A rotor blade assembly device and a rotor assembly

Abstract

The application provides a rotor blade assembling device and a rotor assembly, which comprises a base and a blade clamp fixedly connected to the side of the base, a positioning block is arranged above the base, a first slot structure is arranged on the lower surface of the positioning block, and a positioning notch is formed at the position of the first slot structure when the positioning block is fixed to the base; a limiting piece is extended from the assembling surface of the blade clamp opposite to the base, the limiting piece and the positioning notch are complementarily matched when the blade clamp is fixed to the base, the blade clamp can be fixed to a target posture through the positioning notch and the limiting piece, and then the blade fixed to the blade clamp can be fixed to a target blade angle. The rotor blade assembling device and the rotor assembly can effectively guarantee the posture stability of the blade fixed at the target blade angle, can quickly adjust the blade angle by replacing the positioning block, are convenient to use, and can guide the adjustment of the assembling posture of the blade clamp pre-fixed to the base during the installation and fixation of the positioning block, thereby reducing the assembling precision requirement and improving the assembling efficiency.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and in particular to a rotor blade assembly device and a rotor assembly. Background Technology

[0002] In rotorcraft, the common methods to change the lift of the aircraft include changing the blade angle and changing the speed of the drive motor. Among them, adjusting the motor speed is relatively easy, but the control effect is limited due to the motor speed limit and working efficiency. To further improve the lift of the aircraft, it is necessary to combine it with blade angle control.

[0003] For larger rotorcraft, the connection between the blades and the shaft can be configured as a rotating movable connection, and a hydraulic system and corresponding transmission mechanism can be configured to achieve blade angle adjustment while ensuring blade attitude stability.

[0004] However, for small drones, their small size makes it difficult to guarantee the mechanical strength and stability of their movable components, resulting in insufficient attitude stability of the propellers and poor flight reliability. Summary of the Invention

[0005] Based on this, the purpose of the present invention is to provide a rotor blade assembly device and a rotor assembly to solve the problem that the blade attitude stability is insufficient in the blade angle adjustment scheme of small rotorcraft, resulting in poor flight reliability.

[0006] The present invention provides a rotor blade assembly device, comprising a base and a blade clamp fixedly connected to the side of the base, the blade clamp being used to fix the blade, and the base being used to fix it to a drive motor, wherein...

[0007] A positioning block is also provided above the base, and a first slotted structure is provided on the lower surface of the positioning block so that a positioning slot is formed at the position of the first slotted structure when the positioning block is fixed to the base.

[0008] The mounting surface of the propeller clamp opposite to the base extends out a limiting member, and when the propeller clamp is fixed to the base, the limiting member is positioned in the positioning slot so as to fix the propeller clamp in the target posture through the positioning slot and the limiting member, thereby fixing the propeller blade fixed to the propeller clamp at the target blade angle.

[0009] The target attitude includes multiple, and the positioning blocks are correspondingly provided with multiple, and the first slot structure of each positioning block is different from each other. Each positioning block corresponds to a target attitude, so as to match the propeller clips in different target attitudes one by one.

[0010] Optionally, the base is further provided with a second slotted structure. In the assembled state, the limiting member extends into the second slotted structure, and the size of the second slotted structure is consistent with the preset range of the target posture, so as to provide the limiting stroke of the limiting member.

[0011] Optionally, the limiting member is a cylindrical part and is integrally formed with the propeller clamp, or is screwed to the propeller clamp.

[0012] Optionally, the end of the limiting member pointing towards the base is provided with an extension structure, and the groove cavity of the first slotted structure is provided with an extension cavity that matches the extension structure, so that the limiting member is positioned in the extension cavity by the extension structure in the docking direction between the paddle clamp and the base.

[0013] Optionally, the length of the positioning block is greater than the length of the base, the first slotted structure is disposed in the area of ​​the positioning block that extends beyond the base, the limiting member is clamped between the base and the paddle clamp, and the first slotted structure is fitted and matched with the top surface of the limiting member.

[0014] Optionally, the portion of the limiting member that fits and matches the first slotted structure includes at least one of a plane and an arc surface, and when only the arc surface is included, the axis of the arc surface is offset from the rotation axis of the paddle clamp.

[0015] Optionally, the limiting member is further provided with a first hollow structure.

[0016] Optionally, the top surface of the base is further provided with a third slotted structure, and the bottom surface of the positioning block is provided with a limiting protrusion structure that is aligned with and complementary to the third slotted structure. At least one set of the third slotted structure and the limiting protrusion structure is provided.

[0017] Optionally, the base further includes a second hollow structure, and the second hollow structure is disposed below the second slotted structure.

[0018] Another aspect of the present invention provides a rotor assembly comprising blades and the aforementioned rotor blade assembly device, wherein the blades are fixed to the blade clamp or integrally formed with the blade clamp.

[0019] The rotor blade assembly device provided by the present invention includes a base and a blade clamp fixedly connected to the side of the base. The blade clamp is used to fix the blade, and the base is used to fix it to a drive motor. A positioning block is also provided on the upper part of the base. The lower surface of the positioning block is provided with a first slot structure, which forms a positioning slot when the positioning block is fixed to the base. A limiting member extends from the assembly surface of the blade clamp opposite to the base. When the blade clamp is fixed to the base, the limiting member is positioned in the positioning slot. The blade clamp can be fixed to the target attitude through the positioning slot and the limiting member, thereby fixing the blade fixed to the blade clamp to the target blade angle. The blade angle can be quickly adjusted by replacing the positioning block. The rotor blade assembly device of the present invention can limit and position the limiting block of the blade clamp through the first slotted structure of the positioning block, thereby realizing the angle adjustment of the blade fixed to the blade clamp. The positioning block has high structural stability, which can effectively ensure the stability of the blade fixed at the target blade angle. The blade angle can be quickly adjusted by replacing the positioning block, which is convenient to use. At the same time, the installation of the positioning block can guide the assembly posture of the blade clamp pre-fixed to the base. The alignment accuracy requirement of the assembly is low, which can effectively improve the blade assembly efficiency and blade angle adjustment efficiency.

[0020] The rotor assembly provided by the present invention includes blades and the aforementioned rotor blade assembly device. Its blade angle is adjustable, and the adjustment is flexible, highly precise, and stable, which provides convenience for the performance control of rotorcraft, and is particularly suitable for the needs of small rotorcraft. Attached Figure Description

[0021] Figure 1 This is an exploded structural diagram of the rotor blade assembly device in the first embodiment of the present invention;

[0022] Figure 2 This is a schematic diagram of the rotor blade assembly device in the assembled state according to the first embodiment of the present invention;

[0023] Figure 3 This is an exploded structural diagram of the rotor blade assembly device in the second embodiment of the present invention;

[0024] Figure 4 This is an exploded structural diagram of the rotor blade assembly device in the third embodiment of the present invention;

[0025] Figure 5 This is a schematic cross-sectional view of the rotor blade assembly device in the assembled state according to the third embodiment of the present invention.

[0026] Figure 6 This is a view of the rotor blade assembly device in the second embodiment of the present invention, showing the blade clamp on the assembly surface.

[0027] Figure 7This is a view of the rotor blade assembly device in an embodiment of the present invention, showing the blade clamp on the assembly surface.

[0028] The following detailed description, in conjunction with the accompanying drawings, will further illustrate the present invention. Detailed Implementation

[0029] To facilitate understanding of the present invention, a more complete description will be given below with reference to the accompanying drawings. Several embodiments of the invention are illustrated in the drawings. However, the invention can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.

[0030] It should be noted that when a component is said to be "fixed to" another component, it can be directly on the other component or there may be an intervening component. When a component is said to be "connected to" another component, it can be directly connected to the other component or there may be an intervening component. The terms "vertical," "horizontal," "left," "right," and similar expressions used in this document are for illustrative purposes only.

[0031] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0032] To address the problem of insufficient attitude stability of rotor blades in the blade angle adjustment scheme of small rotorcraft, leading to poor flight reliability, this invention provides a rotor blade assembly device. Please refer to... Figure 1 and Figure 2 It includes a base 10 and a blade clamp 20 fixedly connected to the side of the base 10. The blade clamp 20 is used to fix the blade 01. The base 10 is used to fix to the drive motor and is fixedly connected to the shaft of the drive motor, so that the power transmission from the drive motor to the blade 01 can be realized.

[0033] The base 10 is equipped with a positioning block 30. The lower surface of the positioning block 30 is provided with a first slotted structure 31. When the positioning block 30 is fixed to the base 10, a positioning slot is formed at the position of the first slotted structure 31. The mounting surface of the propeller clamp 20 opposite to the base 10 extends out with a limiting member 21. When the propeller clamp is fixed to the base 10, the limiting member 21 is positioned in the positioning slot. The propeller clamp 20 can be fixed to the target posture through the positioning slot and the limiting member 21, and then the propeller blade 01 fixed to the propeller clamp 20 can be fixed to the target blade angle. At the same time, the blade angle can be quickly adjusted by changing the positioning block 30 and adjusting the position of the positioning slot.

[0034] The rotor blade assembly device of the present invention can limit and position the limiting block of the blade clamp through the first slotted structure of the positioning block, thereby realizing the angle adjustment of the blade fixed to the blade clamp. The block structure of the positioning block is stable, which can effectively ensure the attitude stability of the blade fixed at the target blade angle. Moreover, the blade angle can be quickly adjusted by replacing the positioning block, making it convenient to use.

[0035] Simultaneously, during assembly, the propeller clamp 20 can be pre-assembled by nesting its first assembly post 23 with the second assembly post 12 on the base 10. The posture of the propeller clamp 20 is pre-adjusted by rotation so that the limiting member 21 is approximately in the corresponding position. Then, the positioning block 30 is installed. At this time, the first slotted structure 31 of the positioning block 30 and the limiting member 21 are basically aligned in the vertical direction. As the positioning block 30 is pressed into the assembly area on the upper surface of the base 10, the sidewall of the first slotted structure 31 can guide and position the limiting member 21 to fit and match the first slotted structure 31, thereby accurately and securely fixing the propeller clamp 20 to the target posture. Finally, the positioning holes provided in the first assembly post 23 and the second assembly post 12 are used to... Figure 5 As shown, assembly is completed by pressing and fixing the rotor clamp 20 to the base 10 with the second screw 102. By replacing the positioning block 30 and adjusting the blade angle, the fixing screws in the first assembly post 23 to the second assembly post 12 are loosened, releasing the clamping state between the rotor clamp 20 and the base 10, thus restoring the rotatability of the rotor clamp 20. By setting the positioning block 30, the method of pre-fixing the rotor clamp and then fixing the positioning block can effectively reduce the precision requirements of the assembly, effectively improve the blade assembly efficiency and blade angle adjustment efficiency, and facilitate the improvement of system precision configuration, blade angle configuration accuracy, and product quality of the rotor assembly with adjustable blade angle.

[0036] To further improve product quality, in this embodiment, a second slotted structure 11 is also provided on the base 10. The limiting member 21 extends into the second slotted structure 11, and the size of the second slotted structure 11 is consistent with the preset range of the target posture. When it is necessary to select the extreme blade angle, the blade clamp 20 is rotated until its limiting member 21 abuts against the corresponding side wall of the second slotted structure 11. The bottom surface of the second slotted structure 11 is arc-shaped, and the arc axis coincides with the rotation axis of the blade clamp 20. During the rotation of the blade clamp 20, the limiting member 21 can slide along the bottom surface of the second slotted structure 11, providing support for the rotation operation in addition to the matching support of the first assembly column 23 and the second assembly column 12, and facilitating the horizontal maintenance of the axis of the blade clamp 20. Furthermore, in the extreme blade angle posture, one side of the limiting member 21 can be limited and supported by the side wall of the second slotted structure 11 of the base 11, which can improve the reliability of its limiting and fixing.

[0037] In this embodiment, the propeller clamp 20 is provided with a screw hole 22, and the limiting member 21 is screwed to the propeller clamp 20 through the screw hole 22. Correspondingly, the end of the limiting member 21 pointing to the base 10 is provided with an extension structure, that is, the limiting member 21 is a T-shaped screw structure. The adjustable limit of the blade angle can be adjusted by replacing the T-shaped screw structure with different nut sizes. In the limit position, the first slotted structure 31 of the matching positioning block 30 can reduce one side, thereby reducing the processing cost.

[0038] When the limiting member 21 is a T-shaped screw structure, the groove cavity of the first slotted structure 31 can also be provided with an extension cavity that matches the end extension structure of the T-shaped screw structure, so that the limiting member 21 can be positioned in the extension cavity through the extension structure in the docking direction between the propeller clamp 20 and the base 10, which can increase the number of fixing points for fastening the propeller clamp 20 and the base 10 in the docking direction and improve the fixing effect.

[0039] In alternative embodiments, such as Figure 3 The diagram shows the main structure of the rotor blade assembly device in the second embodiment of the present invention. The limiting member 21 is a cylindrical part of the optical axis and is integrally formed with the blade clamp 20, which facilitates ensuring the fixing strength between the limiting member 21 and the blade clamp 20, and ensures the blade angle adjustment and fixing effect. Figure 1 and Figure 2 The main difference in the first embodiment shown is the different fixing and engagement methods between the limiting member 21 and the propeller clamp 20. Other similar or identical structures will not be described in detail here. In practice, the fixing and engagement methods between the limiting member 21 and the propeller clamp 20 can be adapted according to specific circumstances. When the limiting member 21 and the propeller clamp 20 are screwed together, a corresponding protrusion can be provided on the propeller clamp 20 at the assembly position of the limiting member 21 to strengthen the structural strength of the assembly position and ensure assembly reliability.

[0040] Depending on the specific requirements for fixing the base 10 to the drive motor, the dimensions of the base 10 will generally vary, for example, see further reference. Figure 4 and Figure 5This is a schematic diagram of the main structure of the rotor blade assembly device in the third embodiment of the present invention. In the third embodiment, the limiting member 21 adopts a block structure, and the first slotted structure 31 is a strip-shaped bayonet. The strip-shaped bayonet contacts the surface of the block structure, and the fixed assembly is achieved through surface contact limiting, thereby meeting the pitch requirements of the base 10 and the blade clamp 20. Compared with the third embodiment, in the first and second embodiments of this application, the width of the base 10 is larger, which makes the second slotted structure 11 on the base 10 in the first and second embodiments longer, and the corresponding blade angle is larger. The adjustable range is larger; in the third embodiment, the size of the second slotted structure 11 on the base 10 is smaller, and the length of the positioning block 30 can be set to be greater than the length of the base 10. The first slotted structure 31 is set in the area where the positioning block 30 extends beyond the base 10. The limiting member 31 is sandwiched between the base 10 and the propeller clamp 20. The top surface of the first slotted structure 31 and the limiting member 21 fit and match, so that during the rotation adjustment of the propeller clamp 20, its limiting member 21 is not affected by the limiting of the second slotted structure 11 on the base 10, and is mainly fixed to the target posture by the limiting through the positioning block 30.

[0041] Depending on the different designs of the limiting member 21, the surface structure of the part of the limiting member 21 that fits and matches the first slotted structure 31 is different. In the first and second embodiments, it is mainly an arc surface. In the third embodiment, the projected outline of the limiting member 21 on the assembly surface is a rounded rectangle, and correspondingly, the surface structure of the part that fits and matches the first slotted structure 31 includes a plane and an arc surface. In an optional embodiment, the projected outline of the limiting member 21 on the assembly surface can also be a right-angled rectangle, and correspondingly, the surface structure of the part that fits and matches the first slotted structure 31 is a plane. In an optional embodiment, the top of the projected outline of the limiting member 21 on the assembly surface is arc-shaped, and correspondingly, the surface structure of the part that fits and matches the first slotted structure 31 is an arc surface, and the axis of the arc surface is offset from the rotation axis of the propeller clamp 20, which can ensure the limiting requirements of the propeller clamp 20.

[0042] In the third embodiment of this application, the limiting member 21 is further provided with a first hollow structure 24, which can reduce the weight of the paddle clamp 20. The first hollow structure 24 is located above the first assembly column 23 and is set close to the top surface of the limiting member 21, which can improve the toughness of the limiting member 21 and improve the reliability of the paddle clamp 20 being fixed to the positioning block 30 by the limiting member 21.

[0043] To ensure the assembly and fixation of the positioning block 30, in this embodiment, the top surface of the base 10 is further provided with a third slotted structure 13, and the bottom surface of the positioning block 30 is provided with a limiting protrusion structure 33 that is aligned with and complementary to the third slotted structure 13. At least one set of the third slotted structure 13 and the limiting protrusion structure 33 is provided, such as... Figure 3 As shown, a set can be installed at the location of the third fixing screw 32, or as... Figure 4and Figure 5 As shown, a set of screws can be provided on each side of the location where the third fixing screw 32 is located. Compared with the first embodiment where an assembly groove is provided on the base 10, the positioning block 30 is fully embedded in the base 10, and a partial groove is formed to create a third groove structure 13. This can improve the structural strength of the top sidewall of the base 10 while ensuring the fixing reliability of the positioning block 30 to the base 10.

[0044] To further reduce the overall weight, the base 10 also includes a second hollow structure 14, which is located below the second slotted structure 11. While reducing the weight of the base 10, it can also release the surrounding structural stress, improve the structural reliability of the upper second slotted structure 11, ensure the curvature accuracy of the bottom surface of the second slotted structure 11, and thus ensure the movement accuracy of the limiting member 21 that extends into and abuts against the second slotted structure 11, and ensure the operational reliability of the blade angle adjustment.

[0045] The second assembly column 12 and the base 10 can be an integrally formed structure or a combined structure, and are fixedly connected by the first screw 101.

[0046] The propeller clamp 20 is also provided with a guide groove 201 for assembling the second screw 102. Depending on the specific structure of the propeller clamp 20, the guide groove 201 can be configured as follows: Figure 4 and Figure 5 As shown, it is located inside the propeller clip 20, or as... Figure 3 As shown, it is located on the outside of the propeller clamp 20, which can further reduce the weight of the propeller clamp 20 while ensuring the assembly of the second screw 102.

[0047] The guide groove 201 can also improve the flexibility of the setting position of the second screw 102, making the design range of the distance between the fixed point of the propeller clamp 20 and the base 10 and the fixed point of the limiting member 21 more flexible. This facilitates the increase of positioning torque, improves the stability of the propeller clamp in the target attitude, and thus improves the reliability of the rotor blade angle adjustment and enhances the rotor quality with adjustable blade angle.

[0048] Limited by the second slotted structure 11, the adjustable range of the blade angle is, for example, 30°. Figure 6 The image shown is a view of the rotor blade assembly device in the second embodiment of the present invention, with the blade clamp on the assembly surface. In this embodiment, the limiting member 21 is disposed on the vertical central axis of the assembly surface of the blade clamp 20. When the 0° reference blade angle of the blade 01 is perpendicular to the vertical central axis of the blade clamp 20, the adjustable range of the blade angle of the blade 01 is between +15° and -15°. The required range of the blade angle varies under different conditions, and the setting position of the limiting member 21 can be adjusted by adjusting the design of the blade clamp 20, for example... Figure 7As shown, the position of the limiting member 21 can be offset from the vertical centerline of the mounting surface of the propeller clamp 20, and correspondingly, its blade angle can be adjusted within a range of 0° to +30° or 0° to -30°. In an optional embodiment, the angle between the 0° reference blade angle and the vertical centerline of the propeller clamp 20 can also be adjusted to control the adjustable range of the blade angle, thereby increasing the applicability.

[0049] The present invention also provides a rotor assembly comprising blades and the aforementioned rotor blade assembly device, wherein the blades are fixed to a blade clamp or integrally formed with the blade clamp. Its blade angle is adjustable, and the adjustment is flexible, precise, and stable, providing convenience for the performance control of rotorcraft, and is particularly suitable for the needs of small rotorcraft.

[0050] In the description of this specification, references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0051] The above-described embodiments are merely illustrative of several specific implementations of the present invention, and while the descriptions are detailed, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the scope of protection of the present invention. Therefore, the scope of protection of this patent should be determined by the appended claims.

Claims

1. A rotor blade assembly device, characterized in that, It includes a base and a propeller clamp fixedly connected to the side of the base. The propeller clamp is used to fix the propeller blades, and the base is used to fix it to the drive motor. A positioning block is also provided above the base, and a first slotted structure is provided on the lower surface of the positioning block so that a positioning slot is formed at the position of the first slotted structure when the positioning block is fixed to the base. The mounting surface of the propeller clamp opposite to the base extends out a limiting member, and when the propeller clamp is fixed to the base, the limiting member is positioned in the positioning slot so as to fix the propeller clamp in the target posture through the positioning slot and the limiting member, thereby fixing the propeller blade fixed to the propeller clamp at the target blade angle. The target attitude includes multiple, and the positioning blocks are correspondingly provided with multiple, and the first slot structure of each positioning block is different from each other. Each positioning block corresponds to a target attitude, so as to match the propeller clips in different target attitudes one by one.

2. The rotor blade assembly device according to claim 1, characterized in that, The base is also provided with a second slotted structure. In the assembled state, the limiting member extends into the second slotted structure, and the size of the second slotted structure is consistent with the preset range of the target posture, so as to provide the limiting stroke of the limiting member.

3. The rotor blade assembly device according to claim 1, characterized in that, The limiting member is a cylindrical part, and it is integrally formed with the propeller clamp, or it is screwed to the propeller clamp.

4. The rotor blade assembly device according to claim 1, characterized in that, The limiting member has an extension structure at its end pointing towards the base. The groove of the first slotted structure has an extension cavity that matches the extension structure, so that the limiting member is positioned in the extension cavity by the extension structure in the docking direction between the paddle clamp and the base.

5. The rotor blade assembly device according to claim 1, characterized in that, The length of the positioning block is greater than the length of the base. The first slotted structure is disposed in the area where the positioning block extends beyond the base. The limiting member is clamped between the base and the paddle clamp. The first slotted structure fits and matches the top surface of the limiting member.

6. The rotor blade assembly device according to claim 5, characterized in that, The portion of the limiting member that fits and matches the first slotted structure includes at least one of a flat surface and an arc surface, and when only the arc surface is included, the axis of the arc surface is offset from the rotation axis of the propeller clamp.

7. The rotor blade assembly device according to claim 5, characterized in that, The limiting component also includes a first hollow structure.

8. The rotor blade assembly device according to claim 1, characterized in that, The top surface of the base is also provided with a third slotted structure, and the bottom surface of the positioning block is provided with a limiting protrusion structure that is aligned with and complementary to the third slotted structure. At least one set of the third slotted structure and the limiting protrusion structure is provided.

9. The rotor blade assembly device according to claim 2, characterized in that, The base also includes a second hollow structure, which is located below the second slotted structure.

10. A rotor assembly, characterized in that, The device includes a rotor blade and a rotor blade assembly device according to any one of claims 1 to 9, wherein the rotor blade is fixed to the rotor clamp or integrally formed with the rotor clamp.

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