A paddle mechanism and aircraft

Abstract

The utility model relates to an aircraft technical field especially relates to a kind of paddle mechanism and aircraft, including paddle assembly, locking mechanism and sleeve, paddle assembly includes paddle main part and paddle clamp, paddle clamp is equipped with convex part and avoidance slot, locking mechanism includes the elastic clamping component being located in avoidance slot and partly inclined and projecting and the locking screw piece of inner wall being equipped with ratchet inner tooth and internal thread, convex part prevents it from separating, sleeve rotates sleeve paddle clamp and inserts locking screw piece, sleeve is equipped with notch, sleeve rotates to first position, notch is aligned with avoidance slot, elastic clamping component clamps ratchet inner tooth, limit locking screw piece second direction rotation, sleeve rotates to second position, notch is staggered, component is pressed back, locking screw piece can bidirectional rotation, internal thread screw joint drive mechanism is along second direction rotation, until locking screw piece and drive mechanism separate. By the above way, the utility model can quickly replace the paddle mechanism of aircraft, shorten replacement time, improve maintenance efficiency.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a propeller mechanism and an aircraft. Background Technology

[0002] In the field of aircraft, especially small aircraft such as drones, they have been widely used in many fields, such as aerial photography and agricultural spraying. The drone propeller, as the core power actuator, is an extremely important part of the entire drone, but it is also a part that is relatively easy to be damaged and often needs to be replaced and maintained.

[0003] However, the inventors of this utility model discovered during the process of realizing this utility model that: currently, the propellers of traditional drones are usually installed by permanent connection or screw fixing. The permanent connection method cannot replace the propeller once it is damaged, while the screw fixing method requires additional installation tools during disassembly and assembly, which cannot achieve quick disassembly and assembly, thus limiting the efficient maintenance and flight safety of drones to a certain extent. Utility Model Content

[0004] The main technical problem solved by this utility model embodiment is to provide a propeller mechanism and an aircraft that can quickly replace the propeller mechanism of the aircraft, shorten the replacement time, and improve maintenance efficiency.

[0005] To solve the above-mentioned technical problems, the present invention provides a blade mechanism, comprising a blade assembly, a locking mechanism, and a sleeve. The blade assembly includes a blade body and a blade clamp. One end of the blade clamp is fixed to the blade body, and the other end of the blade clamp has a protrusion. The side wall of the blade clamp has a clearance groove. The locking mechanism includes an elastic snap-fit ​​component and a locking screw. The elastic snap-fit ​​component is disposed in the clearance groove, with a portion extending out of the clearance groove at an inclined angle. The locking screw is rotatably sleeved on the blade clamp. Along the axial direction of the blade clamp, the inner wall of the locking screw near the blade body has ratchet teeth, and the inner wall of the locking screw away from the blade body has an internal thread. The protrusion is used to restrict... The locking screw disengages from the propeller clamp, and the sleeve rotates and is fitted onto the propeller clamp. The sleeve is inserted into the locking screw, and the sleeve has a notch. When the sleeve rotates to the first position, the notch aligns with the clearance groove, and the elastic locking component extends from the clearance groove. The portion of the elastic locking component extending from the clearance groove is used to engage the ratchet's internal teeth to allow the locking screw to rotate in the first direction, but restricts the locking screw to rotate in the second direction. When the sleeve rotates to the second position, the notch and the clearance groove are misaligned, and the elastic locking component is pressed into the clearance groove by the sleeve, allowing the locking screw to rotate in both the first and second directions. The internal thread of the locking screw is used for screwing into the drive mechanism. When the locking screw is screwed into the drive mechanism, the locking screw moves in the second direction.

[0006] Optionally, the paddle clamp is provided with a first convex shaft and a second convex shaft in the clearance groove. The elastic locking assembly includes an elastic element and a limiting block. The elastic element is fixed to the first convex shaft, one end of the limiting block is fixed to the second convex shaft, and the other end of the limiting block abuts against the elastic element. When the sleeve rotates to the first position, the notch aligns with the clearance groove. Under the action of the elastic element, the other end of the limiting block extends from the notch and the clearance groove and abuts against the ratchet's internal teeth.

[0007] Optionally, the elastic element includes a first spring, a second spring, and a bending piece. The two ends of the bending piece are connected to the first spring and the second spring, respectively. The bending piece is sleeved on the first convex shaft. The first spring and the second spring are spaced apart. The other end of the limiting block abuts against the second spring.

[0008] Optionally, the number of clearance grooves, notches, and elastic snap-fit ​​components is two, with two notches arranged opposite each other and one elastic snap-fit ​​component disposed in one clearance groove. When the sleeve is rotated to the first position, one notch aligns with one clearance groove, and a portion of one elastic snap-fit ​​component extends out from one notch and one clearance groove.

[0009] Optionally, the blade assembly includes a first fixing screw and a blade clamp cover, with the blade clamp cover and blade clamp located on both sides of the blade body. The first fixing screw passes through the blade clamp cover and the blade body in sequence and is screwed onto the blade clamp.

[0010] Optionally, the sleeve extends with a baffle handle for rotating the sleeve.

[0011] Optionally, there are two baffle handles, with the two baffle handles located on both sides of the sleeve.

[0012] Optionally, an aircraft includes a drive mechanism and a propeller mechanism. The drive mechanism includes a drive component and a base. The base is disposed on the drive component and has a receiving groove for inserting the propeller clamp of the propeller mechanism. The outer wall of the base has an external thread for screwing the locking screw of the propeller mechanism.

[0013] Optionally, the aircraft also includes a wave spring, which is placed at the bottom of the receiving slot and is used to abut against the rotor clamp of the rotor mechanism.

[0014] Optionally, the drive mechanism may also include a second fixing screw, which is used to screw onto the drive member after passing through the bottom of the receiving groove.

[0015] The beneficial effects of this utility model embodiment are as follows: Unlike existing technologies, this utility model embodiment provides a propeller mechanism, including a propeller assembly, a locking mechanism, and a sleeve. The propeller assembly includes a propeller body and a propeller clamp. The propeller clamp has a protrusion and a clearance groove. The locking mechanism includes an elastic snap-fit ​​component located in the clearance groove and partially extending at an angle, and a locking screw connector with ratchet teeth and internal threads on its inner wall. The protrusion prevents it from disengaging. The sleeve rotates to fit the propeller clamp and inserts into the locking screw connector. The sleeve has a notch. When the sleeve rotates to a first position, the notch aligns with the clearance groove, and the elastic snap-fit ​​component engages the ratchet teeth, restricting the locking screw connector's rotation in a second direction. When the sleeve rotates to the second position, the notch is offset, the component is pressed back, and the locking screw connector can rotate bidirectionally. When the internal thread is used to connect to the drive mechanism, it rotates in the second direction until the locking screw connector and the drive mechanism separate. Through the above method, this utility model embodiment can quickly replace the propeller mechanism of an aircraft, shortening replacement time and improving maintenance efficiency. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments of this application will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on the drawings without creative effort.

[0017] Figure 1 This is a perspective view of the blade mechanism according to an embodiment of the present utility model; Figure 2 This is an exploded view of the blade mechanism according to an embodiment of the present utility model; Figure 3 yes Figure 2 Enlarged view of section A in the middle; Figure 4 yes Figure 2 Enlarged view of section B; Figure 5 This is an exploded view of the aircraft according to an embodiment of this utility model. Detailed Implementation

[0018] To facilitate understanding of this utility model, a more detailed description is provided below with reference to the accompanying drawings and specific embodiments. It should be noted that when an element is described as being "fixed to" another element, it can be directly on the other element, or one or more intermediate elements may exist between them. When an element is described as being "connected" to another element, it can be directly connected to the other element, or one or more intermediate elements may exist between them. The terms "vertical," "horizontal," "left," "right," and similar expressions used in this specification are for illustrative purposes only.

[0019] Unless otherwise defined, all technical and scientific terms used in this specification have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the scope of the invention. The term "and / or" as used in this specification includes any and all combinations of one or more of the associated listed items.

[0020] Please see Figure 1 and Figure 2 This utility model embodiment provides a propeller mechanism, which includes a propeller assembly 2, a locking mechanism 3, and a sleeve 4. Both the locking mechanism 3 and the sleeve 4 are disposed on the propeller assembly 2. The locking mechanism 3 is used to be screwed to the drive assembly of the aircraft. The sleeve 4 is used to constrain or release the locking mechanism 3. When the sleeve 4 releases the locking mechanism 3, the locking mechanism 3 can only be screwed to the drive assembly of the aircraft in a forward direction. The locking mechanism 3 can only be screwed to the drive assembly of the aircraft more and more tightly. Reverse screwing between the locking mechanism 3 and the drive assembly of the aircraft is not allowed. When the sleeve 4 constrains the locking mechanism 3, the locking mechanism 3 can be screwed to the drive assembly of the aircraft in a forward direction or loosened in a reverse direction.

[0021] The aforementioned blade assembly 2 includes a blade body 21, a blade clamp 22, a first fixing screw connector 23, and a blade clamp cover 24. The blade clamp cover 24 and the blade clamp 22 are located on both sides of the blade body 21. The first fixing screw connector 23 passes through the blade clamp cover 24 and the blade body 21 in sequence and is screwed onto the blade clamp 22, thereby fixing one end of the blade clamp 22 to the blade body 21. Of course, in some embodiments, other fixing connection methods can also be used between one end of the blade clamp 22 and the blade body 21, for example, one end of the blade clamp 22 can be fixed to the blade body 21 by welding, bolting, or integral molding.

[0022] Furthermore, the other end of the propeller clip 22 is provided with a protrusion 221, which is an annular protrusion structure and surrounds the outer wall of the propeller clip.

[0023] Furthermore, please combine Figure 3 The side wall of the propeller clamp 22 is provided with a relief groove 222. In some embodiments, the relief groove 222 is a rectangular groove structure that penetrates the side wall of the propeller clamp 22 along the axial direction of the propeller clamp 22. The relief groove 222 is used to accommodate the elastic snap-fit ​​component 31 and provide space for the telescopic movement of the elastic snap-fit ​​component 31.

[0024] Furthermore, the paddle clip 22 is provided with a first convex shaft 223 and a second convex shaft 224 in the clearance groove 222. The first convex shaft 223 and the second convex shaft 224 are spaced apart and are used to install the locking mechanism.

[0025] In some embodiments, the blade body 21 is a plate-shaped or airfoil-shaped structure.

[0026] For sleeve 4 mentioned above, please refer to [reference needed]. Figure 1 and Figure 2 The sleeve 4 is fitted onto the propeller clamp 22 and can rotate relative to the propeller clamp 22. The outer diameter of the protrusion 221 of the propeller clamp 22 is larger than the inner diameter of the sleeve 4 near the protrusion 221, forming an axial limiting structure that can restrict the sleeve 4 from leaving the propeller clamp 22 along the axial direction away from the propeller body 21, thus constraining the stroke of the sleeve 4's axial movement.

[0027] The sleeve 4 is provided with a notch 41. When the notch 41 is aligned with the clearance groove 222, the sleeve 4 constrains the locking mechanism 3. When the notch 41 is aligned with the clearance groove 222, the sleeve 4 releases the locking mechanism 3.

[0028] Furthermore, the sleeve 4 extends with a baffle handle 42, which facilitates the user to rotate the sleeve 4 so that the notch 41 is offset from or aligned with the clearance groove 222. In some embodiments, there are two baffle handles 42, which are located on opposite sides of the sleeve 4.

[0029] For the locking mechanism 3 mentioned above, please refer to... Figure 2 The locking mechanism 3 includes an elastic snap-fit ​​assembly 31 and a locking screw 32. The locking screw 32 is rotatably sleeved on the outer wall of the propeller clamp 22. The outer diameter of the protrusion 221 is larger than the inner diameter of the locking screw 32 near the protrusion 221, forming an axial limiting structure. This structure can restrict the locking screw 32 from disengaging from the propeller clamp 22 along the axial direction away from the propeller body 21, thus constraining the axial movement of the locking screw 32.

[0030] The inner wall of the locking screw connector 32 at the end away from the blade body 21 is provided with an internal thread 322, which is used for screwing into the propulsion assembly of the aircraft. The inner wall of the locking screw connector 32 at the end near the blade body 21 is provided with ratchet internal teeth 321.

[0031] For the aforementioned flexible snap-fit ​​component 31, please refer to... Figure 2 and Figure 3 The elastic locking component 31 is disposed in the clearance groove 222. When the sleeve 4 releases the locking mechanism 3, a portion of the elastic locking component 31 extends out from the clearance groove 222, and the portion of the elastic locking component 31 extending out from the clearance groove 222 is inclined. Specifically, the elastic locking component 31 includes an elastic element 311 and a limiting block 312. The elastic element 311 is fixed to the first convex shaft 223, one end of the limiting block 312 is fixed to the second convex shaft 224, and the other end of the limiting block 312 abuts against the elastic element 311. The limiting block 312 is inclined under the action of the elastic element 311. The sleeve 4 is also inserted into the locking screw 32. When the sleeve 4 rotates to the first position, the notch 41 is aligned with the relief groove 222. Under the action of the elastic member 311, the other end of the limiting block 312 extends from the notch 41 and the relief groove 222 and abuts against the ratchet inner tooth 321. When the locking screw 32 rotates in the first direction (i.e., the locking screw rotates forward), the inclined surface of the elastic locking component 31 slides into contact with the tooth surface of the ratchet inner tooth 321. The elastic locking component 31 does not restrict the rotation of the locking screw 32. When the locking screw 32 rotates in the second direction, the vertical surface of the elastic locking component 31 rigidly abuts against the tooth root of the ratchet inner tooth 321, restricting the locking screw 32 from rotating in the second direction (i.e., the locking screw rotates in reverse), thereby controlling the rotation direction of the locking screw 32 in one direction.

[0032] For the elastic element 311 mentioned above, please refer to... Figure 2 and Figure 4The elastic element 311 includes a first spring piece 3111, a second spring piece 3112, and a bent piece 3113. Both ends of the bent piece 3113 are connected to the first spring piece 3111 and the second spring piece 3112, respectively. The bent piece 3113 is sleeved on the first convex shaft 223. The first spring piece 3111 and the second spring piece 3112 are arranged parallel to each other at intervals. One end of the limiting block 312 is sleeved on the second convex shaft 224 through a shaft hole and rotates around the second convex shaft 224. The other end of the limiting block 312 abuts against the second spring piece 3112. When the sleeve 4 rotates to the first position, and the notch 41 aligns with the clearance groove 222, the second spring piece 3112 generates elastic force, pushing the other end of the limiting block 312 out of the clearance groove 222 and the notch 41. The limiting block 312 is inclined and abuts against the ratchet inner tooth 321. At this time, the locking screw 32 can only rotate in the first direction, but cannot rotate in the second direction. When the sleeve 4 rotates to the second position, and the notch 41 and the clearance groove 222 are misaligned, the sleeve 4 presses the other end of the limiting block 312 into the clearance groove 222. At this time, the locking screw 32 can rotate in both the first and second directions.

[0033] In some embodiments, there are two clearance grooves 222, notches 41 and elastic snap-fit ​​components 31. The two notches 41 are arranged opposite to each other, and an elastic snap-fit ​​component 31 is disposed in a clearance groove 222. When the sleeve 4 is rotated to the first position, a notch 41 is aligned with a clearance groove 222, and a portion of an elastic snap-fit ​​component 31 extends out from a notch 41 and a clearance groove 222.

[0034] It is understood that the elastic snap-fit ​​component 31 is not limited to the above structure, but can also be other structures. For example, the elastic snap-fit ​​component 31 only includes a limiting block 312, the limiting block 312 is elastic, the limiting block 312 is inclined and extends out from the relief groove 222.

[0035] In this embodiment of the utility model, the blade mechanism includes a blade assembly 2, a locking mechanism 3, and a sleeve 4. The blade assembly 2 includes a blade body 21 and a blade clamp 22. The blade clamp 22 is provided with a protrusion 221 and a relief groove 222. The locking mechanism 3 includes an elastic snap-fit ​​component 31 located in the relief groove 222 and partially extending at an angle, and a locking screw connector 32 with ratchet teeth 321 and internal threads 322 on its inner wall. The protrusion 221 prevents it from disengaging. The sleeve 4 rotates to fit the blade clamp 22 and inserts into the locking screw connector 32. With a notch 41, the sleeve 4 rotates to the first position, and the notch 41 aligns with the clearance groove 222. The elastic snap-fit ​​component 31 engages the ratchet inner teeth 321, restricting the second-direction rotation of the locking screw 32. When the sleeve 4 rotates to the second position, the notch 41 is offset, and the elastic snap-fit ​​component 31 is pressed back. The locking screw 32 can rotate in both directions. When the internal thread 322 is screwed into the drive mechanism, it rotates in the second direction until the locking screw 32 and the drive mechanism are separated, thereby enabling quick replacement of the UAV propeller blades and shortening the replacement time.

[0036] This utility model also provides an embodiment of an aircraft; please refer to [link / reference]. Figure 5 The aircraft includes a propeller mechanism 1, a drive mechanism 5, and a wave spring 6. The propeller mechanism 1 in this embodiment has the same structure and function as the propeller mechanism 1 in the above embodiments, and will not be described in detail here.

[0037] The drive mechanism 5 includes a drive member 51 and a base 52. The base 52 is disposed on the drive member 51. The drive member 51 can drive the base 52 to rotate. The base 52 is provided with a receiving groove 521. The outer wall of the base 52 is provided with an external thread 522. The receiving groove 521 is used for the blade clamp 22 of the blade mechanism 1 to be inserted. The receiving groove 521 radially positions the blade clamp 22 so that the blade mechanism 1 and the drive member 51 can be coaxial. The external thread 522 is used for the locking screw 32 of the blade mechanism 1 to be screwed.

[0038] In some embodiments, the drive mechanism 5 further includes a second fixing screw 53, which is used to screw onto the drive member 51 after passing through the bottom of the receiving groove 521, so that the base 52 and the drive member 51 can be detachably fixed.

[0039] A wave spring 6 is placed at the bottom of the receiving groove 521. The wave spring 6 is used to abut against the blade clamp 22 of the blade assembly 2 when the blade clamp 22 is inserted into the receiving groove 521, so as to eliminate the misalignment between one end of the blade clamp 221 and the bottom of the receiving groove 521, and to play a shock absorption role.

[0040] It should be noted that while the preferred embodiments of this utility model are provided in the specification and accompanying drawings, this utility model can be implemented in many different forms and is not limited to the embodiments described herein. These embodiments are not intended to impose additional limitations on the content of this utility model; their purpose is to provide a more thorough and comprehensive understanding of the disclosure of this utility model. Furthermore, the above-described technical features can be combined with each other to form various embodiments not listed above, all of which are considered to be within the scope of this utility model specification. Moreover, those skilled in the art can make improvements or modifications based on the above description, and all such improvements and modifications should fall within the protection scope of the appended claims.

Claims

1. A blade mechanism, characterized in that... ,include: The blade assembly includes a blade body and a blade clamp. One end of the blade clamp is fixed to the blade body, and the other end of the blade clamp is provided with a protrusion. The side wall of the blade clamp is provided with a clearance groove. The locking mechanism includes an elastic snap-fit ​​component and a locking screw. The elastic snap-fit ​​component is disposed in the clearance groove, and a portion of the elastic snap-fit ​​component extends out of the clearance groove. The portion of the elastic snap-fit ​​component extending out of the clearance groove is inclined. The locking screw is rotatably sleeved on the propeller clamp. Along the axial direction of the propeller clamp, the inner wall of the locking screw near the propeller body is provided with ratchet internal teeth, and the inner wall of the other end of the locking screw away from the propeller body is provided with internal threads. The protrusion is used to restrict the locking screw from disengaging from the propeller clamp. A sleeve is rotatably fitted onto the paddle clamp, and the sleeve is inserted into the locking screw, the sleeve having a notch; When the sleeve is rotated to the first position, the notch is aligned with the clearance groove, and the elastic snap-fit ​​component extends out of the clearance groove. The portion of the elastic snap-fit ​​component extending out of the clearance groove is used to snap into the ratchet internal teeth to allow the locking screw to rotate in the first direction, but restricts the locking screw to rotate in the second direction. When the sleeve rotates to the second position, the notch is misaligned with the clearance groove, and the elastic snap-fit ​​assembly is pressed back into the clearance groove by the sleeve, allowing the locking screw to rotate in the first direction and also allowing the locking screw to rotate in the second direction; The internal thread of the locking screw is used to screw into the drive mechanism, wherein when the locking screw is screwed into the drive mechanism, the locking screw moves in the second direction.

2. The blade mechanism according to claim 1, characterized in that, The paddle clamp is provided with a first convex shaft and a second convex shaft in the clearance groove; The elastic snap-fit ​​assembly includes an elastic element and a limiting block. The elastic element is fixed to the first convex shaft, one end of the limiting block is fixed to the second convex shaft, and the other end of the limiting block abuts against the elastic element. When the sleeve rotates to the first position, the notch aligns with the clearance groove. Under the action of the elastic element, the other end of the limiting block extends from the notch and the clearance groove to abut against the ratchet's internal teeth.

3. The blade mechanism according to claim 2, characterized in that, The elastic element includes a first spring sheet, a second spring sheet, and a bending sheet. The two ends of the bending sheet are connected to the first spring sheet and the second spring sheet, respectively. The bending sheet is sleeved on the first convex shaft. The first spring sheet and the second spring sheet are spaced apart. The other end of the limiting block abuts against the second spring sheet.

4. The blade mechanism according to claim 1, characterized in that, The number of the clearance groove, notch and elastic snap-fit ​​component is two, the two notches are arranged opposite to each other, and one elastic snap-fit ​​component is disposed in one of the clearance grooves; When the sleeve is rotated to the first position, one of the notches aligns with one of the clearance grooves, and a portion of one of the resilient snap-fit ​​components extends from one of the notches and the clearance groove.

5. The blade mechanism according to claim 1, characterized in that, The blade assembly includes a first fixing screw and a blade clamp cover. The blade clamp cover and the blade clamp are located on both sides of the blade body. The first fixing screw passes through the blade clamp cover and the blade body in sequence and is screwed onto the blade clamp.

6. The blade mechanism according to any one of claims 1-5, characterized in that, The sleeve extends to a baffle handle for rotating the sleeve.

7. The blade mechanism according to claim 5, characterized in that, There are two baffle handles, which are located on both sides of the sleeve.

8. An aircraft, characterized in that: Includes a drive mechanism and a blade mechanism as described in any one of claims 1-7; The drive mechanism includes a drive component and a base. The base is disposed on the drive component and has a receiving groove for inserting the blade clamp of the blade mechanism. The outer wall of the base has an external thread for screwing the locking screw of the blade mechanism.

9. The aircraft according to claim 8, characterized in that, The aircraft also includes a wave spring, which is placed at the bottom of the receiving slot and is used to abut against the propeller clamp of the propeller mechanism.

10. The aircraft according to claim 8 or 9, characterized in that, The drive mechanism further includes a second fixing screw, which is used to screw onto the drive member after passing through the bottom of the receiving groove.

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