Steering engine mounting mechanism for freight fixed-wing unmanned aerial vehicle

Abstract

The utility model discloses a steering engine installation mechanism for a freight fixed-wing unmanned aerial vehicle, relates to the technical field of steering engines, and solves the problems that when the steering engines are installed, the steering engines are installed in the side walls of wings, so that the steering engines are completely located in grooves of the wings, the steering engine installation space only can wrap the whole steering engines, and the installation cost is low. According to the technical scheme, the problems that due to the fact that the space of an installation groove is small, the needed space is insufficient when a steering engine is installed and disassembled, and disassembly and installation are inconvenient are solved, the wing comprises a wing body and the steering engine, the installation groove is formed in the bottom face of the wing body, and the steering engine is installed in the installation groove, and after the steering engine is installed in the installation groove, the steering engine is installed in the installation groove. The limiting columns penetrate through the interiors of the supporting blocks of the steering engines, then penetrate through the interiors of the wings through the interiors of the supporting blocks till entering the positions above the wings, and are connected to the threaded columns through hexagon nuts, so that the installation work of the steering engines is facilitated, and the installation efficiency is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of rudder mechanism, specifically is a rudder mechanism mounting mechanism for freight fixed wing unmanned plane. BACKGROUND

[0002] The rudder mechanism of the unmanned plane needs to constantly adjust the attitude in the complex environment during the flight of the unmanned plane, and the rudder mechanism helps the unmanned plane to quickly adjust the attitude by accurately controlling the angle change of the control surface, so as to ensure the flight stability and safety.

[0003] According to the search, the patent with the patent publication number CN215285245U discloses a rudder mechanism mounting structure for an unmanned plane and the unmanned plane, which comprises: a wing rear beam, the wing rear beam is provided with a mounting port; a mounting groove, one end of the mounting groove is connected to the mounting port, and the other end extends to the inside of the wing; an ear tab joint, the ear tab joint is arranged at the other end of the mounting groove; a rudder mechanism is arranged in the mounting groove, and the end of the rudder mechanism is connected with the ear tab joint. The structure does not need to open a hole in the skin to install the rudder mechanism in the inside of the wing, so as to ensure the strength and firmness of the wing.

[0004] When the rudder mechanism is installed, the rudder mechanism is installed in the inside of the side wall of the wing, so that the rudder mechanism is completely in the groove of the wing, and the space for installing the rudder mechanism can only wrap the whole rudder mechanism, the space of the mounting groove is small, and the space required for installing and dismounting the rudder mechanism is insufficient, which is not convenient for dismounting and installing. UTILITY MODEL CONTENTS

[0005] In view of the defects of the prior art, the utility model provides a rudder mechanism mounting mechanism for a freight fixed wing unmanned plane, which solves the problems that when the rudder mechanism is installed, the rudder mechanism is installed in the inside of the side wall of the wing, so that the rudder mechanism is completely in the groove of the wing, the space for installing the rudder mechanism can only wrap the whole rudder mechanism, the space of the mounting groove is small, and the space required for installing and dismounting the rudder mechanism is insufficient, which is not convenient for dismounting and installing.

[0006] To achieve the above purpose, the utility model is implemented by the following technical scheme: a rudder mechanism mounting mechanism for a freight fixed wing unmanned plane, comprising a wing and a rudder mechanism, an installation groove is arranged in the inside of the bottom surface of the wing, the rudder mechanism is installed in the inside of the installation groove, support blocks are fixedly installed on the two side walls of the lower end of the rudder mechanism, limit columns are symmetrically and slidably connected in the insides of the support blocks, threaded columns are welded to the upper ends of the limit columns, the threaded columns enter the upper side of the wing by penetrating the upper end side wall of the installation groove, hexagonal nuts are threadedly sleeved on the rod walls of the threaded columns, and the hexagonal nuts are arranged in the upper side of the wing.

[0007] Preferably, the upper part of the wing is provided with a clamping plate, a plurality of fish fins are fixedly installed at the upper end of the clamping plate at equal intervals, fixed bolts are symmetrically and threadedly connected inside the two ends of the clamping plate, the fixed bolts are threadedly connected to the inside of the top surface of the wing through the inside of the clamping plate, clamping holes are symmetrically arranged inside the two sides of the bottom surface of the clamping plate, and the clamping holes are slidably sleeved on the hexagonal nuts, so that the position of the hexagonal nut can be conveniently limited.

[0008] Preferably, the bottom surface of the limiting column is fixedly installed with a fixed block, the bottom surface of the fixed block is fixedly installed with a limiting rod, the limiting rod penetrates the inside of the supporting block and is slidably connected with the inside of the supporting block, so that the position of the limiting column can be prevented from rotating after installation, thereby preventing the position of the rudder from loosening.

[0009] Preferably, the top surface of the hexagonal nut after installation is horizontal with the top surface of the threaded column, so that the installation of the threaded column on the clamping plate can be prevented.

[0010] Preferably, the shape and size of the clamping hole are matched with those of the hexagonal nut, so that the installation of the hexagonal nut is more stable.

[0011] Preferably, the length of the limiting rod is smaller than the height of the supporting block, so that the position of the limiting rod can be prevented from affecting the internal arrangement of the connecting line.

[0012] The utility model provides a rudder installation mechanism for cargo fixed wing unmanned plane. Has the following beneficial effects:

[0013] 1. The rudder installation mechanism for cargo fixed wing unmanned plane, when using the rudder installation mechanism for cargo fixed wing unmanned plane, the limiting column penetrates the inside of the supporting block of the rudder after the rudder is installed in the inside of the installation slot, then penetrates the inside of the wing through the inside of the supporting block, until entering the upper part of the wing, and connecting the threaded column with the hexagonal nut, the installation of the rudder is convenient, and the installation efficiency is improved.

[0014] 2. The rudder installation mechanism for cargo fixed wing unmanned plane, when using the rudder installation mechanism for cargo fixed wing unmanned plane, the position of the hexagonal nut can be limited by the clamping groove on the clamping plate sleeved on the hexagonal nut, the hexagonal nut can be prevented from loosening, and the stability of the rudder after installation is improved. ACCURACY OF DRAWINGS

[0015] Figure 1 It is the overall structure schematic diagram of the utility model;

[0016] Figure 2 It is the top surface structure schematic diagram of the utility model;

[0017] Figure 3A bottom surface structure structure schematic view of the utility model is shown in the figure.

[0018] Figure 4 A rudder structure schematic view of the utility model is shown in the figure.

[0019] Figure 5 A clamping plate structure schematic view of the utility model is shown in the figure.

[0020] Figure 6 A limiting column structure schematic view of the utility model is shown in the figure.

[0021] In the figure, 1 - wing, 2 - clamping plate, 3 - fish fin, 4 - fixed bolt, 5 - hexagon nut, 6 - threaded column, 7 - installation slot, 8 - rudder, 9 - support block, 10 - limiting column, 11 - clamping hole, 12 - limiting rod, 13 - limiting block. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.

[0023] Embodiment 1

[0024] Please refer to Figures 1-6This utility model embodiment provides a servo mounting mechanism for a cargo fixed-wing UAV, including a wing 1 and a servo 8. A mounting groove 7 is provided inside the bottom surface of the wing 1, and the servo 8 is mounted inside the mounting groove 7. Support blocks 9 are fixedly mounted on both lower side walls of the servo 8, and limit posts 10 are symmetrically slidably connected inside the support blocks 9. Threaded posts 6 are welded to the upper ends of the limit posts 10. The threaded posts 6 penetrate through the upper side walls of the mounting groove 7 and extend above the wing 1. Hexagonal nuts 5 are threaded onto the rod walls of the threaded posts 6, and the hexagonal nuts 5 are all located above the wing 1. Fixing blocks 13 are fixedly mounted on the bottom surface of the limit posts 10, and limit posts 13 are fixedly mounted on the bottom surface of the fixing blocks 13. Rod 12 and limit rod 12 pass through the interior of support block 9 and are slidably connected to the interior of support block 9. The length of limit rod 12 is less than the height of support block 9. When installing servo 1, first, limit post 10 passes through the interior of support block 9, and limit rod 12 passes through the interior of support block 9 to prevent the position of limit post 10 from rotating. Then, servo 8 is placed inside mounting slot 7, and the upper end of limit post 10 passes through the upper side wall of mounting slot 7 until threaded post 6 enters the exterior of wing 1. Hexagonal nuts 6 are threaded onto threaded post 6, which facilitates the installation of servo 8 and also makes disassembly easier.

[0025] Example 2

[0026] To facilitate fixing the position of the hexagonal nut 5 after installation, in this embodiment, as follows: Figures 1-5 As shown, a retaining plate 2 is installed above the wing 1. Multiple fins 3 are fixedly installed at equal intervals on the upper end of the retaining plate 2. Both ends of the retaining plate 2 are symmetrically threaded with fixing bolts 4, and the fixing bolts 4 are connected to the top surface of the wing 1 through the internal threads of the retaining plate 2. The bottom surface of the retaining plate 2 is symmetrically provided with retaining holes 11 on both sides, and the retaining holes 11 are slidably fitted onto hexagonal nuts 5. The top surface of the hexagonal nuts 5 after installation is horizontal with the top surface of the threaded post 6. The shape and size of the retaining holes 11 match the shape and size of the hexagonal nuts 5. After the hexagonal thread 6 is installed and secured, the pull plate 2 is installed so that the buckles 11 on the retaining plate 2 are respectively fitted onto the hexagonal nuts 6 until the bottom surface of the retaining plate 2 is in contact with the top surface of the wing 1. Then, the fixing bolts 4 are inserted through the interior of the retaining plate 2 until the fixing bolts 4 are threaded into the top surface of the wing 1, so that the retaining plate 2 is installed securely. At the same time, the use of fins 3 not only increases the aesthetics, but also reduces wind resistance.

[0027] It should be noted that, in this embodiment, when using the servo mounting mechanism of the cargo fixed-wing UAV, such as Figures 1-6As shown, when the rudder 1 is installed, first, the limiting columns 10 are respectively penetrated into the inside of the supporting blocks 9, and the limiting rods 12 are penetrated into the inside of the supporting blocks 9, so that the positions of the limiting columns 10 are prevented from rotating, then the rudder 8 is placed in the inside of the installation groove 7, the upper ends of the limiting columns 10 are penetrated into the inside of the upper end side walls of the installation groove 7, until the threaded columns 6 enter into the outside of the wing 1, the hexagonal nuts 6 are respectively threadedly sleeved on the threaded columns 6, so that the installation of the rudder 8 is convenient, and the dismounting work is also facilitated, after the positions of the hexagonal nuts 6 are installed stably, the clamping plate 2 is installed, the buckles 11 on the clamping plate 2 are respectively sleeved on the hexagonal nuts 6, until the bottom surface of the clamping plate 2 is attached to the top surface of the wing 1, then the fixing bolts 4 are penetrated into the inside of the clamping plate 2, until the fixing bolts 4 are threadedly connected into the inside of the top surface of the wing 1, so that the clamping plate 2 is installed stably, and the fish fin 3 not only can increase the beauty, but also can reduce the wind resistance.

[0028] The basic principle and main features of the present application and the advantages of the present application are shown and described above. It is obvious for those skilled in the art that the present application is not limited to the details of the above-mentioned exemplary embodiments, and the present application can be realized in other specific forms without departing from the spirit or basic characteristics of the present application. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting, and the scope of the present application is defined by the appended claims rather than the above description, and therefore all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present application. Any reference signs in the claims should not be regarded as limiting the claims involved.

[0029] In addition, it should be understood that, although the present specification is described in terms of embodiments, not every embodiment contains only one independent technical solution, and the description manner of the specification is only for the sake of clarity, and those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that those skilled in the art can understand.

Claims

1. A servo mounting mechanism for a cargo fixed-wing drone, characterized by: The utility model relates to a wing and rudder, the bottom of the wing (1) is internally provided with a mounting groove (7), the rudder (8) is installed in the mounting groove (7), the lower end of the rudder (8) is fixedly provided with a support block (9) on both sides, the inside of the support block (9) is symmetrically connected with a limiting column (10), the upper end of the limiting column (10) is welded with a threaded column (6), the threaded column (6) penetrates the upper end of the mounting groove (7) and enters the upper of the wing (1), the rod wall of the threaded column (6) is screwed with a hexagon nut (5), and the hexagon nut (5) is arranged above the wing (1).

2. The servo mounting mechanism for cargo fixed-wing drones according to claim 1, characterized in that: The upper of the wing (1) is provided with a clamping plate (2), a plurality of fish fins (3) are fixedly installed on the upper end of the clamping plate (2) at equal intervals, a fixing bolt (4) is symmetrically screwed in the both ends of the clamping plate (2), the fixing bolt (4) is screwed in the top of the wing (1) through the inside of the clamping plate (2), the inside of the both sides of the bottom of the clamping plate (2) is symmetrically provided with a clamping hole (11), and the clamping hole (11) is slidably connected to the hexagon nut (5).

3. The servo mounting mechanism for cargo fixed-wing drones according to claim 1, characterized in that: The bottom of the limiting column (10) is fixedly provided with a fixing block (13), the bottom of the fixing block (13) is fixedly provided with a limiting rod (12), the limiting rod (12) penetrates the inside of the support block (9), and the inside of the support block (9) is slidably connected.

4. The servo mounting mechanism for cargo fixed-wing drones of claim 1, wherein: The top of the hexagon nut (5) is horizontal with the top of the threaded column (6).

5. The servo mounting mechanism for cargo fixed-wing drones of claim 2, wherein: The shape and size of the clamping hole (11) are matched with the shape and size of the hexagon nut (5).

6. The servo mounting mechanism for cargo fixed-wing drones according to claim 3, characterized in that: The length of the limiting rod (12) is smaller than the height of the support block (9).

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