CN109018342A - One kind is verted cycloid fan swing device, vert cycloid fan rotor aircraft and its control method - Google Patents

Abstract

It verts cycloid fan swing device, vert cycloid fan rotor aircraft and its control method the invention proposes one kind, fan swing device includes the deflectable cycloid fan swing device in conjunction with the cross flow fan wing and cycloid propeller feature.Present invention incorporates both the cross flow fan wing and cycloid propeller advantages.Fan wing blade in the present invention is also the blade of cycloid propeller, which is worked when can be flown before aircraft by operating mechanism with the cross flow fan blade mode in the fan wing, and in aircraft hovering, the blade is with the work of cycloidal oar blade mode.Compared with conventional cross flow fan rotor aircraft, fan blade is adjustable when preceding winged, adapts to different flying conditions, and the ability with VTOL and hovering, compared with conventional cycloid propeller (the rolling wing) aircraft, fly that high-efficient, load-carrying is big before having many advantages, such as.The fan rotor aircraft that verts is designed as four wing modes of verting, and overcomes existing contradiction between hovering performance and preceding winged performance.

Description

A tilting cycloidal fan wing device, a tilting cycloidal fan wing aircraft and its control method

technical field

The invention relates to a military-civil dual-purpose aviation aircraft, relates to the field of aircraft design, a mechanical control system and a lift wing, in particular to an aircraft with a tilting cycloidal fan wing.

Background technique

The cross-flow fan wing is a new type of device that generates aerodynamic lift. It uses the rotating fan in front of the airfoil to generate vortex lift and thrust for flight. It has the advantages of good low-speed performance, large load, and no stall at large angles of attack. The lift generated by the fan wing is composed of two parts: one is that when the fan rotates, the flow velocity of the upper and lower surfaces of the rear half of the wing is different, resulting in a pressure difference between the upper and lower surfaces of the wing, forming the lift of the wing; the other part is because when the fan rotates, A strong eccentric vortex is generated inside the fan, resulting in a strong eccentric vortex low-pressure area, which causes a large pressure difference between the upper and lower surfaces of the arc-shaped area of the front half of the wing, forming a larger part of the wing lift, that is, the vortex lift. The fan-wing aircraft came out not long ago, and the research work is still in the initial stage of exploration. The latest research results and project progress of the fan-wing published at home and abroad are few.

The current tilting aircraft generally adopt the method of tilting the rotor, that is, a pair of rotors are installed at the end of the wing. When taking off, the rotor is horizontal to the ground, and the rotor rotates to generate lift. When flying forward, the rotor gradually tilts until it is horizontal, and the thrust Generated by the rotor, the wing generates lift. At the same time, a general tilting aircraft is a tilting two-rotor and adopts a horizontal layout. Due to the use of a simple rotor as a lift and thrust device, and the difference in the performance of the rotor in hovering and forward flight, this leads to the general tilting aircraft needing a compromise between hovering and forward flight performance, resulting in hovering performance and flat flight performance of the aircraft. Not high, reducing efficiency. Currently, the dual-rotor tilting method is used, which limits the flight time and load capacity of the aircraft.

Contents of the invention

Aiming at the above-mentioned technical problems, the present invention provides a new type of tilting cycloidal fan-wing aircraft and its working principle that simultaneously meet the requirements of vertical take-off and landing, hovering in the air, and high-altitude cruise, combining cross-flow fan wings and cycloidal propellers Advantages, the tilting aircraft is designed to tilt four wings, which overcomes the contradiction between the hovering performance and the forward flight performance, and the hovering performance, level flight performance, flight time and load are all improved.

The present invention provides a tiltable cycloidal fan wing device, comprising a cross-flow fan wing 5 and a cycloidal paddle control mechanism, the cycloidal paddle structure is arranged at the front end of the cross-flow fan wing 5, and one end of the cycloidal paddle is fixed on On the fuselage of the aircraft, the other end is connected to the leading edge of the retractable fan wing on the cross-flow fan wing; the cycloidal propeller structure controls the cycloidal propeller 1 blade through the steering gear, the steering gear linkage and the tilter. to control the hovering or forward flight of the aircraft.

Further, the cycloidal paddle structure includes a cycloidal paddle rotating part, and the cycloidal paddle rotating part includes a cycloidal paddle fixing plate 2, a cycloidal paddle 1, and a transmission shaft 3; wherein, the cycloidal paddle fixing plate 2 Located at both ends of the cycloidal paddle 1, it is used to fix the cycloidal paddle 1; the rotating part of the cycloidal paddle includes several cycloidal paddles 1, and the equiangular circumference of the cycloidal paddle 1 is fixed on the cycloidal paddle fixing plate 2; the transmission shaft 3 runs through the center of the cycloidal paddle, and transmits power to the cycloidal paddle 1 through the cycloidal paddle fixing plate 2, so that the cycloidal paddle 1 rotates around the transmission shaft 3.

Further, the steering mechanism includes a connecting plate 12, a recliner 14, a recliner connecting rod, a cycloid paddle connecting rod, an L-shaped rod, a steering gear, a steering gear connecting rod and a fixing device for a steering gear, and the transmission shaft 3 One end protrudes from the cycloidal paddle fixing plate 2, and the connecting plate 12 is fixed on the end of the transmission shaft protruding from the cycloidal paddle fixing plate 2, and the transmission shaft 3 is connected with the fixing device of the steering gear; the operating mechanism includes Several steering gears, the steering gears are evenly distributed on the transmission shaft by the steering gear fixing device, and each steering gear is connected to the tilter 14 by the steering gear connecting rod; The coordinated movement of the L-shaped rod controls the movement of the cycloidal paddle connecting rod, thereby controlling the change of the installation angle of each cycloidal paddle.

Further, the cross-flow fan wing 5 includes a retractable fan wing leading edge 18, a cycloidal paddle 1 and a cycloidal paddle control mechanism, which are devices for generating lift when the aircraft flies forward.

As a preference, the cycloidal paddle rotating part is composed of eight cycloidal paddle blades; the eight cycloidal paddle blades are arranged in an equiangular circular arrangement around the circumference.

Further, the cycloidal propeller control mechanism is provided with three identical steering gears to provide the control force, and the automatic tilter 14 controls the collective pitch and periodic pitch variable operation of the eight cycloidal propeller blades respectively.

The present invention also provides a tilting cycloidal fan wing aircraft with dual fan wings, said aircraft is provided with four tiltable cycloidal fan wing devices as claimed in claim 6, and is symmetrically installed on the two sides of the aircraft. Both sides are in the form of the cycloidal propeller structure in the front and the rear cross-flow fan wing; when the aircraft flies vertically, the cross-flow fan wing 5 is tilted to be nearly vertical to the ground, the blades work in the cycloidal propeller mode, and the aircraft generates the direction upward. When the aircraft was flying horizontally, the cross-flow fan wing 5 was tilted parallel to the ground, and the blades worked in the cross-flow fan mode, and the aircraft produced forward thrust.

And the present invention also provides the control method of tilting cycloidal fan-wing aircraft, described control method controls the posture of tilter by steering gear, drives several stages of connecting rods by tilter to convert the change of its posture into the position of cycloidal propeller blade The tilt angle changes, and the flight mode of the aircraft is controlled by the tilt of the cross-flow fan wing;

When the tilter is performing periodical variable pitch control, the periodical variable pitch of the blades works in the cycloidal propeller mode; changing the periodical variable pitch control direction can adjust the magnitude and direction of the aerodynamic force of the cycloidal propeller.

When the tilter performs collective pitch adjustment operation without periodic pitch change, the angles of all blades are the same, and it works in the cross-flow fan mode at this time; changing the size of the collective pitch adjusts the angle of the cross-flow fan blades to adjust the aerodynamic force. The size may be used to adapt to different flight conditions, making it possible to maintain a high aerodynamic efficiency.

The beneficial effects of the present invention are:

1. The tilting cycloid fan-wing aircraft overcomes the shortcomings of conventional fan-wing aircraft that cannot take off and land vertically and hover in the air, and expands the scope of use of this type of aircraft.

2. When the aircraft is flying forward, the angle of the cross-flow fan blade on the fan wing can be adjusted, which can change the size of the aerodynamic force or be used to adapt to different flight conditions, so that it can maintain a high aerodynamic efficiency in forward flight.

3. The effective combination of the fan wing and the cycloidal propeller makes the aircraft have high hovering and forward flight efficiency, and the overall performance is excellent.

4. The design of tilting four wings overcomes the contradiction between hovering and forward flight, and effectively improves the hovering efficiency and forward flight performance. And it has greatly improved in terms of load capacity and voyage time.

scope of use

In terms of civilian use, the tilting cycloidal fan-wing aircraft of the present invention can be used for aerial operations such as aerial photography and geological exploration. In military terms, the tilting cycloidal fan-wing aircraft of the present invention can be used for fire detection, Positioning, submarine search and other reconnaissance tasks. Compared with traditional unmanned aerial vehicles, the tilting cycloidal fan-wing aircraft of the present invention has greater advantages in mission execution capability because it takes into account the characteristics of both helicopters and fixed-wing aircraft.

Description of drawings

Figure 1 is a schematic diagram of the overall structure of the cycloidal propeller and the cycloidal propeller operating mechanism.

Fig. 2 is a schematic diagram of an aircraft with a tilting cycloidal fan wing.

Fig. 3 is a left side view of the cycloid paddle control mechanism.

Fig. 4 is a right side view of the cycloid paddle control mechanism.

Fig. 5 is a schematic diagram of the hovering/vertical flight state of the tilting cycloidal fan wing aircraft.

Fig. 6 is a schematic diagram of the horizontal flight state of the tilting cycloidal fan wing aircraft.

Fig. 7 is the state of the wing when the tilting cycloidal fan wing aircraft is hovering/flying vertically.

Fig. 8 is the state of the wings of the tilting cycloidal fan wing aircraft before flying.

Fig. 9 is a schematic diagram of the air flow near the wing when the tilting cycloidal fan wing aircraft is hovering/flying vertically.

Fig. 10 is a schematic diagram of the air flow near the wings of the tilting cycloidal fan wing aircraft during forward flight.

In the figure, cycloidal propeller 1, cycloidal propeller fixing plate 2, transmission shaft 3, fuselage 4, cross-flow fan wing 5, cycloidal propeller connecting rod 6, L-shaped rod 7, tilter connecting rod 8, steering gear 9 , steering gear fixing plate 10, steering gear 11, connecting plate 12, steering gear 13, tilter 14, connecting rod 15, steering gear fixing plate 16, blade rib 17, retractable fan wing leading edge 18, vertical tail 19 , Rudder 20, fan wing leading edge retractable mechanism gear 21, fan wing leading edge retractable mechanism rack 22.

Detailed ways

The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

The cycloid propeller is a new type of device that generates aerodynamic lift. The propeller rotates around the axis of the cycloid propeller and at the same time performs a pitching oscillation around the hinge. The lift is provided by periodically changing the angle of attack of the propeller at different positions in the rotating propeller system. , by changing the phase angle of the periodic variable pitch of the blade and then changing the direction of the net vector pull force, due to the unsteady flow characteristics brought about by the periodic rotation of the cycloid propeller, the stall angle of attack of the blade is increased, so that the cycloid propeller has high efficiency , low noise, and fast vector thrust changes.

Example 1

As shown in Figures 1 to 4, the present invention provides a tiltable cycloidal fan wing device, including a cycloidal paddle 1 and a cross-flow fan wing 5 connected by an operating mechanism, the cycloidal fan wing structure, It is mainly composed of a cycloidal propeller control mechanism, a cycloidal propeller rotating part and cross-flow fan wings 5 . Combining the advantages of cross-flow fan blades and cycloidal propellers.

The cycloidal paddle rotating part fixes eight or more pieces of the same cycloidal paddles 1 equiangularly and circumferentially through the cycloidal paddle fixing plate 2, and the transmission shaft 3 transmits power to the cycloidal paddle through the cycloidal paddle fixing plate 2. Paddle 1 makes eight cycloidal paddles 1 rotate around transmission shaft 3.

Described cycloidal paddle control mechanism connects the transmission shaft 3 and the steering gear fixing plate 10 through the connecting plate 12, and the steering gear 9, the steering gear 13 and the steering gear are connected by the steering gear fixing plate 10 and the steering gear fixing plate 16. 11 is fixed, the steering gear 13 controls the movement of the tilter 14 through the steering gear connecting rod 15, and the movement of the tilter 14 controls the movement of the cycloid paddle connecting rod 6 through the cooperative movement of the tilter connecting rod 8 and the L-shaped rod 7, thereby controlling the swing The angle of attack of the line paddle changes, and the steering gear 9 and the steering gear 11 respectively control the motion of the tilter 14 and the cycloid paddle connecting rod in the same manner. The cycloidal propeller control mechanism is mainly provided with three identical steering gears 9, 11 and 13, and the tilter 14 controls the collective pitch and periodic pitch change operation of eight cycloidal paddles. The cycloidal propeller operating mechanism has a simple structure and no stagnation among the mechanisms, so compared with other existing operating mechanisms, it has the advantages of higher operating efficiency, quick response and light weight.

The main function of the cross-flow fan wing 5 is to fix the cycloidal propeller 1 and the cycloidal propeller control mechanism, and it is also an aircraft lift generating device.

Example 2

Based on the above-mentioned tiltable cycloidal fan wing device, as shown in Figure 5 to Figure 8, the present invention also provides a tilting cycloidal fan wing aircraft, the tiltable cycloidal fan wing device is symmetrical in pairs Installed on both sides of the aircraft, the cycloidal propeller structure is in the form of the front cross-flow fan wing behind; when the aircraft flies vertically, the cross-flow fan wing 5 is tilted to be nearly vertical to the ground, and the blades work in the cycloidal propeller mode. The direction of lift generated by the aircraft is upward; when the aircraft is flying horizontally, the cross-flow fan wing 5 is tilted parallel to the ground, and the blades work in the cross-flow fan mode, and the aircraft generates forward thrust.

The control method controls the attitude of the oblique device through the steering gear, and then drives several stages of connecting rods through the oblique device to convert the change of its attitude into the inclination angle of the cycloid blade, and controls the flight mode of the aircraft with the inclination of the wing of the cross-flow fan;

When the tilter is performing periodical variable pitch control, the periodical variable pitch of the blades works in the cycloidal propeller mode; changing the periodical variable pitch control direction can adjust the magnitude and direction of the aerodynamic force of the cycloidal propeller.

When the tilter is operated for collective pitch adjustment without periodic pitch change, the angles of all the blades are the same, and it works in the cross-flow fan mode at this time; changing the size of the collective pitch can adjust the angle of the cross-flow fan blades to adjust the aerodynamic force The size may be used to adapt to different flight conditions, making it possible to maintain a high aerodynamic efficiency.

The cross-flow fan wing 5 can be tilted; the arc portion 18 of the leading edge of the cross-flow fan wing can be retracted into the wing 5 to reduce the aerodynamic interference to the cycloidal propeller when the aircraft is hovering. The tilting fan wing aircraft can realize hovering in the air, vertical flight and horizontal flight.

Wherein, the wing tilting mechanism can adopt the scheme in the patent CN105799934A.

Example 3

And the present invention also provides the control method of tilting cycloidal fan-wing aircraft, described control method controls the posture of tilter by steering gear, drives several stages of connecting rods by tilter to convert the change of its posture into the position of cycloidal propeller blade The tilt angle changes, and the flight mode of the aircraft is controlled by the tilt of the cross-flow fan wing;

When the tilter is performing periodical variable pitch control, the periodical variable pitch of the blades works in the cycloidal propeller mode; changing the periodical variable pitch control direction can adjust the magnitude and direction of the aerodynamic force of the cycloidal propeller.

When the tilter performs collective pitch adjustment operation without periodic pitch change, the angles of all blades are the same, and it works in the cross-flow fan mode at this time; changing the size of the collective pitch adjusts the angle of the cross-flow fan blades to adjust the aerodynamic force. The size may be used to adapt to different flight conditions, making it possible to maintain a high aerodynamic efficiency.

Fig. 9 is a schematic diagram of the air flow near the wing when the tilting cycloidal fan wing aircraft hovers/vertically flies when the aircraft is controlled; Fig. 10 is a schematic diagram of the air flow near the wing of the tilting cycloidal fan wing aircraft when it flies forward.

The tilting cycloidal fan-wing aircraft overcomes the shortcomings of conventional fan-wing aircraft that cannot take off and land vertically and hover in the air, and expands the application range of this type of aircraft. When the aircraft is flying forward, the angle of the blades of the cross-flow fan on the fan wing can be adjusted, which can change the size of the aerodynamic force or be used to adapt to different flight conditions, so as to maintain a high aerodynamic efficiency in forward flight. The effective combination of the fan wing and the cycloidal propeller makes the aircraft have high hovering and forward flight efficiency, and the comprehensive performance is excellent. The tilting four-wing design overcomes the contradiction between hovering and forward flight, effectively improving hovering efficiency and forward flight performance. And it has greatly improved in terms of load capacity and voyage time.

In terms of civilian use, the tilting cycloidal fan-wing aircraft of the present invention can be used for aerial operations such as aerial photography and geological exploration. In military terms, the tilting cycloidal fan-wing aircraft of the present invention can be used for fire detection, Positioning, submarine search and other reconnaissance tasks. Compared with traditional unmanned aerial vehicles, the tilting cycloidal fan-wing aircraft of the present invention has greater advantages in mission execution capability because it takes into account the characteristics of both helicopters and fixed-wing aircraft.

There are many specific application approaches of the present invention, and the above description is only a preferred embodiment of the present invention. It should be pointed out that for those of ordinary skill in the art, some improvements can also be made without departing from the principles of the present invention. Improvements should also be regarded as the protection scope of the present invention.

Claims (9)

1. A tiltable cycloid fan wing device, characterized in that it includes a cross-flow fan wing (5) and a cycloid paddle control mechanism, and the cycloid paddle structure is arranged on the cross-flow fan wing (5) Front end, one end of which is fixed on the aircraft fuselage, and the other end is connected with the front edge of the retractable fan wing on the cross-flow fan wing; Control the angle of the cycloidal propeller (1) blade, so as to control the hovering or forward flight of the aircraft. 2. A tiltable cycloidal fan wing device according to claim 1, characterized in that: the cycloidal paddle structure includes a cycloidal paddle rotating part, and the cycloidal paddle rotating part includes a cycloidal paddle fixing plate (2), cycloidal paddle (1), transmission shaft (3); wherein, the cycloidal paddle fixing plate (2) is located at both ends of the cycloidal paddle (1), and is used to fix the cycloidal paddle ( 1); the cycloidal paddle rotating parts include several cycloidal paddles (1), and the cycloidal paddles (1) are fixed on the cycloidal paddle fixing plate (2) at equiangular circles; the transmission shaft (3) runs through At the central position of the cycloidal paddle, the power is transmitted to the cycloidal paddle (1) through the cycloidal paddle fixing plate (2), so that the cycloidal paddle (1) rotates around the transmission shaft (3). 3. A tiltable cycloidal fan wing device according to claim 1, characterized in that: the operating mechanism includes a connecting plate (12), a tilter (14), a tilter connecting rod, a cycloidal paddle Rod, L-shaped rod, steering gear, steering gear connecting rod and fixing device for steering gear, one end of the transmission shaft (3) protrudes from the cycloid paddle fixing plate (2), and the connecting plate (12) is fixed on the transmission shaft Protrude the end of one end of the cycloidal propeller fixing plate (2), and connect the transmission shaft (3) and the fixing device of the steering gear; Distributed on the transmission shaft, and each steering gear is connected to the tilter (14) through the steering gear connecting rod; the tilter (14) controls the cycloid paddle connection through the coordinated movement of the tilter connecting rod and the L-shaped rod. The movement of the rod, thereby controlling the change of the installation angle of each cycloidal paddle. 4. A tiltable cycloidal fan wing device according to claim 1, characterized in that: the cross-flow fan wing (5) includes a retractable fan wing leading edge (18), a cycloidal paddle (1) and the cycloidal propeller control mechanism are devices that generate lift when the aircraft flies forward. The two gears (21) driven by the servo motor drive the rack (22) on the leading edge (18) of the fan wing that meshes with it. The retractable operation of the leading edge of the fan wing. 5. A tiltable cycloidal fan wing device according to any one of claims 1 to 4, characterized in that: said cycloidal paddle rotating part is composed of eight cycloidal paddle blades; said eight The blades of the cycloid paddles are arranged in a circular arrangement at equal angles to the circumference. 6. A tiltable cycloidal fan wing device according to claim 5, characterized in that: said cycloidal propeller control mechanism is provided with three identical steering gears to provide control force, and the automatic tilter ( 14) Control the collective pitch and periodic pitch variable operation of eight cycloidal propeller blades respectively. 7. Tilting cycloidal fan wing aircraft, is characterized in that, described aircraft is provided with four tiltable cycloidal fan wing devices as claimed in claim 6, is installed symmetrically in pairs on both sides of aircraft, is The cycloidal propeller structure is in the form of the cross-flow fan wing in the front; when the aircraft is flying vertically, the cross-flow fan wing (5) is tilted to be nearly vertical to the ground, the blades work in the cycloidal propeller mode, and the aircraft generates lift in the upward direction ; When the aircraft is flying horizontally, the cross-flow fan wing (5) is tilted parallel to the ground, the blades work in the cross-flow fan mode, and the aircraft generates forward thrust. 8. The control method of the tilting cycloidal fan wing aircraft according to claim 7, characterized in that: the control method controls the attitude of the oblique device through the steering gear, and then drives several stages of connecting rods through the oblique device to adjust the attitude of the oblique device. The change is converted into a change in the inclination angle of the cycloidal blade, and the flight mode of the aircraft is controlled with the tilt of the cross-flow fan wing; When the tilter is performing periodical variable pitch control, the periodical variable pitch of the blades works in the cycloidal propeller mode; changing the periodical variable pitch control direction can adjust the magnitude and direction of the aerodynamic force of the cycloidal propeller. 9. The control method according to claim 8, characterized in that: when the tilter performs collective pitch adjustment manipulation without periodic pitch change, the angles of all the blades are the same, and at this time it works in cross-flow fan mode; Adjust the angle of the cross-flow fan blades to adjust the size of the aerodynamic force or to adapt to different flight conditions, so as to maintain a high aerodynamic efficiency.