Swash-plate-free helicopter rotor system

Abstract

The utility model discloses a helicopter rotor system without a swash plate, which is arranged at the top of a helicopter and comprises a motor, variable pitch seats, blades, a propeller clamp, a propeller hub and a variable pitch hinge torsion spring, and the propeller hub is arranged at the upper end of the motor, is sleeved on a main shaft of the motor and synchronously rotates along with the main shaft of the motor to drive the variable pitch seats at the upper end and the lower end to rotate. The two sides of the pitch changing seat rotate on the ball shafts of the pitch changing U-shaped grooves, and then the propeller clamps are stirred to rotate around the propeller hub protruding shafts so as to drive the propeller blades to change the pitch. According to the swash-plate-free helicopter rotor system, the propeller hubs are driven to change the pitch by controlling the angular acceleration of the phase of the main shaft of the motor, the complexity of the mechanism and the weight of the system are reduced, and the overall reliability is improved; a symmetrical structure design is adopted, so that the stability and reliability of the rotor system are kept; the effects of variable-pitch adjustment and reset stabilization are achieved through the variable-pitch hinge torsion spring; by driving the difference variable-pitch deflection of the left and right blades, the rotor wing for generating pitching torque and rolling torque to the helicopter achieves the variable-pitch purpose.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of helicopter, especially a kind of no swash plate helicopter rotor system. BACKGROUND

[0002] The rotor of helicopter generally needs to be provided with pitch mechanism to achieve the control of posture such as forward and backward, tilt, lift and the like.The traditional helicopter rotor system usually includes automatic tilting device, and the tilting angle of blade is controlled by mechanical connecting rod transmission mechanism, so as to realize the operations such as climbing, descending, advancing and retreating of helicopter.However, this design has some shortcomings, such as large weight, low reliability and complex maintenance, etc., and meanwhile, the redundant servo motor limits the endurance time of aircraft.For micro unmanned helicopter, the weight and the complexity of mechanism are particularly sensitive, and the demand in this aspect is more prominent. SUMMARY

[0003] In view of the problems existing in the prior art helicopter rotor system, the utility model discloses a kind of no swash plate helicopter rotor system, utilize motor control system to drive hub rotation to drive both sides paddle clamp and blade rotation, further drive blade angle to deflect, this system has greatly reduced the complexity of mechanism and the weight of system and improved overall reliability.

[0004] The technical scheme adopted by the utility model is as follows: a kind of no swash plate helicopter rotor system is arranged at the top of helicopter, including motor, pitch seat, blade, paddle clamp, hub, pitch torsional spring, the hub is arranged at the upper end of motor and is fixedly sleeved on motor spindle;Further, the hub is set as circular ring structure and symmetrically sets convex shaft and tab;The pitch seat is square and is provided with through hole in the middle, which is matched with the outer diameter size of motor spindle, and the pitch seat is installed on the upper and lower ends of hub and is fixedly sleeved on motor spindle;The connecting sheet is provided with upper and lower symmetrical through holes in U-shaped structure, and the connecting sheet is fixedly connected with the upper and lower two pitch seats by screw passing through the through hole.

[0005] Further, the paddle clamp is fixedly sleeved on the convex shaft on both sides of the hub, and a U-shaped groove structure is arranged on the outside of the paddle clamp to adaptably install the blade.

[0006] Further, the tab symmetrically arranged on both sides of the hub is provided with symmetrical cylindrical structure.

[0007] Further, the pitch U-shaped groove is arranged on the end of the paddle clamp close to the motor spindle, and the pitch U-shaped grooves are arranged symmetrically above and below the motor spindle.

[0008] Further, the convex shaft end of the pitch seat is provided with protruding and symmetrical ball shaft, and one end of the ball shaft is arranged in the pitch U-shaped groove of the paddle clamp.

[0009] Further, the connecting piece middle part is provided with a through hole matched with the cylinder on the boss flange, and the connecting piece is sleeved on both ends of the boss cylinder through the middle part through hole, and the variable pitch hinge torsional spring is pressed when the variable pitch seat is fixed.

[0010] Further, the number of the connecting pieces is four.

[0011] Further, the variable pitch hinge torsional spring is sleeved on the cylinder of the boss flange on both sides.

[0012] Further, the number of the variable pitch hinge torsional springs is four.

[0013] The utility model discloses a beneficial effect: 1. The utility model discloses a swash plateless helicopter rotor system, through the short and sharp acceleration / deceleration of the specific phase of the motor main shaft drive boss, the balance state of the variable pitch seat is destroyed, the variable pitch seat rotates relative to the boss, drives the ball shaft to drive the up and down variable pitch U groove of the paddle clamp to drive the left and right paddle difference rotation, carries out periodic variable pitch, reaches front and rear pitching, left and right tilting motion, when the acceleration / deceleration of the motor main shaft is controlled, the change of rotational speed causes the change of lift, equivalent to the total distance variable pitch effect, reaches the purpose of up and down lifting, thereby cancels the automatic tilting device and mechanical control lever system, greatly reduces the complexity of mechanism and the weight of system and improves overall reliability. 2. The utility model discloses a swash plateless helicopter rotor system, including variable pitch seat, connecting piece etc., adopts symmetrical structure design, keeps the stability of the rotor system reliable, 3. The utility model discloses a swash plateless helicopter rotor system, has the effect of variable pitch adjustment and reset stability. 4. The utility model discloses a swash plateless helicopter rotor system, through the difference variable pitch deflection of driving left and right two paddles, thereby produces the rotor of the pitch moment and the roll moment of the helicopter, the angle of attack increases when accelerating, the angle of attack decreases when decelerating, the acceleration / deceleration control rotor torsion is given in the specific phase, reaches the purpose of variable pitch. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 It is swash plateless helicopter rotor system structure schematic diagram.

[0015] Figure 2 It is the partial enlarged view of swash plateless helicopter rotor system.

[0016] Figure 3 It is the schematic diagram of the positive angle difference of paddle mechanism and motor main shaft.

[0017] Figure 4 It is the schematic diagram of the negative angle difference of paddle mechanism and motor main shaft.

[0018] Figure 5 It is the boss schematic diagram of swash plate helicopter rotor system.

[0019] Figure 6 It is the variable pitch seat schematic diagram of swash plate helicopter rotor system.

[0020] Figure 7 Figure is a schematic view of a blade holder of a swashplate helicopter rotor system.

[0021] Figure 8 Figure is a schematic view of a connecting piece of a swashplate helicopter rotor system.

[0022] In the figure, reference numerals: 100 - motor; 101 - motor spindle; 200 - variable pitch seat; 201 - ball shaft; 300 - blade; 400 - blade holder; 401 - variable pitch U-shaped groove; 402 - U-shaped groove; 500 - hub; 501 - convex shaft; 502 - convex piece; 503 - cylinder, 600 - variable pitch hinge torsional spring; 700 - connecting piece; 800 - screw. DETAILED DESCRIPTION

[0023] The technical solutions in the embodiments of the present application will be described clearly and completely below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0024] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0025] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0026] As Figures 1-8As shown, a kind of swash plate-free helicopter rotor system is arranged on the top of helicopter, including motor 100, variable-pitch seat 200, paddle 300, paddle clamp 400, hub 500, variable-pitch hinge torsion spring 600, the hub 500 is arranged on the upper end of motor 100 and is sleeved on motor spindle 101, and hub 500 rotates synchronously with motor spindle 101;Further, hub 500 is set as circular ring structure and symmetrically sets convex shaft 501 and tab 502;The variable-pitch seat 200 is square and is provided with through hole with the outer diameter size of motor spindle 101 is adapted, and variable-pitch seat 200 is installed on the upper and lower ends of hub 500 and is sleeved on motor spindle 101;The connecting piece 700 is provided with upper and lower symmetrical through holes with U-shaped structure, and connecting piece 700 is fixedly connected to the upper and lower two variable-pitch seats 200 by screw 800 passing through the through hole;The paddle clamp 400 is set to be sleeved and fixed on the two sides of convex shaft 501 of hub 500, and U-shaped groove 402 structure is set on the outside of paddle clamp 400 to adapt to install paddle 300.

[0027] Further, the symmetrically convex tab of the hub 500 is provided with symmetrically cylindrical structure, and variable-pitch hinge torsion spring 600 can be installed.

[0028] Further, the paddle 400 clamp is provided with variable-pitch U-shaped groove 401 close to the end of motor spindle 101, and the variable-pitch U-shaped groove 401 is symmetrically arranged on the two sides of motor spindle as upper and lower, and the synchronous rotation of the two sides of paddle clamp 400 can simultaneously adjust the variable-pitch of paddle 300, so that the positive and negative angle difference between paddle 300 and motor spindle 101 is generated.

[0029] Further, the variable-pitch seat 200 is provided with symmetrically ball shaft 201, one end of ball shaft 201 is arranged in variable-pitch U-shaped groove 401 of paddle clamp 400, and the rotation of motor spindle 101 drives the rotation of variable-pitch seat 200, further drives the rotation of the two sides of ball shaft 201 around motor spindle 101, and the rotation of paddle clamp 400 around convex shaft 501 of hub 200 is driven by the stirring of ball shaft 201 in variable-pitch U-shaped groove 401 to carry out variable-pitch.

[0030] Further, the connecting piece 700 is provided with through hole matched with the cylinder 503 on the convex tab 502 of hub in the middle, and the connecting piece 700 is sleeved on the two ends of hub cylinder 503 through the through hole in the middle, so that variable-pitch seat 200 is fixed, and variable-pitch hinge torsion spring 600 is compressed.

[0031] Further, the number of connecting piece 700 is 4, and the upper and lower two variable-pitch seats 200 are fixed by connecting piece 700.

[0032] Further, the variable-pitch hinge torsion spring 600 is sleeved on the cylinder 503 of the two sides of symmetric tab 502 of hub 500;Further, the number of variable-pitch hinge torsion spring 600 is 4, which plays a stabilizing role when variable-pitch adjustment and reset.

[0033] Working principle: when the unmanned helicopter needs to adjust the flight attitude, the motor shaft 101 rotates to drive the synchronous rotation of the hub 500, further driving the rotation of the variable pitch seat 200 at both ends of the hub 500, the ball shaft 201 on both sides of the variable pitch seat 200 rotates through the variable pitch U-shaped groove 401 of the upper and lower symmetrical paddle clamp 400 of the motor shaft 101 to respectively drive the two sides connected paddle 300 to change the pitch, the two sides of the paddle 300 synchronously change the angle; at a certain phase, give a short and sharp acceleration / deceleration control to twist the rotor, the lower hub 500 rotates relative to the variable pitch seat 200 to push the paddle 300 to deflect, so as to achieve the purpose of periodic pitch change, to control the forward, backward and tilt attitude of the helicopter; by slower acceleration and deceleration, the balance of the variable pitch seat is not damaged, the paddle pitch does not change, the rotation speed increases / decreases, so as to control the lifting attitude of the helicopter.

[0034] Further, when accelerating, the angle of the right paddle 300 decreases, and the angle of the left paddle 300 increases, the two sides of the paddle 300 and the motor shaft 101 produce a positive angle difference, the angle of attack increases, and the rotational lift increases.

[0035] Further, when decelerating, the angle of the right paddle 300 increases, and the angle of the left paddle 200 decreases, the two sides of the paddle 300 and the motor shaft 101 produce a negative angle difference, the angle of attack decreases, and the rotational lift decreases.

[0036] Further, the variable pitch hinge torsion spring 600 between the connecting pieces 700 produces a counterforce to make the variable pitch relative stable and smooth, and at the same time, the hub 500 is reset in time after the variable pitch is finished, to keep the system stable.

[0037] It should be noted that in the present specification, the terms "comprising", "including" or any other variant thereof are intended to cover non-exclusive inclusion, so that the device including a series of elements not only includes those elements, but also includes other elements not explicitly listed. Without more limitation, the element defined by the statement "including a" does not exclude the presence of another identical element in the inclusion.

[0038] The above only describes the preferred embodiments of the present application, and is not used to limit the protection scope of the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application are included in the protection scope of the present application.

Claims

1. A swashplate-less helicopter rotor system, mounted on the top of a helicopter, comprising a motor, a pitch control mount, rotor blades, rotor clips, a rotor hub, and a pitch control hinge torsion spring, characterized in that: The propeller hub is located at the upper end of the motor and is fitted and fixed on the motor spindle; further, the propeller hub is configured as a circular structure with symmetrically arranged convex shafts and convex plates; the pitch seat is square with a through hole in the middle that matches the outer diameter of the motor spindle, and the pitch seat is installed at the upper and lower ends of the propeller hub and fitted on the motor spindle; the connecting piece is a U-shaped structure with symmetrically arranged through holes at the top and bottom, and the connecting piece is fixedly connected to the upper and lower pitch seats by screws passing through the through holes.

2. The swashplate-less helicopter rotor system according to claim 1, characterized in that: The propeller clamp is mounted on the convex shafts on both sides of the propeller hub, and a U-shaped groove structure is provided on the outside of the propeller clamp to adapt to the installation of the propeller blade.

3. The swashplate-less helicopter rotor system according to claim 1, characterized in that: The symmetrical protrusions on both sides of the propeller hub are arranged with symmetrical cylindrical structures.

4. The swashplate-less helicopter rotor system according to claim 1, characterized in that: The propeller clamp is provided with a variable pitch U-shaped groove near the motor spindle end, and the propeller clamps on both sides are provided with variable pitch U-shaped grooves symmetrically above and below the motor spindle.

5. A swashplate-less helicopter rotor system according to claim 1, characterized in that: The variable pitch seat has a convex and symmetrical ball shaft at the convex end, and one end of the ball shaft is set in the variable pitch U-shaped groove of the propeller clamp.

6. The swashplate-less helicopter rotor system according to claim 1, characterized in that: The connecting piece has a through hole in the middle that matches the cylinder on the rotor hub protrusion. The connecting piece is fitted onto both ends of the rotor hub cylinder through the middle through hole, which presses the pitch hinge torsion spring while fixing the pitch seat.

7. The swashplate-less helicopter rotor system according to claim 1, characterized in that: The number of connecting pieces is 4.

8. A swashplate-less helicopter rotor system according to claim 1, characterized in that: The variable pitch hinge torsion spring is mounted on symmetrical protruding cylindrical plates on both sides of the propeller hub.

9. A swashplate-less helicopter rotor system according to claim 1, characterized in that: The number of variable pitch torsion springs is 4.

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