation around the vertical axis, while the wing with mechanization elements for changing the wing profile has an annular outline in plan, while the wing toe with mechanization elements for changing the wing profile is in the region of the incoming air stream from turboprops or turbofan engines, while creating a stable total balancing reactive moment relative to the center of gravity of the aircraft, in the mode of lifting, hovering and landing resulting efforts of three or more t of turboprop or turbofan engines are directed radially in at least three directions (RF patent N 2670361, author B. Suchentsev, publication October 22, 2018) It should be noted that for the take-off, hover and landing mode, only a portion of the ring wings is functionally used no more than a ring sector with an angle of no more than 90 degrees, in each of three directions. The aim of this invention is to optimize the shape of the wings in the nose of the fuselage for the implementation of vertical take-off, hovering and landing. This goal is achieved by performing an airplane with a shortened or vertical take-off and landing, including a cigar-shaped streamlined fuselage, wings with mechanization elements to change the aerodynamic characteristics of the wing, a power plant of four or more rotor engines, or turboprops, or turbofans, an integral control system, this in the mode of vertical lifting, hovering and landing creates a balanced balance of lifting reactive moments creating flowing streams from propeller, or turboprop, or turbofan engines directed to wing sections with mechanization elements, while to create lifting reactive moments in at least two directions in the nose of the fuselage, there are two load-bearing wing consoles of integral form on both sides the fuselage, consisting of the frontal section of the integral wing, the corner section of the integral wing with mechanization elements and the longitudinal side section of the integral wing with elements of mechanization, while the connection of adjacent sections of the integral wing is made streamlined lekally jointed, while the frontal section of the front integrated wing has a streamlined shape lekolno articulated with the surface of the fuselage, while the corner section of the front integral wing is made or a straight line in plan at an angle to the longitudinal axis the fuselage, either in the form of an annular sector in plan with an angle of the annular sector from 50 degrees to 90 degrees, or as a sector of an annular polygon in plan is described or inscribed in an annular sector with an angle from 50 degrees to 90 degrees, while the longitudinal side section of the front integral wing is made rectilinear in plan, in the direction coinciding with the longitudinal axis of the fuselage, while the angular and longitudinal side sections, or only the longitudinal side the front integral wing section is used in take-off, hover and landing mode to create lifting jet moments relative to the center of gravity of the aircraft and are located in the region of the incoming flow of the outgoing jet from the propeller motor, or turboprop, or turbofan engines. The illustrative examples of this invention show the versions of aircraft with vertical take-off and landing using propeller, or turbofan, or turboprop engines:

in FIG. 1 - a layout diagram of an airplane with a shortened or vertical take-off and landing in the plan in the vertical take-off, hover and landing mode, including a streamlined cigar-shaped fuselage, two marching turbofan engines with tail rotor and located on the supporting consoles in the rear of the fuselage, two lateral rotary turbofan engine with tail rotor for blowing the front wings with mechanization elements, with each supporting console in front of the wing consists of three sections, the frontal, angular and longitudinal lateral sections, while the frontal section of the front wing support console has a streamlined shape that is articulated articulated with the fuselage surface, while the corner section of the front wing support console is made in the form of an annular sector with an angle of 50 60 deg., While the longitudinal side section of the front wing support console is made rectilinear coinciding with the longitudinal axis of the fuselage, while in the region of the incoming flow of the outflowing jet from marching turboprops rotary engines with tail rotors in the rear of the fuselage made a high wing linear wing with mechanization elements located above the front wing level and mounted on vertical consoles, while in the mode of vertical lifting, hovering and landing, the resulting traction forces to create lifting reactive moments from turbofan engines with the tail of the screws are directed radially in three directions;

in FIG. 2 is a layout diagram of an airplane with shortened or vertical take-off and landing in the plan of FIG. 1 in the horizontal cruise flight mode;

in FIG. 3 - the layout of the aircraft with a shortened or vertical take-off and landing in the plan, in the mode of vertical take-off, hovering and landing, including a streamlined cigar-shaped fuselage, two marching turboprop engines located on the supporting consoles in the rear of the fuselage, two lateral rotary turboprop engines for blowing the front wings with mechanization elements, with each supporting console of the front wing consists of three sections, frontal, angular and longitudinal side section, etc. this frontal section of the front wing support console has a streamlined shape lekalno articulated with the surface of the fuselage, while the corner section of the front wing support console is made in the form of an annular sector with an angle of 50-60 degrees., while the longitudinal side section of the front wing support console is made rectilinear with the longitudinal axis of the fuselage, while in the region of the incoming flow of the outflowing jet of marching turboprop engines in the rear part of the fuselage a linear wing of a high-wing with elements of Hanizats located above the level of the front wing and mounted on vertical consoles, while in the mode of vertical lifting, hovering and landing, the resulting traction efforts to create lifting reactive moments from turboprop engines are directed radially in three directions; in FIG. 4 is a layout diagram of an airplane with shortened or vertical take-off and landing in the plan of FIG. 3 in the horizontal cruise flight mode; in FIG. 5 - section A 1.1-A 1.1, shows a diagram of the airflow of the tail linear wing of an aircraft with free-flow mechanization elements from a marching turbofan engine in take-off, hovering or landing mode, including the main wing profile, the first retractable liner of an asymmetric streamlined section of a concave-convex profile , the second extendable wing liner of an asymmetric streamlined section of a plano-convex profile, while in the extended position back and down, both wing liners are at an optimal angle attack;

in FIG. 6 is a section A1.2-A1.2, a diagram of the blowing of the tail linear wing of an aircraft wing with free-stream mechanization elements of a flowing jet from a marching turbofan engine of FIG. 5 in the horizontal cruise flight mode, while all wing elements are in the folded position; in FIG. 7 - section A2.1-A2.1, shows a diagram of the airflow of the tail linear wing of an aircraft wing with free-stream mechanization elements from a marching turbofan engine in take-off, hovering or landing mode, including the main wing profile, a rotary flap, a retractable flap, the flaps are rotated and extended at the optimum angle of attack; in FIG. 8 is a section A2.2-A2.2, a diagram is shown for blowing a tail linear wing of an aircraft with free-flow mechanization elements from a marching turbofan engine of FIG. 7 in cruise flight mode, while all elements of the wing are in the folded position;

in FIG. 9 - section B1.1-B1.1, shows a diagram of the airflow of the tail linear wing of an aircraft with free-flow mechanization elements from a marching turboprop in take-off, hovering or landing mode, including the main wing profile, the first retractable asymmetric streamlined wing liner is concave convex profile, the second retractable wing liner of an asymmetric streamlined section of a plano-convex profile, while in the extended position back and down, there are both wing liners at the optimal angle of attack;

in FIG. 10 is a section B1.2-B1.2, there is shown a scheme for blowing a tail linear wing of an aircraft with free-flow mechanization elements from a marching turboprop engine of FIG. 9 in the horizontal cruise flight mode, while all wing elements are in the folded position; in FIG. 11 is a section B2.1-B2.1, a diagram is shown of blowing a tail of an aircraft wing with mechanization by a free-flowing outflowing jet from a marching turboprop in take-off, hovering or landing mode, including the main wing profile, a rotary flap, a retractable flap, the flaps are rotated and extended at the optimum angle of attack; in FIG. 12 is a section B2.2-B2.2, there is shown a scheme for blowing a tail linear wing of an aircraft with free-flow mechanization elements from a marching turboprop engine of FIG. 11 in cruise flight mode, while all wing elements are in the folded position;

in FIG. 13 - section A * 1.1-A * 1.1, shows a diagram of the airflow of the angular and longitudinal lateral sections of the front integral wing of the aircraft with free-flow mechanization elements from the side turbofan engine in the take-off, hover or landing mode, including the main wing profile, the first extendable wing liner asymmetric streamlined section of a concave-convex profile, the second retractable wing liner of an asymmetric streamlined section of a flat-convex profile, while in the extended position, back and down, n both wing flaps come at an optimal angle of attack;

in FIG. 14 is a section A * 1.2-A * 1.2, a diagram of the transverse profile of the angular and longitudinal lateral sections of the front integral wing of the aircraft with the mechanization elements of FIG. 13 in the horizontal cruise flight mode, while all wing elements are in the folded position;

in FIG. 15 is a section A * 2.1-A * 2.1, a diagram of the airflow of the angular and longitudinal lateral sections of the front integral wing of the aircraft with elements of mechanization by the flow of a flowing jet from a turbofan engine in take-off, hover or landing mode, including the main wing profile, a rotary flap, extendable flap, while the flaps are turned and extended at the optimal angle of attack;

in FIG. 16 is a section A * 2.2-A * 2.2, a diagram of the transverse profile of the angular and longitudinal lateral sections of the front integral wing of the aircraft with the mechanization elements of FIG. 15 in cruise flight mode, while all the elements are in the folded position;

in FIG. 17 - section B * 1.1-B * 1.1, shows a diagram of the blowing of the angular and longitudinal lateral sections of the front integral wing of the aircraft with free-stream mechanization elements of a turbulent engine in take-off, hovering or landing mode, including the main wing profile, the first asymmetric retractable wing liner a streamlined section of a concave-convex profile, the second retractable wing liner of an asymmetric streamlined section of a flat-convex profile, while in the extended position back and down, there are both undercuts ka at the optimum angle of attack;

in FIG. 18 is a section B * 1.2-B * 1.2, a diagram is shown for blowing the transverse profile of the angular and longitudinal lateral sections of the front integral wing of the aircraft with the mechanization elements of FIG. 17 in the horizontal cruise flight mode, while all elements of the wing are in the folded position;

in FIG. 19 - section B * 2.1-B * 2.1, shows a diagram of the airflow of the angular and longitudinal lateral sections of the front integral wing of the aircraft with free-flow mechanization elements from a turboprop in take-off, hovering or landing mode, including the main wing profile, a rotary flap, extendable flap, while the flaps are turned and extended at the optimal angle of attack;

in FIG. 20 is a section B * 2.2-B * 2.2, a diagram of the transverse profile of the angular and longitudinal lateral sections of the front integral wing of the aircraft with the mechanization elements of FIG. 19 in cruise flight mode, while all the elements are in the folded position. In the drawings, the positions indicated:

pos. 1 - fuselage cigar streamlined shape;

pos. 2 - marching turbofan engine;

pos. 3 - rotary turbofan engine;

pos. 4 - mid-flight turboprop engine;

pos. 5 - rotary turboprop engine;

pos. 6 - console for mounting a rotary turbofan engine;

pos. 7 - console with a rotary platform for mounting a rotary turboprop engine;

pos. 8 - supporting console for fastening the mid-flight engine in the rear of the fuselage;

pos. 9 - frontal section of the front integral wing;

pos. 10 - corner section of the front integral wing;

pos. 11 - side section of the front integral wing;

pos. 12 - wing supporting console with mechanization elements in the rear of the fuselage;

pos. 13 - vertical console;

pos. 14 - horizontal tail;

pos. 15 - the main profile of the transforming wing;

pos. 16 - the first wing liner of the transformable wing;

pos. 17- second wing liner of the transformable wing;

pos. 18 - rotary flap transformable wing;

pos. 19 - extendable flap transform wing; 2

+ Mp ^Z - lifting vertical reactive moment relative to the center of gravity of the aircraft.

Claims (1)

Aircraft with a shortened or vertical take-off and landing, including a cigar-shaped streamlined fuselage, wings with mechanization elements to change the aerodynamic characteristics of the wing, a power plant of four or more propeller, or turboprop, or turbofan engines, an integral control system, while in vertical lift mode , hovering and landing, a total balanced balance of the lifting jet moments created by the flows of the outgoing jets from the screw is created motor, or turboprop, or turbofan engines aimed at wing sections with mechanization elements, characterized in that for creating lifting reactive moments, at least in two directions, in the nose of the fuselage there are two load-bearing wing consoles of integral shape on both sides of the fuselage from the frontal section of the integral wing, the corner section of the integral wing with the elements of mechanization, the longitudinal side section of the integral wing with the elements of mechanization, the connections of adjacent sections of the front integral wing are made streamlined lekally jointed, while the frontal section of the front integral wing has a streamlined shape lekalno articulated with the surface of the fuselage, while the corner section of the front integral wing is made either rectilinear in plan at an angle to the longitudinal axis of the fuselage in the form of an annular sector in plan with an angle of the annular sector of 50 deg. up to 90 degrees. Or in the form of a sector of an annular polygon in terms of described or inscribed in an annular sector with an angle of 50 degrees. up to 90 degrees., while the longitudinal side section of the front integral wing is made straight in plan, in the direction coinciding with the longitudinal axis of the fuselage, while the corner and side sections or only the side section of the front integral wing are used in take-off, hover and landing mode to create lift reactive moments relative to the center of gravity of the aircraft and are located in the region of the incoming flow of the flowing jet from rotary propeller, or turboprop, or turbofan engines d.

Images