Tail rudder locking device of vertical take-off and landing fixed-wing unmanned aerial vehicle

Abstract

The present application relates to the tail rudder technical field of fixed-wing unmanned aerial vehicle, concretely is a kind of tail rudder locking device of vertical take-off fixed-wing unmanned aerial vehicle, including fixed-wing unmanned aerial vehicle main body, the rear of fixed-wing unmanned aerial vehicle main body is provided with locking balance component;Locking balance component, the outer wall of locking balance component includes gear, the gear is engaged with gear ring, the inside of gear ring is connected with No. nut pair, the periphery of gear ring is provided with shell, locking device is set through the setting of card rudder block and rotating roller, the abrasion of fixed-wing unmanned aerial vehicle main body is reduced, card rudder block is stuck tail rudder of fixed-wing unmanned aerial vehicle main body, avoid sudden operation in the process of take-off and landing tail rudder, cause fixed-wing unmanned aerial vehicle main body to spin, avoid to cause crash accident, through the setting of balancing block, No. nut pair drives balancing block to move in the direction away from tail rudder, so that the whole reaches balance, avoid the whole to appear the phenomenon of inclination in the stage of take-off and landing.

Description

Technical Field

[0001] This invention relates to the field of tail rudder technology for fixed-wing unmanned aerial vehicles (UAVs), specifically to a tail rudder locking device for a vertical take-off and landing (VTOL) fixed-wing UAV. Background Technology

[0002] In recent years, with the development of unmanned aerial vehicle technology and the reduction of costs, fixed-wing UAVs have been widely used in various fields such as military, security, transportation, exploration, surveying and mapping, and meteorology.

[0003] However, existing vertical takeoff and landing fixed-wing UAVs need to switch between power units during takeoff, landing and cruise phases. The tail rudder may be affected by link communication interference and cannot switch normally. If the tail rudder is working during takeoff and landing, it will force the vertical takeoff and landing fixed-wing UAV to spin, causing a crash and resulting in cost losses. Summary of the Invention

[0004] The purpose of this invention is to provide a tail rudder locking device for a vertical take-off and landing fixed-wing UAV, so as to solve the problem mentioned in the background art that the tail rudder operation during the take-off and landing phase forces the vertical take-off and landing fixed-wing UAV to spin.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a tail rudder locking device for a vertical takeoff and landing fixed-wing unmanned aerial vehicle, comprising:

[0006] The main body of the fixed-wing drone, with a rudder lock balancing assembly located at the rear of the main body;

[0007] A rudder locking and balancing assembly includes a gear, a gear ring meshing with the outer wall of the gear, a first nut assembly connected inside the gear ring, a housing surrounding the gear ring, a first lead screw inside the first nut assembly, a rudder locking block connected to one end of the first lead screw, a shaft mounted on the inner side of the rudder locking block near the main body of the fixed-wing UAV, a roller connected to the outer wall of the shaft, a second lead screw mounted on the side of the gear ring away from the rudder locking block, a second nut assembly connected to the outer wall of the second lead screw, and a balancing block provided on the outer wall of the second nut assembly.

[0008] Preferably, the motor inside the fixed-wing UAV body can drive the gears to rotate.

[0009] Preferably, the toothed ring is fixedly connected to the first nut pair, and the housing is fixedly connected to the main body of the fixed-wing UAV.

[0010] Preferably, the housing has a hole corresponding to the lead screw, and the gear ring is rotatably connected to the housing.

[0011] Preferably, the housing has a hole corresponding to the second lead screw, and the first lead screw is fixedly connected to the rudder block.

[0012] Preferably, the rotating roller is rotatably connected to the shaft, and the second lead screw is fixedly connected to the toothed ring.

[0013] Preferably, the second lead screw has a groove corresponding to the first lead screw, and the second nut pair is fixedly connected to the balance block.

[0014] Compared with the prior art, the beneficial effects of the present invention are:

[0015] (1) The new rudder locking device, through the setting of the rudder locking block and the rotating roller, allows the motor inside the fixed-wing UAV to drive the gear to rotate when the fixed-wing UAV is preparing to land. The gear drives the gear ring to rotate, the gear ring drives the first nut pair to rotate, the first nut pair drives the first lead screw to move towards the tail rudder, the first lead screw drives the rudder locking block to move towards the tail rudder, and the rotating roller is in a rolling connection with the fixed-wing UAV body, which reduces the wear of the fixed-wing UAV body. The rudder locking block locks the tail rudder of the fixed-wing UAV body, preventing the tail rudder from suddenly operating during take-off and landing, which would cause the fixed-wing UAV body to spin and avoid causing a crash.

[0016] (2) The new type of rudder locking device, through the setting of the balance block, when the gear drives the gear ring to rotate, the gear ring can drive the No. 2 lead screw to rotate, the No. 2 lead screw can drive the No. 2 nut pair to move away from the tail rudder, and the No. 2 nut pair drives the balance block to move away from the tail rudder, so that the whole reaches the balance and avoids the phenomenon of the whole tilting during the take-off and landing phase. Attached image description:

[0017] Figure 1 This is a front view of the overall structure of the present invention;

[0018] Figure 2 This is a schematic diagram of the rudder balancing assembly of the present invention;

[0019] Figure 3 For the present invention Figure 2 Schematic diagram of part A in the middle;

[0020] Figure 4 This is a schematic diagram of the internal structure of the housing of the present invention;

[0021] Figure 5 This is an exploded view of the rudder balancing assembly of the present invention.

[0022] In the diagram: 01, main body of the fixed-wing UAV; 02, rudder lock and balance assembly; 21, gear; 22, gear ring; 23, first nut pair; 24, shell; 25, first lead screw; 26, rudder lock block; 27, shaft; 28, roller; 29, second lead screw; 30, second nut pair; 31, balance block. Detailed implementation method:

[0023] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0024] Please see Figure 1-5 The present invention provides an embodiment of a tail rudder locking device for a vertical take-off and landing fixed-wing UAV. The fixed-wing UAV body 01, the first nut pair 23 and the second nut pair 30 used in this application are all products that can be directly purchased on the market. Their principles and connection methods are existing technologies well known to those skilled in the art, so they will not be described in detail here.

[0025] Includes: a fixed-wing UAV body 01, with a rudder lock balancing assembly 02 located at the rear of the fixed-wing UAV body 01;

[0026] The rudder locking and balancing assembly 02 includes a gear 21, with a gear ring 22 meshing on its outer wall. The gear ring 22 drives a second lead screw 29 to rotate, which in turn moves a second nut assembly 30. The second nut assembly 30 then moves a balance block 31. A first nut assembly 23 is connected inside the gear ring 22. A housing 24 surrounds the gear ring 22, providing protection. A first lead screw 25 is located inside the first nut assembly 23, which drives a rudder locking block 26 to move. The rudder locking block 26 locks the tail rudder of the fixed-wing UAV body 01, preventing the tail rudder from activating during takeoff and landing. One end of the rod 25 is connected to a rudder block 26. The rudder block 26 is mounted on the inner side of the fixed-wing UAV body 01. The outer wall of the rudder block 27 is connected to a roller 28. The roller 28 rolls on the fixed-wing UAV body 01, reducing the wear of the fixed-wing UAV body 01. The toothed ring 22 is mounted on the side away from the rudder block 26 with a second lead screw 29. The outer wall of the second lead screw 29 is connected to a second nut pair 30. The outer wall of the second nut pair 30 is provided with a balance block 31. The total weight of the second nut pair 30 and the balance block 31 is basically the same as the total weight of the rudder block 26, the rudder block 27 and the roller 28. During the take-off and landing phase, the whole will not tilt significantly.

[0027] Furthermore, the motor inside the fixed-wing UAV body 01 can drive the gear 21 to rotate, ensuring that the rotation of the gear 21 can be controlled by the fixed-wing UAV body 01, making it convenient to operate.

[0028] Furthermore, the gear ring 22 is fixedly connected to the first nut pair 23, ensuring that the gear ring 22 can drive the first nut pair 23 to rotate, the first nut pair 23 can drive the first lead screw 25 to move, the first lead screw 25 can drive the rudder block 26 to move, and the shell 24 is fixedly connected to the main body 01 of the fixed-wing UAV. The shell 24 plays a protective role and ensures the stability of the shell 24.

[0029] Furthermore, the housing 24 has a hole corresponding to the first lead screw 25 to ensure that the housing 24 does not affect the movement of the first lead screw 25. The movement of the first lead screw 25 can drive the rudder block 26 to move. The gear ring 22 is rotatably connected to the housing 24. The rotation of the gear ring 22 can drive the second lead screw 29 to rotate, which can drive the first nut pair 23 to rotate.

[0030] Furthermore, the housing 24 has a hole corresponding to the second lead screw 29 to ensure that the housing 24 does not affect the rotation of the second lead screw 29. The first lead screw 25 is fixedly connected to the locking block 26 to ensure that the first lead screw 25 can drive the locking block 26 to move. The locking block 26 can lock the tail rudder of the fixed-wing UAV body 01 to prevent the tail rudder from working during takeoff and landing.

[0031] Furthermore, the rotating roller 28 is rotatably connected to the shaft 27. The rotating roller 28 rolls on the fixed-wing UAV body 01, reducing the wear of the fixed-wing UAV body 01. The second lead screw 29 is fixedly connected to the gear ring 22, ensuring that the gear ring 22 can drive the second lead screw 29 to rotate. The second lead screw 29 drives the second nut pair 30 to move, and the second nut pair 30 drives the balance block 31 to move.

[0032] Furthermore, the second lead screw 29 has a groove corresponding to the first lead screw 25, ensuring that the first lead screw 25 can be inserted into the groove of the second lead screw 29 without affecting the movement of the first lead screw 25, and thus without affecting the movement of the rudder block 26. The second nut assembly 30 is fixedly connected to the balance block 31, ensuring that the second nut assembly 30 can drive the balance block 31 to move. The balance block 31 and the rudder block 26 move relative to each other without affecting the balance of the overall structure.

[0033] Working Principle: During use, when the fixed-wing UAV is preparing to land, the motor inside the UAV body 01 drives the gear 21 to rotate. The gear 21 drives the gear ring 22 to rotate, which in turn drives the first nut assembly 23 to rotate. The first nut assembly 23 drives the first lead screw 25 to move towards the tail rudder. The first lead screw 25 then drives the rudder locking block 26 to move towards the tail rudder. The rotating roller 28 is in a rolling connection with the fixed-wing UAV body 01. The rudder locking block 26 locks the tail rudder of the fixed-wing UAV body 01. At the same time, the gear ring 22 drives the second lead screw 29 to rotate. The second lead screw 29 drives the second nut assembly 30 to move away from the tail rudder. The second nut assembly 30 then drives the balance block 31 to move away from the tail rudder, thus achieving overall balance. The above is the complete working principle of this invention.

[0034] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. A tail rudder locking device for a vertical takeoff and landing fixed-wing unmanned aerial vehicle, characterized in that, include: A fixed-wing unmanned aerial vehicle (UAV) body (01), wherein a rudder balancing assembly (02) is provided at the rear of the fixed-wing UAV body (01); A rudder balancing assembly (02) includes a gear (21), a gear ring (22) meshing with the outer wall of the gear (21), a first nut pair (23) connected inside the gear ring (22), a housing (24) provided around the gear ring (22), a first lead screw (25) provided inside the first nut pair (23), a rudder locking block (26) connected to one end of the first lead screw (25), a shaft (27) installed on the inner side of the rudder locking block (26) near the main body (01) of the fixed-wing UAV, a roller (28) connected to the outer wall of the shaft (27), a second lead screw (29) installed on the side of the gear ring (22) away from the rudder locking block (26), a second nut pair (30) connected to the outer wall of the second lead screw (29), and a balance block (31) provided on the outer wall of the second nut pair (30).

2. The tail rudder locking device for a vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that: The motor inside the main body (01) of the fixed-wing UAV can drive the gear (21) to rotate.

3. The tail rudder locking device for a vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that: The toothed ring (22) is fixedly connected to the first nut pair (23), and the housing (24) is fixedly connected to the main body (01) of the fixed-wing UAV.

4. The tail rudder locking device for a vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that: The housing (24) has a hole corresponding to the lead screw (25), and the toothed ring (22) is rotatably connected to the housing (24).

5. The tail rudder locking device for a vertical takeoff and landing fixed-wing UAV according to claim 2, characterized in that: The housing (24) has a hole corresponding to the second lead screw (29), and the first lead screw (25) is fixedly connected to the rudder block (26).

6. The tail rudder locking device for a vertical takeoff and landing fixed-wing unmanned aerial vehicle according to claim 3, characterized in that: The roller (28) is rotatably connected to the shaft (27), and the second lead screw (29) is fixedly connected to the toothed ring (22).

7. The tail rudder locking device for a vertical takeoff and landing fixed-wing UAV according to claim 4, characterized in that: The second lead screw (29) has a groove corresponding to the first lead screw (25), and the second nut pair (30) is fixedly connected to the balance block (31).

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