The invention relates to aviation equipment.

Background Art

The conventional wing is used in aircraft in the form of a lift generating airfoil. The flow of air particles around the wing creates pressures different in magnitude on its upper and lower surfaces caused by different speeds of streams above and below the wing and resulting in creating the lifting force (for instance, see references: 1) New Polytechnic Dictionary ed. by A. Yu. Ishlinsky. - Moscow: Research Publishing "Bolshaya Rossiyskaya Entsiklopediya", 2000. - p. 36; 2) Lift (force) Wikipedia. /[Electronic resource]. - Access mode: https://en.wikipedia.org/wiki/Lift (force) (date of access: 04.03.2021)).

The air flow around the wing is a three-dimensional nonlinear process. The lifting force of the wing depends on its area, section, planform shape, as well as on the angle of attack, air speed, viscosity and density, and on other physical factors. When a wing is moving in the air flow, the air layers and the wing upper and lower surfaces interact. The air flow moving along the wing upper surface gets attracted to it and moves along it even after the profile inflection due to the effect of viscosity forces, which is known as the Coanda effect (for instance, see references: 1) Loytsyansky, L. G., Fluid Mechanics. - Moscow: Drofa Publishing, 2003, 7 ^th edition, p. 504-507; 2) Caroline Lubert. On Some Recent Applications of the Coanda Effect. International Journal of Acoustics and Vibration, Vol. 16, No. 3, p. 144, 2011). The increase of the wing lifting force due to the Coanda effect is possible by virtue of the forced increase of the air flow rate on the wing upper surface by the fan air blower.

One of the well-known is the aerodynamic device consisting of a Custer channel wing and a propeller engine (see: 1) Bowers P. Unconventional Aircraft. - Moscow: Mir, 1991 (Rus). pp. 137-138; 2) Patent US 2,691,494, Cl. 244-12, date of publication: Oct. 12, 1954). The Custer channel wing is a semi-circular airfoil of a channel or "half barrel" shape. Furthermore, in its section along the airflow, the channel wing has an aerodynamic contour. Above the Custer channel wing, there is a propeller engine, while the prop plane is located at the airfoil trailing edge. The propeller sucks the air into the channel creating the increase of the air flow rate above the airfoil and thus increases the wing lifting force.

The closest analogous solution (prototype) is an aerodynamic device which has a fan air blower and an aerodynamic special-shaped wing located under the blower, which is connected to it by mechanical components and designed in the form of a double-curved open surface made up by a system of longitudinal grooves along the entire wing surface and with a vertical longitudinal plane of symmetry. Along the trajectory of the air flow, the wing has a convergent segment and a divergent segment, between the convergent and the divergent segments there is a smooth transitional segment. The system of longitudinal grooves of the wing consists of the central grooves provided in the wing central part and of lateral grooves provided in the wing side parts. At the boundary ridges which divide the longitudinal grooves, the vertices of the central and lateral grooves are rounded, in so doing, the generatrix curvature radii for the groove vertices are smaller than the generatrix curvature radii for the groove lower parts. The wing outlines have end elements, in the transitional and the di vergent segments of the wing lower surface which is not blown by air, there is a controlled drive system for the wing surface cambering and area changing. The divergent segment tip on the wing trailing edge has a deflectable controlled element whose purpose is similar to that of the conventional wing plain flap. (This prototype is described in detail in the following titles of protection for the invention: i) Innovation Patent of the Republic of Kazakhstan No. 29950 “Aerodynamic Device”, date of publication:

15.06.2015; 2) Patent of the Republic of Kazakhstan No. 29950 “Aerodynamic Device”, date of publication: 30.03.2017; 3) Patent EA No. 027683 “Aerodynamic Device”, date of publication: 31.08.2017; 4) Patent EP No. 3077282 “Aerodynamic Device”, date of publication: 27.12.2017; 5) Patent US No. 10,569,856 “Aerodynamic Device”, date of publication: Feb. 25. 2020); 6) Patent IL No. 248596 “Aerodynamic Device”, date of publication: 31.03.2020),

The technical result of the well-known analogues with an unconventional wing is creating the lifting force by employing the Coanda effect.

A common drawback of the above aerodynamic devices is underutilization of air viscosity and compressibility as well as insufficiently effective choice of the wing upper surface shape, which is interacting with the air flow _' and acts as an underlying surface in relation to the air flow, which results in low efficiency of the air flow power use. The lifting force induced on the wing surface is reducing due to the high radial speeds of the air flow from the fan that contribute to separation of the flow from the wing upper surface and dissipation of energy into the ambient atmosphere. Due to the motion of the aerodynamic device in the atmosphere, the incoming flow of the external environment has a strong effect on the air flow induced by the blower, and this interaction contributes to a partial loss of the power expended by the blower.

Summary of invention

An object of this invention is to develop a new aerodynamic device which can obviate the above drawbacks of conventional devices, increase the efficiency of the air flow power use in the process of air flowing around the wing, and increase the efficiency of the lifting force by virtue of:

1) extension of underlying surface area on the divergent segment of the wing for more reliable and stable attachment of the air flow to the wing upper surface;

2) formation of a conical shape of the air flow pressed against the longitudinal axis;

3) decrease in the radial component in the dynamic air pressure, which contributes to conversion of part of the flow rotation power into die translational energy of the air flow movement along the wing;

4) decrease in the negative effect created by the incoming flow of the external environment in the fan operation area and creation of injection suction of the air mass from the surrounding environment moving above the wing which adds the number of air particles creating an additional force impulse.

Another object of the present invention is to extend the range of aerodynamic devices for aviation through providing a specific unconventional device.

For this purpose, the aerodynamic device has a fan air blower and an aerodynamic special-shaped wing located under the blower, connected to if and designed in the form of a double-curved open surface made up by a system of longitudinal grooves along the entire wing surface and with a vertical longitudinal plane of symmetry, along the trajectory of the air flow; the wing has a convergent segment and a divergent segment, between the convergent and the divergent segments there is a smooth transitional segment; the system of longitudinal grooves of the wing consists of the central grooves provided in the wing central part and of the lateral grooves provided in the wing side parts; at the boundary ridges which divide the longitudinal grooves, the vertices of the central and lateral grooves are rounded, in so doing, the generatrix curvature radii for the groove vertices are smaller than the generatrix curvature radii for the groove lower parts; the wing outlines have end elements; in the transitional and the divergent segments of the wing lower surface which is not blown by air, there is a controlled drive system for the wing surface cambering and area changing; the divergent segment tip on the wing trailing edge has a deflectable control ed element; in accordance with the invention, the fan air blower is designed as a two-stage fan with radially positioned stage blades that have an aerodynamic contour in the cross-sectional area; in so doing, the fan is provided with a coaxially mounted geared engine which is responsible for the different direction of the blades rotation of the first and second fan stages and different rotational speeds. For air flow straightening, the device additionally contains a circular flow straightener mounted coaxially with the fan between the fan and the wing leading edge, the flow straightener contains a shrouding ring which has an aerodynamic contour in the cross-sectional area whose leading edge is placed towards the fan, on the shrouding ring there is a system of radially positioned vanes which have an aerodynamic contour in the cross-sectional area whose leading edge placed towards the fan. To prevent the dissipation of air flow energy, there is a cylindrical fairing mounted coaxially with the fan in front of the wing leading edge, the fairing is designed as a framing casing inside which there are a circular flow straightener and a fan. In so doing, the cylindrical fairing is mechanically connected to the wing and the shrouding ring. At the divergent segment of the wing at the boundary ridges which divide the longitudinal grooves, additional conical grooves are longitudinally made, starting from the points located at the line of the tops of the ridges and ending at the wing trailing edge, the depth and the area of the additional conical grooves are smoothly increasing towards the wing trailing edge. For the two-stage fan, the relation between the diameter of the circle defined by the blades of the second stage which is the closest to the wing leading edge and the diameter of the circle defined by the blades of the first stage (the farthest stage from the wing leading edge) - D ₂ /D ₁ - lies in the range from 0.60 to 0.90, in so doing, the number and the shape of the stage blades are established depending on the specific purpose of the device for its efficient operation. For the circular flow straightener, the relation between the diameter of the shrouding ring and the diameter of the circle defined by the blades of the second stage (D _B /D ₂ ) lies in the range from 0.80 to 1.10, for the system of radially positioned vanes located on the shrouding ring, the relation between the length of the vane and the diameter of the shrouding ring L _B /D _B lies in the range from 0.10 to 0.25, in so doing, the number and the shape of the radial vanes located on the shrouding ring are established depending on the specific purpose of the device for its efficient operation. For the cylindrical fairing, the relation between its internal diameter and the diameter of the circle defined by the blades of the first fan stage D _F /D ₁ lies in the range from 1.05 to 1.10, and the relation between the internal diameter of the fairing and the diameter of the circle describing the wing leading edge (D _F /D _K ) lies in the range from 0.80 to 0.90. For the additional conical grooves, radii Ro of the cone base in relation to (in comparing the values) generatrix curvature radii R for the longitudinal groove lower parts lies in the range from 0 to R. For the divergent segment of the wing, the relation between length L _AB of line AB which lies in the plane of symmetry of the additional conical groove, where points A and B are accordingly related to the start and the end points of the additional conical groove, and length Leo of line CD which lies in the plane of symmetry of the central groove, where points C and D are accordingly related to the start and the end points of the divergent segment, L _AB /L _CD lies in the range from 0.30 to 0.80.

The invention is illustrated, by way of example, in the accompanying scheme drawings which show one of the possible preferred embodiments of the invention. These drawings have sufficient detail for understanding the essence of the invention, it should be noted that In the following, for the sake of clarity of the disclosure of the invention: 1) each separate figure shows primarily only those device elements which are necessary for illustrating the essence of this or that part of the invention description (without extra dements which can be conceptually omitted), in so doing, the mechanical elements which connect the main units of the device are not numbered on the figures so as not to clutter them with unnecessary inscriptions, since the designation of these mechanical elements for mechanical connection is perfectly clear; 2) besides, in characterizing some structural components of the device in their description and claims, if is indicated that there is a possibility for them to implement a certain function, which complies with the international patent rules for the “Device" category.

Brief Description of Drawings The figures show a fan air blower as a two-stage fan 1 (position 1) which is provided with a coaxially mounted geared engine (which - geared engine - is conceptually omitted on the figures), which is responsible for the different direction of the blades rotation of the fan 1 first 2 and second 3 stages and different rotational speeds (in so doing, it should be considered that fire blades of the second 3 fan stage are the closest to the wing 4 leading edge and the blades of the first 2 stage are located farther from the wing 4 leading edge); aerodynamic wing 4 mechanically connected to blower 1 ; convergent segment 5 of wing 4; transitional segment 6 of wing 4; divergent segment 7 of wing 4; central grooves 8; lateral grooves 9; boundary ridges 10 which divide longitudinal grooves 8 and 9; groove vertices 11; groove lower part 52; deflectable controlled element 13; controlled drive system 14 for cambering and area changing of the wing 4 transitional 6 and divergent 7 segments; end elements 15; additional conical grooves 16 of wing 4; circular flow straightener 17 which contains shrouding ring 18 with radial vanes 19 on it; cylindrical fairing 20 which is mechanically connected to wing 4 and shrouding ring 18,

Fig. 1 is a structure of the whole device and its visual image which shows the main of the above elements: positions 1-4, 8-10, 13, 16, 17, 20.

Fig. 2 is a side view of the device with the longitudinal section which shows positions 5-7, 14, and 20. Fig. 2 shows the following dimensions: diameter D ₂ of the circle defined by the blades of the second fan 1 stage 3 which is the closest to the wing 4 leading edge; diameter D ₁ of the circle defined by the blades of the first fan 1 stage 2 (the farthest stage from the wing 4 leading edge); internal diameter D _F of cylindrical fairing 20.

Fig. 3 is a device; view A with positions 2 and 3. Fig. 3 shows diameter D _K of the circle describing the wing 4 leading edge.

Fig. 4 is a wing, section C-C with positions 11, 12. Fig. 4 shows the following values: generatrix curvature radii R for groove lower part 12, and radii Ro of the cone base for additional conical groove 16.

Fig. 5 is a device, section B-B with positions 2, 3.

Fig. 6 is shrouding ring 18 with radial vanes 19 on it; axonometric drawing. Fig. 6 shows the following values; diameter D _B of the shrouding ring and length L _B of the vane.

Fig. 7 is a wing, axonometric drawing with positions 10, 15, 16. Fig. 7 shows points A, B, C, D, lines L _AB and L _CD where points A and B are located on line AB which lies in the plane of symmetry of additional conical groove 16, and they are accordingly related to the start and end points of additional conical groove 16. Points C and D are located on line CD which lies in the plane of symmetry of central groove 8, and they are accordingly related to the start and end points of divergent segment 7.

Fig. 8 is an aircraft option.

Modes for Carrying out the Invention

The operation of the proposed aerodynamic device and the device described in detail in the above prototype are mostly identical due to the similarity of some of their structural elements (as indicated in the prior art of the proposed claims), except for some new distinctive elements implemented into the present object which have changed the air flow and increased, as compared to the known objects, the efficiency of the air flow power use in the process of the air flow around wing 4, as well as increased the lifting force, namely:

1) implementation of additional conical grooves 16 has significantly increased the area of the surface welted by the air flow of divergent part 7 of wing 4, in so doing, the rate of the air flow decreasing in stages along wing 4 contributes to more reliable attachment of the air flow to the wing 4 upper surface;

2) implementation of circular flow straightener 17 has allowed to decrease the radial component in the dynamic air pressure converting part of the flow rotation power into the translational energy of the air flow moving along the wing;

3) implementation of the two-stage fan has contributed to the creation of the air flow shape pressed against the longitudinal axis, thereby decreasing dissipation of energy into the surrounding environment;

4) implementation of cylindrical fairing 20 has decreased the negative effect created by the incoming flow of the external environment in the fan 1 operation area and contributed to injection suction of the air mass from the surrounding environment moving above wing 4, which adds the number of air particles around wing 4, thus, creating an additional force impulse.

The proposed aerodynamic device operates in the following way (Fig. 1-8).

The air from the surrounding environment gets sucked into cylindrical fairing 20 by the operation of two-stage fan 1 connected to wing 4. Cylindrical fairing 20 is designed as a framing casing inside which there are fan 1 and circular flow straightener 17. Cylindrical fairing 20 is mechanically connected to wing 4 and shrouding ring 18 of circular flow straightener 17. Two-stage fan 1 (whose blade of the second 3 stage is shorter than the blade of the first 2 stage and, accordingly, describes the circle of the less diameter: D ₂ is less than D ₁ ) has blades positioned along the air flow direction which rotate in different directions in order to press the air flow against the longitudinal axis of two-stage fan 1. In so doing, the number and the shape of the stage 2 and 3 blades are established depending on the specific purpose of the de vice for its efficient operation. Cylindrical fairing 20 prevents dissipation of energy of the air flow coming from the stage 2 and 3 blades of fan 1 into the surrounding environment. Circular flow straightener 17 is mounted behind the second stage 3 of fan 1 (when looking at the flow from left to right) and contains shrouding ring 18 which has an aerodynamic contour in the cross-sectional area whose leading edge is placed towards fan 1. On the internal surface of shrouding ring 18, there is a certain number of radially positioned vanes 19 which have an aerodynamic contour in the cross-sectional area whose leading edge is placed towards fan 1. In so doing, the number and the shape of radial vanes 19 on shrouding ring 18 are established depending on the specific purpose of the device for its efficient operation. The air flow coming from blades 2 and 3 of fan 1 encounters flow straightener 17 in its path and partially loses its rotation power, by converting it into the translational energy of the air flow moving along the longitudinal axis of the aerodynamic device. Then, the high-energy air flow, when passing through convergent segment 5 of wing 4, interacts with its underlying surface due to the effect of viscosity forces, according to the Coanda effect. The special shape of longitudinal grooves 8 and 9 of convergent segment 5 of wing 4 contributes to the movement of flow particles along the direction of transitional segment 6 of wing 4 along with the simultaneous process of jets (layers) redistribution. The air flow fills the entire volume of convergent segment 5 and starts to additionally inject air particles from the surrounding environment. The air flow passes through transitional segment 6 of wing 4 along the direction of longitudinal grooves 8 and 9 and reaches the underlying surface of divergent segment 7 of wing 4. The structure of wing 4 on the way to its divergent segment 7 has geometrical shapes complied with those which are presented in the prototype. Due to the reduction of the air flow rate on the underlying (in relation to the flow) surface of divergent segment 7, for the attached flow around the surface, it is necessary to meet the condition of the positive area increment for the “wetting” flow. With this purpose, additional conical grooves 16 are longitudinally made on the surface of divergent segment 7 (see Fig. 1, 4 and 7), which contributes to reduction of the intensity of the displacing thickness of the air flow boundary layer. In so doing, it contributes to more reliable and stable attachment of the air flow to the surface of divergent segment 7, which, in its turn, ensures more stable creation of lifting force on wing 4. The optimal shapes of additional conical grooves 16 are determined by calculation (using numerical methods) and by experiments and established depending on the specific purpose of the aerodynamic device. Therefore, the proposed ranges used for the additional conical grooves are optimal.

Cambering and area changing of the wing transitional segment 6 and divergent segment 7 are achieved by the special design and/or by using special elastic and resilient materials. In the proposed device, as in the prototype, aerodynamic wing 4 is provided with a system of controlled drives 14 for the wing 4 surface cambering and area changing, which ensures meeting the condition of the positive increment of the wing 4 underlying surface area over the wing 4 length, longitudinally along the flow, as well as for generating control forces and moments during various flight modes and conditions.

Optimization of the other proposed design characteristics of the aerodynamic device was carried out similar to that, done for the additional conical grooves by means of the conventional design-theoretical methods and model tests established in fluid mechanics (Encyclopedic Dictionary of Physics / ed. by A. M. Prokhorov. - Moscow: Sovetskaya Entsiklopedia, 1983. - p. 928; Krasnov, N. F., Aerodynamics. Part I. Theoretical Framework. Airfoil and Wing Aerodynamics. Technical college textbook. - Moscow, Vysshaya Shkola, 1976. - p, 384; Krasnov, N. F., Aerodynamics. Part II. Aerodynamics Technology. Textbook for technical college students. — 3 ^rd edition, revised and enlarged. — Moscow, Vysshaya Shkola, 1980. - p. 416). In so doing, it has been established that all the proposed ranges are optimal. In other eases, beyond these optimal ranges, the efficiency of utilizing the air flow power used for generating the wing resultant lifting force declines by at least 10%.

The proposed aerodynamic device makes it possible to create vertical take-off and landing aircrafts, which can fly forward and have a hovering mode at any point in the airspace with a limitation in the flight height. With using the proposed aerodynamic device, it becomes possible to apply a modular principle in order to create aircrafts with different weight-lifts and purposes for use. If the aerodynamic device is used as a wing unit, which contains all the proposed elements, and supplemented with a universal attaching device in order to attach it to the load frames of different weight-lift, providing the load frames with the different number of such wing units, it becomes possible to create vertical take-off and landing aircrafts of different weight-lift, for example, as it is shown on Fig. 8. A similar principle is used in the creation of different automobile lifting vehicles, when a large number of wheeled automobile bridges (axles) are connected into one load-bearing unit.