WO2006025765A1

WO2006025765A1 - Improvement of an aerodynamic lifting-pulling propeller

Info

Publication number: WO2006025765A1
Application number: PCT/RU2005/000426
Authority: WO
Inventors: Andrey Igorevich Akaro; Anatoly Mikhailovich Zelinsky; Mikhail Mikhailovich Medvedev
Original assignee: Obschestvo S Ogranichennoi Otvetstvennostyu 'midera-K'
Priority date: 2004-08-24
Filing date: 2005-08-12
Publication date: 2006-03-09
Also published as: RU2267445C1

Abstract

The inventive two-stage propeller (1) comprises two identical coaxial frames provided with elements for the circular movement thereof about an axis of movement in the opposite directions and at least two aerodynamic surfaces which are mounted on each frame and are provided with means for rotating each aerodynamic surface around an axis of rotation parallel to the axis of movement synchronously with the circular movement in a direction opposite to the movement of corresponding frame and means for oscillating each aerodynamic surface synchronously with the rotation around two mutually perpendicular axes which are disposed on two mutually perpendicular planes which intersect each other along the axis of rotation of the aerodynamic surfaces, wherein one surface crosses the circular movement axis and the axis of rotation of the aerodynamic surfaces. The aircraft comprises a body (53) provided with the two-stage propeller (1) mounted thereon, a propeller (54) which is arranged on the rear end of the body (53) and whose axis of rotation passes along a longitudinal plane of symmetry of the body (53) in a horizontal direction and below the center of the aircraft mass. During flying, the aircraft is exposed to the action of lifting aerodynamic and horizontal thrust forces produced by the propeller operation. The movement of the aerodynamic surfaces of one frame above the dynamic surfaces of the other frame produces a mutual translation movement thereof, which increases the lifting aerodynamic and horizontal thrust forces by using a screen effect.

Description

IMPROVEMENT OF AERODYNAMIC LIFT-DRIVING ENGINE

Technical field

The invention relates to the field of aviation technology and can be applied in aircraft with vertical take-off and landing, using aerodynamic lifting and pulling propulsion.

Prior art

Known aerodynamic lifting and propelling propulsion containing a frame with a means of movement of the frame around the circumference relative to the axis of movement and at least two aerodynamic surfaces mounted on the frame and having means to rotate each aerodynamic surface relative to the axis of rotation parallel to the axis of movement around the circumference and means to oscillate each aerodynamic surface synchronously with rotation about two mutually perpendicular axes located respectively in two mutually perpendicular s planes intersecting along the rotation axis of the airfoil, and one of the planes passes through the axis of movement along the circumference and the rotational axis of the aerofoil (RF Patent N ° 2227107, B 64 C 39/08, 2004, the closest analog).

A disadvantage of the known aerodynamic lifting and pulling propulsion is its lack of efficiency while maintaining compactness.

Known twin-screw coaxial helicopters are known, for example, the Ka-26 helicopter, comprising a hull with two coaxial rotors located on it (AM Izakson, “The Soviet orbit helicopter,” Moscow, “Mash”, p. 242-245).

However, in well-known helicopters, rotors are used that have insufficient lift creation efficiency, as a result, to obtain acceptable lift forces, it is necessary to bring considerable power to them, which leads to a decrease in the flight range and height of the helicopter.

In the proposed invention, a new two-stage aerodynamic lifting-pulling propulsion was used, which ensures high efficiency of creating both lifting force and horizontal thrust.

In the prior art, no analogs were found - the means of the same purpose, namely, vertical take-off and landing aircraft with a two-stage aerodynamic lifting and pulling propulsor.

DISCLOSURE OF THE INVENTION The invention is based on the task of creating a two-stage aerodynamic lifting-pulling propulsion, which ensures high efficiency while maintaining compactness by using the screen effect, which increases the aerodynamic lifting force and horizontal propulsion thrust

SUBSTITUTE SHEET (RULE 26) with the mutual translational motion of the aerodynamic surfaces of both stages.

The task of creating a two-stage aerodynamic lifting and pulling propulsion is solved by the fact that in a two-stage aerodynamic lifting and pulling propulsion containing two identical coaxial frames with means for moving the frames around the circumference relative to the axis of motion in opposite directions and at least two aerodynamic surfaces mounted on each of frames and having means for rotating each aerodynamic surface relative to the axis of rotation parallel to the axis of movement synchronously with the movement around the circumference opposite to the movement of the corresponding frame and means for oscillations of each aerodynamic surface synchronously with rotation about two mutually perpendicular axes located respectively in two mutually perpendicular planes intersecting along the axis of rotation of the aerodynamic surface, and one of the planes passes through the axis of circumference and the axis of rotation aerodynamic surface.

The implementation of a two-stage aerodynamic lifting-pulling propulsion containing two identical coaxial frames with means for moving the frames around the circumference relative to the axis of movement in opposite directions and at least two aerodynamic surfaces mounted on each of the frames and having means for rotating each aerodynamic surface relative to the axis of rotation parallel to the axis of movement synchronously with the movement in a circle in the direction opposite to the movement of the corresponding frame and the means for oscillation This aerodynamic surface synchronously rotates about two mutually perpendicular axes located respectively in two mutually perpendicular planes intersecting along the axis of rotation of the aerodynamic surface, and one of the planes passes through the axis of circumference and the axis of rotation of the aerodynamic surface provides translational (without rotation) aerodynamic surfaces relative to the air on each of the frames and the uniform distribution of aerodynamic forces on the aerodynamic th surface, leading to high efficiency lift. The oscillation of each aerodynamic surface provides simultaneously with the creation of lifting force the creation of horizontal thrust. The coaxial arrangement of two frames with aerodynamic surfaces provides a compact propulsion and allows you to use the screen effect that occurs when aerodynamic surfaces move one above the other, increasing the lifting force and horizontal thrust.

SUBSTITUTE SHEET (RULE 26) The basis of the invention is the task of creating for the first time an aircraft of a vertical take-off and landing with a two-stage aerodynamic lift-and-pull propulsion unit.

The task of creating an aircraft of vertical takeoff and landing with a two-stage aerodynamic lifting and pulling propulsion is solved by the fact that an aircraft of vertical takeoff and landing with a two-stage aerodynamic lifting and pulling propulsion includes a body with a two-stage propeller mounted on it, mounted on the tail end of the hull, the axis of rotation which passes in the longitudinal plane of symmetry of the hull horizontally and below the center of mass of the aircraft.

A vertical take-off and landing aircraft with a two-stage aerodynamic lifting-pulling propeller, comprising a hull with a two-stage propeller installed on it, a screw mounted on the hull tail section, the axis of rotation of which runs horizontally below the center of mass of the aircraft and allows flight of the aircraft and at the same time compensate for the moment of diving by the force created by the propeller passing below the center of mass of the ny device.

The choice of the distance from the center of mass to the line passing through the axis of rotation of the screw is determined from the condition of ensuring the balance of forces acting on the aircraft.

Brief description of the invention

FIG. 1 shows a top view of the upper frame of a two-stage aerodynamic lifting-pulling propulsor; in fig. 2 - side view of the aerodynamic lifting and pulling propulsion (without aerodynamic surfaces); in fig. 3 is a side view of a part of a two-stage aerodynamic lift-and-pull propulsion unit with an aerodynamic surface; in fig. 4 is a view A of FIG. 3; in fig. 5 is a side view of the upper half of the central part of a two-stage aerodynamic lift-pull propulsor; in fig. 6 is a view B in FIG. five; in fig. 7 is a view of B in FIG. five; in fig. 8 is a general view of a vertical take-off and landing aircraft with a two-stage aerodynamic lift-and-pull propulsor; in fig. 9 is a diagram of aerodynamic forces acting on an aircraft in horizontal flight.

BEST MODE FOR CARRYING OUT THE INVENTION A two-stage aerodynamic lifting-pulling propulsion unit 1 contains identical coaxial frames 2 and 3 (upper and lower) with means for moving the frames around the circumference relative to the axis of motion 4 in opposite directions to each other.

SUBSTITUTE SHEET (RULE 26) relative to the other, made for example in the form of an output shaft 7 (Fig. 2) of a motor connected to it (not shown) driving the output shaft 7 and the gearbox, one bevel gear 8 of which is fixed to the output shaft 7, and the other two kinematically connected bevel gears 9 and 10, mounted respectively on the tubular rod 11 attached to the frame 2 and the rod 12 mounted on the frame 3.

Frames 2 and 3 are located at a minimum distance from each other providing free movement of the aerodynamic surfaces 13 at each of the stages of the propeller. At least two aerodynamic surfaces 13 are installed on each of the frames 2 and 3 and have means for rotating each aerodynamic surface 13 relative to the axis of rotation 14 parallel to the axis of movement 4 synchronously with the circumferential movement and means for oscillation of each aerodynamic surface 13 synchronously with rotation relative to two mutually perpendicular axes 15 and 16, located respectively in two mutually perpendicular planes intersecting along the axis of rotation 14 of the aerodynamic surface 13, and one of the planes it passes through the axis of motion 4 along the circumference and the axis of rotation 14 of the aerodynamic surface 13.

The means for rotating each aerodynamic surface 13 can be made, for example, in the form of a tubular rod 17 (Fig. 2 and 3) fixed to the body 18 of the aircraft, attached to the tubular rod 17 of the setting gears 19 and 20, kinematically associated with them, respectively, gears 21 and 22 attached to the corresponding swinging sliding shafts 23 and 24, at the ends of which are fixed bevel gears 25. On each aerodynamic surface 13 on its central part there is a conical driven gear wheel 26 kine aticheski connected with a conical pinion 25. Each extensible rocker shaft 23 and 24 attached to the corresponding frame 2 and 3. Swinging sliding shafts 23 and 24 can be made with a universal joint.

Means for oscillations of the aerodynamic surface can be performed, for example in the form of a copier 27 (Fig. 3,4,5 and 6) deviations in the tangent plane and a copier 28 deviations in the radial plane, made in the form of flat rings and installed respectively on the axes 29 and 30 deviations copiers 27 and 28 with the possibility of rolling. The axis 29 of the deviations of the copier 27 is installed on the coupling 5, which in turn is installed on the tubular rod 17 to move along the tubular rod 17. The axis 30 of the deviations of the copier 28 is mounted on the tubular rod 17. On the edge of each of the copiers 27 and 28, the pushers 31 are installed respectively and 32 offset from each other by 90 °. Pushers 31 and 32 using the appropriate

SUBSTITUTE SHEET (RULE 26) lever gears are connected to the aerodynamic surface 13. The lever gears can be made in the form of translators directions 33 and 34 fixed on the casing 35 attached to the frame 3 and the corresponding inclined rods 36 and 37 and the second translators directions 38 and 39 in the vertical direction connected to the second pushers 40 and 41, ending with hinges 42 and 43, placed in the central part of the aerodynamic surface at its edges displaced from each other by 90 °.

In the central part of the aerodynamic surface 13, a ball bearing 45 is mounted, which is fixed to frame 3 by means of support 46. Aerodynamic surface 13 consists of two parts - central (fixed relative to frame 3) and peripheral with fixed bevel gear 26 fixed on it bearing 44 and mounted for rotation.

The copiers 27 and 28, as well as the clutch 5 are installed, respectively, the rods 47,48 49 control actuators (not shown) or levers of the lever control mechanism, which provide the required deviations and vibrations of the aerodynamic surface 13.

Arrows 50 in FIG. 3.5 shows the direction of the longitudinal movement of the inclined bars 36 and 37, the arrows 51 (in FIG. 5) the directions of movement of the tappets 31 and 32, and the arrows 52 the directions of the turns of the copiers 27 and 28.

Similarly, the means for oscillation of the aerodynamic surface 13 on the frame 2.

Means for movement around the circumference of each of the frames 2 and 3, means for rotating the aerodynamic surface and means for oscillation of the aerodynamic surface can be made differently, for example, as described in RF patent L ° 2227107, B 64 C 39/08, 2004. ; in the RF patent tf ° 2232105, B 64 C 39/08, 2004; international publication WO 03/086857 of 10.23.2003, B 64 C 11/46, 27/08; international publication WO 03/086858 of 10.23.2003, B 64 C 11/46, 27/08. Other embodiments of the above-mentioned means are possible according to well-known schemes. A vertical take-off and landing aircraft with a two-stage aerodynamic lifting-pulling propeller 1 comprises a housing 53 (Fig. 8) with a two-stage aerodynamic lifting-pulling propulsion 1 mounted on it, a screw 54 mounted on the tail section of the hull, the axis of rotation extending in the longitudinal plane of symmetry The body 53 is horizontal and below the center of mass of the 55 aircraft.

In the horizontal flight mode of the aircraft (Fig. 9), a two-stage aerodynamic lifting and pulling propulsor 1 creates a lifting

SUBSTITUTE SHEET (RULE 26) aerodynamic force 56 and horizontal thrust 57. The moment for diving 58 relative to the Z axis is created from horizontal thrust 57, and the compensating moment 59 is created by a thrust 60 of the screw 54 located below the center of mass 55 of the aircraft. The direction of flight is shown by arrow 61. A two-stage aerodynamic lift-and-pull propulsion operates as follows.

The frames 2 and 3 together with the aerodynamic surfaces 13 move relative to the axis of movement 4 around the circumference in opposite directions relative to each other using means for moving the frames around the circumference, for example as described in the materials of the present invention, where the movement from the output shaft 7 through the bevel gear 9, the tubular rod 11 is transmitted to the frame 2 and through the bevel gear 10, the rod 12 is transmitted to the frame 3.

At the same time, each aerodynamic surface 13 together with the movements of frames 2 and 3 around the circumference about the axis of movement 4 synchronously with the movement around the circumference rotates in the direction opposite to the movement of the corresponding frames 2 and 3 using means for rotating the aerodynamic surface, for example as described in the materials of the present invention where the movement around the circumference of the frame 3 and the frame 2 is transmitted to the gears 22 and 21 rolling over the fixed driver gears 20 and 19 and through the swinging sliding shafts 24 and 23 to the driving gears 25 transmitting rotation to the driven gears 26 mounted on the aerodynamic surfaces 13 and causing the aerodynamic surfaces 13 to rotate. Thus, the translational movement of the aerodynamic surfaces 13 relative to the air is created.

Each aerodynamic surface 13 oscillates with respect to two mutually perpendicular axes 15 and 16 synchronously with the rotation using means for oscillation of the aerodynamic surface, for example, as described in the materials of the present invention, where with fixed cam forms 27 and 28, respectively, the plungers Zl 32 fixed through the lever transmission on frame 3 and 2, slide along the edge of copiers 27 and 28 along with movement around the circumference of frames 3 and 2. When the copiers 27 and 28 move from the horizontal position, the pushers 31 and 32 perform a sinusoid The up and down movement is synchronized with the slide of the pushers 31 and 32 and, therefore, with the rotation of frames 3 and 2. Through the translators direction 33 and 34, the thrust 36 and 37, the second translator directions 38 and 39, the second pusher 40 and 41 with hinges 42 and 43, the sinusoidal displacements of the pushers 31 and 32 are translated into a sinusoidal displacement of the aerodynamic surface 13, i.e., into its oscillations in two mutually perpendicular planes - respectively in the tangent plane and in the radial plane to the aerodynamic surface 13, ensuring the creation of zonalnogo

SUBSTITUTE SHEET (RULE 26) thrust with the creation of lift. When moving the clutch 5 together with the cam 27 in the direction of movement of the pusher 31 from the rod 47, under the action of the control drives, a new position of the aerodynamic surface 13 relative to which oscillations will be made is provided, which expands the possible modes of operation of the propeller. The aerodynamic lifting forces and horizontal thrusts are created on both stages of the propeller from both frames 2 and 3 with aerodynamic surfaces 13, where due to the creation of translational movement of the aerodynamic surfaces 13 of frames 2 and 3 and the relative position of the aerodynamic surfaces one above the other, a screen effect occurs that increases the lifting force horizontal thrust. The flight of the aircraft vertical takeoff and landing with a two-stage aerodynamic lifting and pulling the propeller as follows.

A two-stage aerodynamic lifting-pulling propulsion 1 with three aerodynamic surfaces 13 at each of the steps is used. Each aerodynamic surface 13 on frame 3 moves in a circle with the frame 3 in one direction, and on frame 2 moves in a circle with the frame 2 in the opposite direction and accordingly simultaneously rotates in the opposite direction of circumference relative to the axis of rotation 14 parallel to the axis of motion 4 with an angular velocity equal to the angular velocity of the circumferential motion. A forward movement of the aerodynamic surfaces 13 is created, ensuring the uniform distribution of the aerodynamic forces over the aerodynamic surfaces 13, leading to a high efficiency of creating a lifting force. Each aerodynamic surface 13 oscillates synchronously with rotation about two mutually perpendicular axes 15 and 16, respectively located in two mutually perpendicular planes intersecting along the axis of rotation 14 of the aerodynamic surface 13, one of the planes passing through the axis of movement 4 along the circumference and the axis of rotation 14 , while from each frame 2 and 3 with aerodynamic surfaces 13 together with a lifting aerodynamic force 56, horizontal thrust 57 is also created, and the distribution of aerodynamic forces on aerodynamic surfaces remains uniform. When creating a mutual translational motion of the aerodynamic surfaces 13 of frames 2 and 3, a screen effect occurs, increasing the aerodynamic lifting force 56 and horizontal thrust 57.

During the horizontal flight of the aircraft, the lifting aerodynamic force 56 and the horizontal thrust 57 of the two-stage aerodynamic lifting-pulling propulsion 1, created during its operation, act. From the horizontal thrust 57, a moment is created for diving 58, which is balanced

SUBSTITUTE SHEET (RULE 26) compensating moment 59 created by the pitch 60 of the screw 54 located below the center of mass 55 of the device.

The proposed aircraft vertical takeoff and landing with a two-stage aerodynamic lifting and pulling propulsion allows the flight of the aircraft with high energy efficiency.

Industrial Applicability

The most successful of the present invention can be used in aircraft with vertical takeoff and landing, using aerodynamic lifting and pulling propulsion.

SUBSTITUTE SHEET (RULE 26)

Claims

Claim

1. A two-stage aerodynamic lifting and pulling propulsion device containing two identical coaxial frames with means for moving the frames in a circle around the axis of movement in opposite directions and at least two aerodynamic surfaces mounted on each of the frames and having means for rotating each aerodynamic surface about the axis rotation parallel to the axis of movement, synchronously with the movement around the circumference in the direction opposite to the movement of the corresponding frame, and means for oscillation of each aerodynamic of the surface of the aircraft synchronously with rotation relative to two mutually perpendicular axes located respectively in two mutually perpendicular planes intersecting along the axis of rotation of the aerodynamic surface, and one of the planes passes through the axis of movement around the circle and the axis of rotation of the aerodynamic surface.

2. Aircraft of vertical take-off and landing with a two-stage aerodynamic lifting-pulling propulsion device, comprising a body with a two-stage propulsion mounted on it, a screw mounted on the tail of the body, the axis of rotation of which passes in the longitudinal plane of symmetry of the body horizontally and below the center of mass of the aircraft.

SUBSTITUTE SHEET (RULE 26)