A tapered UAV tail wing quick-release device

Abstract

The present invention discloses a tapered UAV tail quick-release device, which includes a front strut joint, a clamping pin, a clamping pin fixing ring, a torsion spring, a positioning pin, a rear strut joint and a positioning pin fixing ring. One end of the front strut joint has a conical concave surface, and the rear strut joint is fixed with a conical convex surface, and the conical concave surface and the conical convex surface are matched. The present invention increases the adaptability and safety of the quick-release parts to various requirements through the adjustable locking torque of the torsion spring; amplifies the locking torque and realizes the self-locking of the device through a small-angle bevel groove; eliminates the virtual position of the two parts through the contact of the front and rear joint conical surfaces and amplifies the tightening force. The quick-release mechanism of the composite wing UAV is not easy to loosen during flight, and the flight is safer. The device can be quickly disassembled and assembled by rotating the clamping pin fixing ring, thereby realizing the quick disassembly and assembly of the UAV tail. The disassembly and assembly time of the UAV can be greatly shortened.

Description

Technical Field

[0001] The invention relates to a UAV tail quick-release device, in particular to a UAV tail quick-release device with a taper, and belongs to the technical field of UAVs. Background Art

[0002] In order to facilitate transportation and storage, drones with tail struts in the aircraft field are generally designed to be quickly disassembled. There are many ways to disassemble and assemble the tail of a drone. The most common way is to connect through threads, using a hand-tightened nut on the rear strut joint and the threads on the front strut joint to tighten.

[0003] The tail quick-release device of the drone adopts the threaded connection form, and its front and rear strut joints generally adopt the form of a large diameter pipe sleeve and a small diameter pipe. This form can only be used with clearance fit, and there will be a certain amount of clearance in the tail when in use, which is not conducive to the control accuracy of the drone.

[0004] During the cruising process of the drone, the vibration generated by the engine or motor when it is working may cause the hand-tightened nut to loosen, thereby causing the drone tail wing connector to fail. This tail wing connection method affects the flight safety of the composite wing drone. Summary of the invention

[0005] The purpose of the present invention is to provide a tapered UAV tail quick-release device to solve the problem proposed in the above background technology that during the cruising process of the UAV, the vibration generated when the engine or motor is working may cause the hand-tightened nut to loosen, thereby causing the UAV tail connector to fail and affecting the flight safety of the composite wing UAV.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: the UAV tail wing quick-release device comprises a front strut joint, a clamping pin, a clamping pin fixing ring, a torsion spring, a locating pin, a rear strut joint and a locating pin fixing ring, the front strut joint has a conical concave surface at one end, the rear strut joint is fixedly provided with a conical convex surface, the conical concave surface and the conical convex surface are matched with each other, and a torsion spring is sleeved between the front strut joint and the rear strut joint, a clamping pin fixing ring is fixedly provided at the connection of the front strut joint, clamping pin holes are fixedly provided on both sides of the outer wall of the clamping pin fixing ring, and the two clamping pin holes are interference fit with clamping pins, and a locating pin fixing ring is fixedly provided at the connection of the rear strut joint, pin holes are opened on both sides of the outer wall of the locating pin fixing ring, and the insides of the two pin holes are interference fit with locating pins.

[0007] As a preferred technical solution of the present invention, a rear strut joint elongated hole is provided on the conical convex surface of the rear strut joint, and the rear strut joint elongated hole is interlaced and connected with the end of the clamping pin.

[0008] As a preferred technical solution of the present invention, a torsion spring fixing side force arm is fixedly provided at one end of the torsion spring, and a torsion spring force applying side force arm is fixedly provided at the other end of the torsion spring.

[0009] As a preferred technical solution of the present invention, a plurality of torsion spring fixed side force arm installation adjustment holes are provided on the side of the positioning pin fixing ring, one of which is inserted and connected with the torsion spring fixed side force arm, and a torsion spring force side force arm installation adjustment hole is provided on the side of the clamping pin fixing ring, one of which is inserted and connected with the torsion spring force side force arm.

[0010] As a preferred technical solution of the present invention, a front strut joint straight groove is provided at the conical concave surface of the front strut joint, a front strut joint oblique groove is provided at the end of the front strut joint straight groove, and the front strut joint oblique groove is interlaced and connected with the locking pin.

[0011] As a preferred technical solution of the present invention, the clamping pin and the positioning pin are both cylindrical pins made of 304 stainless steel.

[0012] As a preferred technical solution of the present invention, the front strut joint, the clamping pin fixing ring, and the rear strut joint are made of 7075 aviation aluminum alloy.

[0013] Compared with the prior art, the invention has the following beneficial effects: the invention is a tapered UAV tail wing quick-release device, which can adjust the locking torque of the torsion spring, thereby increasing the adaptability and safety of the quick-release parts to various requirements; the locking torque is amplified by the small-angle bevel groove and the self-locking of the device is realized; the front and rear joints are connected by tapered surfaces to eliminate the virtual position of the two parts and amplify the fastening force, so that the quick-release mechanism of the composite wing UAV is not easy to loosen during flight, and the flight is safer. The device can be quickly disassembled and assembled by rotating the clamping pin fixing ring, thereby realizing the quick disassembly and assembly of the UAV tail wing. The disassembly and assembly time of the UAV can be greatly shortened. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 The assembly diagram of the UAV tail quick-release device of the present invention is in a locked state;

[0015] Figure 2 The assembly diagram of the UAV tail wing quick-release device of the present invention is in the unlocked state;

[0016] Figure 3 is an isometric view of the front strut joint of the present invention;

[0017] Figure 4 A partial cross-sectional view of a rear support rod joint of the present invention;

[0018] Figure 5 It is a partial cross-sectional view of the clamping pin fixing ring of the present invention;

[0019] Figure 6 It is a schematic diagram of a torsion spring of the present invention;

[0020] Figure 7 It is a schematic diagram of the installation position of the torsion spring of the present invention.

[0021] Among them, 1. front strut joint; 1-1. straight groove of front strut joint; 1-2. oblique groove of front strut joint; 2. clamping pin; 3. clamping pin fixing ring; 3-1. installation adjustment hole of torsion spring force side force arm; 4. torsion spring; 4-1. torsion spring fixed side force arm; 4-2. torsion spring force side force arm; 5. positioning pin; 6. rear strut joint; 6-1. long strip hole of rear strut joint; 6-2. installation adjustment hole of torsion spring fixed side force arm; 7. positioning pin fixing ring. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] See also Figure 1-7 The present invention provides a technical solution for a tapered UAV tail quick-release device: Figure 1-7 As shown, the UAV tail wing quick-release device includes a front strut joint 1, a clamping pin 2, a clamping pin fixing ring 3, a torsion spring 4, a locating pin 5, a rear strut joint 6 and a locating pin fixing ring 7. One end of the front strut joint 1 is a conical concave surface, and the rear strut joint 6 is fixedly provided with a conical convex surface. The conical surface between the conical concave surface and the conical convex surface cooperates to further amplify the fastening force of the front strut joint 1 and the rear strut joint 6 and reduce the virtual position of the cooperation. A torsion spring 4 is sleeved between the front strut joint 1 and the rear strut joint 6. A clamping pin fixing ring 3 is fixedly provided at the connection of the front strut joint 1. Clamping pin holes are fixedly provided on both sides of the outer wall of the clamping pin fixing ring 3. The two clamping pin holes are interference-fitted with the clamping pins 2. A locating pin fixing ring 7 is fixedly provided at the connection of the rear strut joint 6. Pin holes are opened on both sides of the outer wall of the locating pin fixing ring 7. The insides of the two pin holes are interference-fitted with locating pins 5.

[0024] A rear support rod joint strip hole 6-1 is provided on the conical convex surface of the rear support rod joint 6, and the rear support rod joint strip hole 6-1 is connected with the end of the clamping pin 2 through the clamping pin 2, which is convenient for fixing the clamping pin fixing ring 3; one end of the torsion spring 4 is fixed with a torsion spring fixing side force arm 4-1, and the other end of the torsion spring 4 is fixed with a torsion spring force side force arm 4-2, which is convenient for fixing the torsion spring 4 to the front support rod joint 1 and the rear support rod joint 6; a plurality of torsion spring fixing side force arm installation adjustment holes 6-2 are provided on the side of the positioning pin fixing ring 7, one of which is connected with the torsion spring fixing side force arm 4-1 through the clamping pin fixing ring 3, and a torsion spring force side force arm installation adjustment hole 3-1 is provided on the side of the clamping pin fixing ring 3, one of which is connected with the torsion spring force side force arm 4-2 through the torsion spring fixing side force arm installation adjustment hole 6 -2 is interlaced and connected with the torsion spring fixed side force arm 4-1, and the torsion spring force side force arm installation adjustment hole 3-1 is interlaced and connected with the torsion spring force side force arm 4-2, which is convenient for fixing the torsion spring 4; a front strut joint straight groove 1-1 is opened at the conical concave surface of the front strut joint 1, and a front strut joint oblique groove 1-2 is opened at the end of the front strut joint straight groove 1-1. Through the opened front strut joint straight groove 1-1 and the front strut joint oblique groove 1-2, and the front strut joint oblique groove 1-2 is interlaced and connected with the locking pin 2, it is convenient for connecting the support rod joint 1; the clamping pin 2 and the positioning pin 5 are both cylindrical pins made of 304 stainless steel. 304 stainless steel is a standard part, which is beneficial to reducing the production cost of the drone; the front strut joint 1, the clamping pin fixing ring 3, and the rear strut joint 6 are made of 7075 aviation aluminum alloy, which can effectively reduce the weight of the device while ensuring the strength of the device.

[0025] When used specifically, the invention provides a tapered UAV tail wing quick-release device. When installing, the clamping pin fixing ring 3 is rotated clockwise to the position, the rear strut joint 6 is docked with the front strut joint 1, and the clamping pin fixing ring 3 is released after docking. The clamping pin fixing ring 3 is driven by the torsion spring 4, and the clamping pin fixing ring 3 drives the clamping pin 2 to be clamped into the oblique groove 1-2 of the front strut joint to complete the locking. Figure 1 The locked state is shown; when disassembling, Figure 1 In the locked state, turn the clamping pin fixing ring 3 clockwise to Figure 2 That is, the clamping pin fixing ring 3 will drive the clamping pin 2 to rotate, complete the unlocking, and take out the rear support rod joint 6 backwards to complete the disassembly; the clamping pin 2 and the locating pin 5 are cylindrical pins made of 304 stainless steel, which are standard parts and are beneficial to reducing the production cost of the UAV; the front support rod joint 1, the clamping pin fixing ring 3, and the rear support rod joint 6 are made of 7075 aviation aluminum alloy, which can effectively reduce the weight of the device while ensuring the strength of the device.

[0026] In the description of the present invention, it is necessary to understand that the indicated orientation or positional relationship is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0027] In the present invention, unless otherwise clearly stipulated and limited, for example, it can be a fixed connection, a detachable connection, or an integrated one; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. Unless otherwise clearly defined, for ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0028] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A tapered UAV tail wing quick-release device, characterized in that: The UAV tail wing quick-release device comprises a front strut joint (1), a clamping pin (2), a clamping pin fixing ring (3), a torsion spring (4), a positioning pin (5), a rear strut joint (6) and a positioning pin fixing ring (7), wherein one end of the front strut joint (1) is provided with a conical concave surface, the rear strut joint (6) is fixedly provided with a conical convex surface, the conical concave surface and the conical convex surface are matched with each other, and a torsion spring (4) is sleeved between the front strut joint (1) and the rear strut joint (6), a clamping pin fixing ring (3) is provided at the connection of the front strut joint (1), clamping pin holes are fixedly provided on both sides of the outer wall of the clamping pin fixing ring (3), and the two clamping pin holes are interference-fitted with the clamping pins (2), and a positioning pin fixing ring (7) is fixedly provided at the connection of the rear strut joint (6), pin holes are provided on both sides of the outer wall of the positioning pin fixing ring (7), and the insides of the two pin holes are interference-fitted with positioning pins (5); A torsion spring fixing side force arm (4-1) is fixedly provided at one end of the torsion spring (4), and a torsion spring force applying side force arm (4-2) is fixedly provided at the other end of the torsion spring (4); A plurality of torsion spring fixed side force arm installation adjustment holes (6-2) are provided on the side of the positioning pin fixing ring (7), one of which is connected to the torsion spring fixed side force arm (4-1) through insertion; a torsion spring force side force arm installation adjustment hole (3-1) is provided on the side of the clamping pin fixing ring (3), one of which is connected to the torsion spring force side force arm (4-2) through insertion; A front strut joint straight groove (1-1) is provided at the conical concave surface of the front strut joint (1), a front strut joint oblique groove (1-2) is provided at the end of the front strut joint straight groove (1-1), and the front strut joint oblique groove (1-2) is interlacedly connected with the clamping pin (2).

2. The tapered UAV tail quick-release device according to claim 1, characterized in that: A rear support rod joint strip hole (6-1) is provided on the conical convex surface of the rear support rod joint (6), and the rear support rod joint strip hole (6-1) is interlaced and connected with the end of the clamping pin (2).

3. The tapered UAV tail quick-release device according to claim 1, characterized in that: The clamping pin (2) and the positioning pin (5) are both cylindrical pins made of 304 stainless steel.

4. The tapered UAV tail quick-release device according to claim 1, characterized in that: The front strut joint (1), the clamping pin fixing ring (3), and the rear strut joint (6) are made of 7075 aviation aluminum alloy.

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