An electromagnetic automatic tilt for changing the pitch angle of a helicopter

Abstract

The present application relates to the field of helicopter design, in particular to an electromagnetic automatic tilt device for changing the pitch angle of a helicopter. The device comprises a moving ring and a stationary ring, which are connected by a bearing. The moving ring comprises a total pitch control coil and a cyclic pitch control coil. The total pitch control coil changes the size and direction of the magnetic field by changing the current size and direction through the coil, which drives the permanent magnet on the variable pitch rocker to move upward or downward simultaneously, thereby changing the blade installation angle. The cyclic pitch control coil is composed of several iron cores and coils with regular changes in the number of turns and winding direction, which makes the magnetic force change periodically. A permanent magnet is embedded in the inner ring of the moving ring. The automatic tilt device has a simplified mechanical structure and weight, and the control line system between the control stick and the total pitch lever and the automatic tilt device is replaced by electrical signal control, which greatly reduces the weight of the helicopter. The present application also reduces the corresponding actuator (rudder, etc.) and the variable pitch pull rod, which helps to improve the performance of the helicopter.

Description

Technical Field

[0001] This invention relates to the field of helicopter design, specifically to an electromagnetic automatic swashplate for changing the pitch angle of a helicopter rotor blade. Background Technology

[0002] Currently, the vast majority of helicopter automatic swashplates are purely mechanical in structure, mainly consisting of a moving ring, a stationary ring, a ball joint, bearings, an anti-torsion arm, and a torque arm. They are complex in structure, heavy in weight, and require extremely high manufacturing precision for the ball joints. If the ball joints are not manufactured to the required standard, the automatic swashplate may jam, seriously affecting flight safety. Summary of the Invention

[0003] An electromagnetic automatic swashplate suitable for helicopters is proposed, which simplifies the structure of the automatic swashplate, reduces the weight of the helicopter, and improves reliability.

[0004] Technical solution

[0005] An electromagnetic automatic swashplate for changing the pitch angle of a helicopter rotor comprises a moving ring and a stationary ring, which are connected as one unit by bearings. The moving ring includes a collective pitch control coil 1 and a periodic pitch control coil 2. The collective pitch control coil 1 changes the magnitude and direction of the magnetic field by changing the magnitude and direction of the current passing through the coil, thereby driving the permanent magnet on the pitch control arm to move upward or downward simultaneously, thus changing the rotor blade installation angle. The periodic pitch control coil 2 consists of several iron cores and coils with regularly varying number of turns and winding direction, causing the magnetic force to change periodically. Two permanent magnets 3 are embedded in the inner ring of the moving ring.

[0006] The stationary ring 4 has coils in two directions. When performing longitudinal and lateral manipulation, the longitudinal or lateral coils are energized respectively to change the direction of the magnetic field, attracting the permanent magnet 3 fixed on the moving ring to move in the corresponding direction, thereby changing the tilt direction of the magnetic plane.

[0007] Furthermore, the number of turns of the collective pitch control coil 1 depends on the rotor hinge torque of the specific aircraft model.

[0008] Furthermore, the periodic pitch control coil 2 is specifically configured such that: the number of coil turns increases sequentially along the azimuth angle from 0° to 90°, and the winding direction is clockwise; the number of coil turns decreases sequentially along the azimuth angle from 90° to 180°, and the winding direction is clockwise; the number of coil turns increases sequentially along the azimuth angle from 180° to 270°, and the winding direction is counterclockwise; and the number of coil turns decreases sequentially along the azimuth angle from 270° to 360°, and the winding direction is counterclockwise.

[0009] Furthermore, the two permanent magnets 3 are symmetrically distributed on the moving ring.

[0010] Furthermore, the two permanent magnets have opposite magnetic poles.

[0011] Furthermore, the two permanent magnets 3 are symmetrically distributed on the moving ring, specifically one permanent magnet is arranged at each of the azimuth angles of 0° and 180° or at the azimuth angles of 90° and 270°.

[0012] Furthermore, the distance between the permanent magnet 3 and the stationary ring should be such that no interference occurs between the permanent magnet 3 and the stationary ring when the moving ring rotates.

[0013] Technical effect

[0014] The simplified mechanical structure and weight of the automatic swashplate, compared to traditional mechanically controlled helicopters, eliminates the control lines between the control stick and collective pitch stick to the automatic swashplate, replacing them with electrical signal control, resulting in a significant weight reduction for the helicopter. Compared to conventional fly-by-wire control, this solution also reduces the corresponding actuators (servos, etc.) and pitch control sticks, contributing to improved helicopter performance. Attached Figure Description

[0015] Figure 1 Schematic diagram of the overall structure of the electromagnetic automatic tilting device;

[0016] Figure 2 Schematic diagram of magnetic field changes when the collective pitch rod is raised;

[0017] Figure 3 Schematic diagram of magnetic field change when collective pitch rod is pressed down;

[0018] Figure 4 Top view of the electromagnetic automatic tilting device;

[0019] Figure 5 Schematic diagram of the magnetic field of the periodic variable pitch control coil;

[0020] Figure 6 Component diagram of an electromagnetic automatic tilting device;

[0021] in:

[0022] Collective Pitch Control Coil-1

[0023] Periodic Pitch Control Coil-2

[0024] Permanent Magnet-3

[0025] Fixed Ring-4

[0026] Fixed-loop transverse coil -5

[0027] stationary ring longitudinal coil -6 Detailed Implementation

[0028] The present invention will be further described below with reference to embodiments. The following description represents only a portion of the embodiments of the present invention, not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0029] Collective Pitch Control: When the collective pitch lever is raised, collective pitch control coil 1 is energized. At this time, the magnetic field is as follows: Figure 2 As shown, the permanent magnet on the variable pitch rocker arm is lifted due to the repulsive force, increasing the blade installation angle; when the collective pitch lever is pressed down, the current in the collective pitch control coil 2 reverses, and the magnetic field is as follows: Figure 3 As shown, the permanent magnet on the variable pitch rocker arm is pressed down by gravity, reducing the blade installation angle. The magnitude of the energized current is proportional to the collective pitch rod stroke.

[0030] Periodic pitch control: When the control lever is pushed forward (pulled back), the stationary ring longitudinal coil 6 and the periodic pitch control coil 2 are energized. The permanent magnet 3 on the moving ring is affected by the magnetic force, causing the moving ring to rotate in the corresponding direction. The magnetic field of the automatic tilter is as follows: Figure 5 As shown, this causes the blade installation angle to change periodically, thus achieving longitudinal control of the helicopter; when the control stick is pressed to the right (left), the stationary ring lateral coil 5 and the periodic pitch control coil 2 are energized, and the permanent magnet 3 on the moving ring is affected by the magnetic field, causing the moving ring to rotate in the corresponding direction, thus causing the blade installation angle to change periodically, thus achieving lateral control of the helicopter.

[0031] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the meaning consistent with their meaning in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein. The specific embodiments described above further illustrate the purpose, technical solutions, and beneficial effects of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An electromagnetic automatic swashplate for changing the pitch angle of a helicopter rotor blade, characterized in that, It includes a moving ring and a stationary ring (4), which are connected as one unit by bearings. The moving ring includes a collective pitch control coil (1) and a periodic pitch control coil (2). The collective pitch control coil (1) changes the magnitude and direction of the magnetic field by changing the magnitude and direction of the current passing through the coil, thereby driving the permanent magnet on the pitch rocker arm to move upward or downward simultaneously, thus changing the blade installation angle. The periodic pitch control coil (2) is composed of several iron cores and coils with regularly changing number of turns and winding direction, so that the magnitude of the magnetic force changes periodically. Two permanent magnets (3) are embedded in the inner ring of the moving ring. The stationary ring (4) has coils in two directions. When performing longitudinal and transverse manipulation, the longitudinal or transverse coils are energized respectively to change the direction of the magnetic field and attract the permanent magnet (3) fixed on the moving ring to move in the corresponding direction, thereby changing the tilt direction of the magnetic plane. The periodic pitch control coil (2) is as follows: the number of coil turns increases sequentially along the azimuth 0°-90° direction, and the winding direction is right-handed; the number of coil turns decreases sequentially along the 90°-180° direction, and the winding direction is right-handed; the number of coil turns increases sequentially along the 180°-270° direction, and the winding direction is left-handed; the number of coil turns decreases sequentially along the 270°-360° direction, and the winding direction is left-handed.

2. An electromagnetic automatic swashplate for changing the pitch angle of a helicopter according to claim 1, characterized in that, The number of turns of the collective pitch control coil (1) depends on the rotor hinge torque of the specific aircraft model.

3. An electromagnetic automatic swashplate for changing the pitch angle of a helicopter according to claim 2, characterized in that, There are four types of periodic pitch control coils (2).

4. An electromagnetic automatic swashplate for changing the pitch angle of a helicopter according to claim 3, characterized in that, The two permanent magnets (3) are symmetrically distributed on the moving ring.

5. An electromagnetic automatic swashplate for changing the pitch angle of a helicopter according to claim 4, characterized in that, The two permanent magnets (3) have opposite magnetic poles.

6. An electromagnetic automatic swashplate for changing the pitch angle of a helicopter according to claim 5, characterized in that, The two permanent magnets (3) are symmetrically distributed on the moving ring, specifically one permanent magnet is arranged at the azimuth angles of 0° and 180° or at the azimuth angles of 90° and 270°.

7. An electromagnetic automatic swashplate for changing the pitch angle of a helicopter according to claim 6, characterized in that, The distance between the permanent magnet (3) and the stationary ring should be such that when the moving ring rotates, there is no interference between the permanent magnet (3) and the stationary ring.

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