Unmanned aerial vehicle flight control box

Abstract

The invention relates to the technical field of unmanned aerial vehicle equipment, in particular to an unmanned aerial vehicle flight control box which comprises a bracket, a box body and a three-dimensional damping mechanism, and a locking assembly is arranged on one side of the bracket; the box body is arranged on the bracket, a spring bolt is arranged on the box body, and the spring bolt is inserted into the locking assembly to enable the box body to be installed on the bracket. The three-dimensional damping mechanism is arranged in the box body and used for installing a flight control board. Through the locking structure of the spring bolt and the locking assembly and the positioning matching of the limiting pin and the limiting hole, the box body is quickly mounted and dismounted, bolts do not need to be dismounted one by one, and the maintenance efficiency is greatly improved. A three-dimensional secondary damping mechanism composed of a plurality of damping pieces is adopted, all-directional damping is conducted on the flight control board from the upper portion and the lower portion in the vertical direction and the left side and the right side in the horizontal direction, the influence of fuselage vibration on the flight control board is weakened to the maximum degree, meanwhile, only targeted damping is conducted on the flight control board, and the damping effect and the equipment lightweight requirement are both considered.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicle equipment, and particularly relates to a flight control box of an unmanned aerial vehicle. BACKGROUND

[0002] The flight control box is a key core component of the unmanned aerial vehicle, and bears the important responsibility of flight control and management. The working stability of the flight control box directly determines the flight safety of the unmanned aerial vehicle. The existing flight control box of the unmanned aerial vehicle has many deficiencies in actual application. Firstly, the disassembly and assembly process of the flight control box and the fuselage is complicated. When maintenance, repair or program updating is needed, a plurality of fixing members need to be disassembled, which consumes a lot of time and is low in efficiency. Secondly, the vibration generated during the flight of the unmanned aerial vehicle is easily transmitted to the flight control board. As a sensitive electrical element, the vibration will seriously affect the working stability and reliability of the flight control board, and even cause failure. SUMMARY

[0003] The present application provides a flight control box of an unmanned aerial vehicle to solve the problem of complicated disassembly and assembly process of the flight control box and the fuselage in the prior art.

[0004] The present application provides a flight control box of an unmanned aerial vehicle, comprising: A bracket, one side of the bracket is provided with a locking assembly; A box body, the box body is arranged on the bracket, and a locking tongue is arranged on the box body. The locking tongue is inserted into the locking assembly to enable the box body to be mounted on the bracket; A three-dimensional damping mechanism, the three-dimensional damping mechanism is arranged in the interior of the box body and is used for mounting a flight control board.

[0005] In a possible design, the locking assembly comprises: A locking shaft, one end of the locking shaft is rotationally connected with the bracket, and the other end is a free end; A locking ring, the locking ring is sleeved on the locking shaft and is threadedly connected with the locking shaft. An end surface of the locking ring is formed with an outer ring and an inner ring which extend along the axial direction of the locking ring. The locking shaft is capable of enabling the end of the locking tongue to be inserted between the outer ring and the inner ring by rotating a preset angle. The locking ring is capable of enabling the upper surface of the locking tongue to abut against the inner wall of the outer ring and the lower surface of the locking tongue to abut against the outer wall of the inner ring by threadedly rotating around the locking shaft.

[0006] In a possible design, the locking tongue is in an arc structure.

[0007] In a possible design, the locking assembly further comprises a stop ring, the stop ring is sleeved on the locking shaft and is circumferentially limited by the locking shaft. The stop ring and the locking ring are respectively provided with saw-shaped teeth at one end close to each other. The saw-shaped teeth are engaged with each other / detached from each other by sliding the stop ring along the axial direction of the locking shaft to approach / away from the locking ring.

[0008] In a possible design, the locking assembly further comprises a compression spring, which is sleeved on the locking shaft, one end of which abuts against the free end, and the other end of which abuts against the end face of the stop ring.

[0009] In a possible design, the other side of the bracket is provided with a limiting pin, and the box body is provided with a limiting hole corresponding to the limiting pin.

[0010] In a possible design, the three-dimensional damping mechanism comprises: The box body is mounted on the inner bottom wall of the box body through the lower damping member, and the flight control board is installed in the box body; The side bracket is mounted on the inner bottom wall of the box body, and the side bracket and the side wall of the box body are connected through the side damping member; The upper bracket is mounted on the upper end of the side bracket, and the upper bracket and the upper end of the box body are connected through the upper damping member.

[0011] In a possible design, the box body comprises a lower box body, a plate seat, an upper box body and a top cover connected in sequence from top to bottom, the lower end face of the lower box body is connected with the box body through the lower damping member, and the axis of the lower damping member is vertically arranged; the side wall of the lower box body is connected with the side bracket through the side damping member, and the axis of the side damping member is horizontally arranged; the upper damping members are uniformly distributed around the top cover and are respectively connected with the upper bracket, the axis of the upper damping member is horizontally arranged, and the axes of adjacent two upper damping members are perpendicular.

[0012] In a possible design, the top cover is provided with a filling port.

[0013] In a possible design, the box body comprises box walls connected with each other, the adjacent two box walls are matched in concave-convex mode, the conductive rubber pads are arranged on the matching faces respectively, and the box wall is further provided with a grounding column.

[0014] The beneficial effects of the present application are as follows: The unmanned aerial vehicle flight control box of the present application realizes rapid installation and disassembly of the box body through the locking structure of the locking tongue and the locking assembly, the positioning and matching of the limiting pin and the limiting hole, without disassembling the bolts one by one, which greatly improves the maintenance efficiency; the design of the saw-shaped tooth and the compression spring in the locking assembly ensures the stability of the locking state and effectively prevents loosening caused by body vibration.

[0015] The three-dimensional secondary damping mechanism composed of multiple damping members performs omnidirectional damping on the flight control board from the vertical direction of the upper and lower parts and the horizontal direction of the left and right sides, maximally weakens the influence of body vibration on the flight control board, and simultaneously performs targeted damping on the flight control board, taking into account the damping effect and the lightweight requirement of the equipment.

[0016] The box body is made of conductive aluminum alloy material, cooperates with the convex structure of the upper cover plate and the lower bottom plate to reduce electromagnetic signal penetration through the gap, realizes the equipotential grounding of the box body and the fuselage through the grounding column, avoids the formation of a ground loop, effectively blocks external electromagnetic signal interference, and ensures the stable operation of the flight control circuit.

[0017] The concave-convex matching structure of adjacent box walls cooperates with the conductive rubber pad and the waterproof rubber pad at the plug-in part to form multiple waterproof barriers, reduce the entry of water vapor and rainwater into the box, delay the aging of components, and improve the service life of the equipment.

[0018] The box body is designed in a split type, and each plate can be individually disassembled. A program filling opening is formed on the top cover to facilitate flight control board program updating without the need to disassemble the entire equipment, reducing maintenance difficulty. The aluminum alloy material has good thermal conductivity, the grid structure on the surface of the box body increases the heat dissipation area, cooperates with the flat layout of electrical components, improves the heat dissipation efficiency, and avoids equipment failure caused by high temperature. BRIEF DESCRIPTION OF DRAWINGS

[0019] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the following will briefly introduce the drawings needed to be used in the description of the specific embodiments or the prior art. Obviously, the drawings described below are some embodiments of the present application, and those skilled in the art can also obtain other drawings according to these drawings without creative labor.

[0020] Figure 1 The structure schematic diagram of the unmanned aerial vehicle flight control box provided by the embodiment of the present application is shown in the figure. Figure 2 The structure schematic diagram of the bracket of the unmanned aerial vehicle flight control box provided by the embodiment of the present application is shown in the figure. Figure 3 The structure schematic diagram of the box body of the unmanned aerial vehicle flight control box provided by the embodiment of the present application is shown in the figure. Figure 1 ; Figure 4 The structure schematic diagram of the box body of the unmanned aerial vehicle flight control box provided by the embodiment of the present application is shown in the figure. Figure 2 ; Figure 5 The part drawing of the locking assembly of the unmanned aerial vehicle flight control box provided by the embodiment of the present application is shown in the figure. Figure 6 The assembly drawing of the locking assembly of the unmanned aerial vehicle flight control box provided by the embodiment of the present application is shown in the figure. Figure 7 The structure schematic diagram of the three-dimensional damping mechanism of the unmanned aerial vehicle flight control box provided by the embodiment of the present application is shown in the figure.

[0021] Reference signs: 100. Bracket; 110. Locking assembly; 111. Locking shaft; 1111. Cutting surface; 112. Locking ring; 1121. Outer ring; 1122. Inner ring; 113. Stop ring; 114. Compression spring; 120. Limit pin; 200. Housing; 210. Locking tongue; 220. Limiting hole; 230. Grounding post; 300. Three-dimensional vibration damping mechanism; 311. Lower housing; 312. Plate base; 313. Upper housing; 314. Top cover; 3141. Program filling port; 320. Side bracket; 330. Upper bracket; 340. Lower vibration damper; 350. Side vibration damper; 360. Upper vibration damper; 400. Primary vibration damping bolt. Detailed Implementation

[0022] The technical solutions of this application will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0023] The following is combined with Figures 1-7 This describes the drone flight control box provided in the embodiments of this application.

[0024] Reference Figure 1 As shown in the embodiment of this application, a drone flight control box includes a bracket 100, a box body 200, and a three-dimensional shock absorption mechanism 300. The components work together to achieve stable installation, quick assembly and disassembly of the flight control box, and effective protection of the flight control board.

[0025] Reference Figure 2 , Figure 3 As shown, the bracket 100 provides mounting support for the housing 200. A locking component 110 is provided on one side of the bracket 100. The housing 200 is quickly fixed by the cooperation of the locking component 110 and the housing 200. The housing 200 is mounted on the bracket 100 and is provided with a locking tongue 210. The locking tongue 210 is inserted into the locking component 110 to install the housing 200 on the bracket 100. This plug-in structure of the locking tongue 210 and the locking component 110 eliminates the traditional multi-bolt fixing method, greatly simplifies the installation process of the housing 200 and the bracket 100, eliminates the need to remove the bolts one by one, significantly improves the efficiency of disassembly and assembly, and facilitates subsequent maintenance, repair or program update of the flight control box.

[0026] Reference Figure 4As shown, the other side of the bracket 100 is provided with a limiting pin 120120, and the box body 200 is provided with a limiting hole 220 opposite to the limiting pin 120120. When the box body 200 is installed, the limiting pin 120120 is inserted into the limiting hole 220 to accurately position the installation position of the box body 200, so that the locking tongue 210 can be accurately aligned with the locking assembly 110, thereby improving the installation efficiency. Meanwhile, the cooperation between the limiting pin 120120 and the limiting hole 220 can form a transverse limiting for the box body 200, so as to avoid the transverse shaking of the box body 200 during flight, and form a three-dimensional space limiting together with the locking assembly 110, thereby further improving the stability of the installation of the box body 200.

[0027] Referring to Figure 5 As shown, in some embodiments, the locking assembly 110 includes a locking shaft 111 and a locking ring 112. One end of the locking shaft 111 is rotationally connected with the bracket 100, and the other end is a free end. The locking ring 112 is sleeved on the locking shaft 111 and is in threaded cooperation with the locking shaft 111. The end face of the locking ring 112 is formed with an outer ring 1121 and an inner ring 1122 extending in the axial direction thereof. The locking shaft 111 can make the end of the locking tongue 210 inserted between the outer ring 1121 and the inner ring 1122 by rotating a predetermined angle. The locking ring 112 can make the upper surface of the locking tongue 210 abut against the inner wall of the outer ring 1121 and the lower surface of the locking tongue 210 abut against the outer wall of the inner ring 1122 by rotating around the locking shaft 111. The annular gap formed by the outer ring 1121 and the inner ring 1122 limits the locking tongue 210 in the circumferential direction. Then, the locking ring 112 is axially moved by using the threaded transmission to clamp and fix the upper and lower surfaces of the locking tongue 210. This double limiting and clamping structure makes the connection between the box body 200 and the bracket 100 more firm and reliable, effectively avoids the loosening of the box body 200 due to vibration during flight of the unmanned aerial vehicle, and further improves the convenience of disassembly and assembly by using the threaded transmission which only needs to rotate the locking ring 112 to complete the locking.

[0028] Further, referring to Figure 3 As shown, the locking tongue 210 has an arc-shaped structure to adapt to the shapes of the outer ring 1121 and the inner ring 1122. The arc-shaped locking tongue 210 has a higher adhesion and a larger contact area with the inner walls of the annular outer ring 1121 and the inner ring 1122. This not only makes the process of inserting the locking tongue 210 between the outer ring 1121 and the inner ring 1122 more smooth, but also forms a more stable stress structure after locking to avoid local stress concentration and damage to the components, and improves the sealing performance after locking to reduce the penetration of external impurities or moisture from the cooperation gap.

[0029] In some embodiments, the locking assembly 110 further comprises a stop ring 113 sleeved on the locking shaft 111 and circumferentially limited by the locking shaft 111. The stop ring 113 and the locking ring 112 are respectively provided with sawtooth teeth at one end close to each other. The sawtooth teeth are engaged / disengaged by the stop ring 113 sliding towards / away from the locking ring 112 along the axial direction of the locking shaft 111. Specifically, the locking shaft 111 is formed with cutting surfaces 1111 extending along the axial direction of the locking shaft 111 at opposite sides thereof. The center of the stop ring 113 is provided with a rectangular hole in sliding cooperation with the cutting surfaces 1111. By engaging the sawtooth teeth on the stop ring 113 and the locking ring 112, the locking ring 112 is circumferentially fixed, effectively preventing the locking ring 112 from accidentally rotating due to the vibration of the unmanned aerial vehicle during flight, thereby avoiding the loosening of the box 200 and ensuring the stability of the locking structure. The cutting surfaces 1111 of the locking shaft 111 and the rectangular hole of the stop ring 113 cooperate to achieve the circumferential limitation of the stop ring 113 and the locking shaft 111, ensuring that the stop ring 113 can only slide axially along the locking shaft 111 and cannot rotate relative to the locking shaft 111, and ensuring that the sawtooth teeth can be precisely engaged.

[0030] Referring to Figure 6 In some embodiments, the free end of the locking shaft 111 is sleeved with an end cap, and the locking assembly 110 further comprises a compression spring 114 sleeved on the locking shaft 111, one end of the compression spring 114 abutting against the end cap of the free end, and the other end abutting against the end face of the stop ring 113. The compression spring 114 continuously applies an axial compression force to the stop ring 113, so that the sawtooth teeth on the stop ring 113 and the locking ring 112 are always in close engagement, preventing the stop ring 113 from retreating along the axial direction and causing the sawtooth teeth to disengage, further enhancing the locking effect of the locking ring 112, avoiding the failure of the locking structure in a vibrating environment, and improving the reliability of the installation of the flight control box.

[0031] Referring to Figure 1 , Figure 7 The three-dimensional damping mechanism 300 is arranged in the interior of the box 200 and is used for installing the flight control board. Through the buffering effect of the three-dimensional damping mechanism 300, the influence of the vibration generated during the flight of the unmanned aerial vehicle on the flight control board can be effectively weakened, the electronic components on the flight control board are prevented from loosening, being damaged or abnormally working due to vibration, the working stability and reliability of the flight control board are ensured, and compared with the design of damping the entire box 200, the damping mechanism is arranged only for the flight control board, the overall weight of the equipment can be reduced as much as possible on the premise of ensuring the damping effect, and the lightweight design requirement of the unmanned aerial vehicle is met.

[0032] Further, the three-dimensional damping mechanism 300 comprises a box body, a side support 320 and an upper support 330. The box body is mounted to the inner bottom wall of the box body 200 by a lower damping member 340, and the box body is used to mount the flight control board. The side support 320 is mounted to the inner bottom wall of the box body 200, and the side support 320 is connected with the side wall of the box body by a side damping member 350. The upper support 330 is mounted to the upper end of the side support 320, and the upper support 330 is connected with the upper end of the box body by an upper damping member 360. The box body provides a separate mounting space for the flight control board. The lower damping member 340, the side damping member 350 and the upper damping member 360 respectively elastically support the box body from the top, the left and right and the front and back three dimensions, form a full three-dimensional damping protection, can effectively absorb the multi-directional vibration generated by the unmanned aerial vehicle in different flight states, and maximize the weakening of the transmission of the vibration to the flight control board, thereby ensuring the working stability of the flight control board. At the same time, the modular damping mechanism design is compact in structure, and is convenient for assembly and maintenance.

[0033] Further, the box body comprises a lower box body 311, a board seat 312, an upper box body 313 and a top cover 314 connected in sequence from top to bottom. The lower end surface of the lower box body 311 is connected with the box body 200 by the lower damping member 340, and the axis of the lower damping member 340 is vertically arranged, which can effectively absorb the vertical vibration. The side wall of the lower box body 311 is connected with the side support 320 by the side damping member 350, and the axis of the side damping member 350 is horizontally arranged, which can absorb the horizontal vibration. The upper damping members 360 are uniformly distributed around the top cover 314 and are respectively connected with the upper support 330. The axis of the upper damping member 360 is horizontally arranged, and the axes of the adjacent two upper damping members 360 are perpendicular, which can comprehensively absorb the horizontal longitudinal and other horizontal vibrations. The lower damping member 340, the upper damping member 360 and the side damping member 350 all adopt flight control damping bolts. By arranging the damping members in different directions, a two-stage three-dimensional damping effect of the flight control board is realized (a plurality of damping members are arranged between the box body and each support to form a multi-stage buffer), the damping coverage is wider, the damping effect is better, the complex vibration environment of the unmanned aerial vehicle can be adapted, the high requirements of the flight control board on stability and reliability are met, and the connection mode of each component is simple and reliable, which facilitates disassembly and replacement of the damping members.

[0034] In some embodiments, a program pouring port 3141 is arranged on the top cover 314. The program pouring port 3141 is arranged to realize program import and update of the flight control board without disassembling the top cover 314, which is convenient to operate and avoids component wear or sealing performance degradation caused by frequent disassembly of the top cover 314, thereby improving the maintenance efficiency and the service life of the equipment.

[0035] Further, the box 200 comprises six mutually connected upper, lower, left, right, front and back walls, and grids are machined on the upper, left, right and front walls to increase the surface area of the box 200 and better dissipate heat. The adjacent two walls are in concave-convex cooperation, and conductive rubber pads are arranged on the cooperation surfaces. The box wall is also provided with a grounding column 230. The concave-convex cooperation structure of the adjacent walls increases the sealing performance of the box 200 and reduces the generation of gaps. In cooperation with the conductive rubber pads, the box 200 can effectively block moisture and rain in the air from entering the box, play a good waterproof and moisture-proof role, ensure the dryness of the internal circuit, and reduce the influence of humidity on the circuit. At the same time, the conductive rubber pads cooperate with the conductive box 200 (preferably made of aluminum alloy), which can improve the electromagnetic shielding performance of the box 200. In combination with the design of the grounding column 230, the ground wires of the internal circuit modules of the flight control box can be converged at a common point and connected with the shell, and then connected with the fuselage through the grounding column 230 to form equipotential grounding, thereby avoiding electromagnetic induction of the ground wire loop and effectively reducing the interference of external electromagnetic signals on the circuit in the box. In addition, the concave-convex cooperation structure can also improve the structural strength of the box 200 and enhance the impact resistance of the box 200.

[0036] In order to quickly disassemble and assemble the flight control box, the bracket 100 is fixedly installed on the aircraft fuselage by the first-level damping bolt 400, so that the flight control box bracket 100 and the fuselage form an integral whole, and the flight control damping bolt realizes first-level damping.

[0037] During installation, the limiting hole 220 of the box 200 is aligned with the limiting pin 120120 of the bracket 100 and is inserted, so that the box 200 is positioned. At this time, the lock tongue 210 is aligned with the gap between the outer ring 1121 and the inner ring 1122 of the locking assembly 110. The lock shaft 111 is rotated to keep the angle of the lock shaft 111 inclined upward, so that the lock tongue 210 is inserted between the outer ring 1121 and the inner ring 1122. Then, the locking ring 112 is rotated, and the locking ring 112 is axially moved through threaded transmission, so that the inner wall of the outer ring 1121 and the upper surface of the lock tongue 210 abut, and the outer wall of the inner ring 1122 and the lower surface of the lock tongue 210 abut, thereby completing the preliminary locking of the box 200. Then, under the action of the compression spring 114, the stop ring 113 slides along the lock shaft 111 in the axial direction, so that the stop ring 113 is engaged with the saw-shaped teeth of the locking ring 112, thereby fixing the locking ring 112 in the circumferential direction and preventing it from loosening.

[0038] During disassembly, the stop ring 113 is axially pulled to separate the saw-shaped teeth, the locking ring 112 is rotated to loosen the clamping of the lock tongue 210, and then the lock shaft 111 is reversely rotated, so that the lock tongue 210 can be taken out from between the outer ring 1121 and the inner ring 1122. Finally, the box 200 is pulled out along the direction of the limiting pin 120120, and the disassembly is completed.

[0039] During the flight of the unmanned aerial vehicle, the lower damping piece 340, the side damping piece 350 and the upper damping piece 360 of the three-dimensional damping mechanism 300 absorb vibration from multiple dimensions, realize secondary damping, and effectively protect the flight control board; the concave-convex matching structure of the box body 200, the conductive rubber pad and the grounding column 230 cooperate to realize good waterproof, moisture-proof and anti-electromagnetic interference effects; the box body 200 is made of aluminum alloy material, the box wall is processed with a grid structure, and the internal components are arranged in a flat layout, thereby improving the heat dissipation efficiency; meanwhile, the box body 200 is designed in a split manner, the upper cover plate, the side plate and the rear plate can be separately disassembled, and combined with the filling port 3141 on the top cover 314, the maintenance convenience is greatly improved.

[0040] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0041] In addition, the terms "first", "second" are only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined with "first", "second" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "multiple" is at least two, such as two, three, etc., unless otherwise explicitly specified and limited.

[0042] In the present application, unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection", "fixing" and the like should be understood in a broad sense, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected or in communication with each other; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise explicitly limited. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0043] In this application, the terms "one embodiment", "some embodiments", "an example", "a specific example", or "some examples" mean that a particular feature, structure, material, or characteristic is included in at least one embodiment or example of the present application. The illustrative appearances of the above-mentioned terms in various places in the specification are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics can be combined in any suitable manner in one or more embodiments or examples. Moreover, the terms "first", "second", "third", etc. are used herein to describe various embodiments or examples and are not necessarily intended to denote a particular order, position, or priority of the elements being described. In addition, the terms "comprises", "comprising", "includes", "including", "has", "having", "contains", "containing", or any other similar word(s), are intended to be inclusive or open ended and not restrictive or exhaustive. In other words, the terms "comprises", "comprising", "includes", "including", "has", "having", "contains", "containing", or any other similar word(s), are intended to cover a special embodiment or example, but not exclude other embodiments or examples. In addition, the terms "an" and "one" are intended to be inclusive or open ended and not restrictive or exhaustive. In other words, the terms "an" and "one" are intended to cover both the singular aspect and the plural aspect, unless the context clearly indicates otherwise.

[0044] Although the embodiments of the present application have been shown and described above, it is understood that the above-described embodiments are exemplary, and are not to be interpreted as limiting the present application, and that the ordinary skilled person in the art can make changes, modifications, replacements, and variations to the above-described embodiments within the scope of the present application.

Claims

1. A UAV flight control box, characterized in that, The utility model relates to a kind of box and bracket, including: Bracket, one side of the bracket is provided with locking assembly; Box, the box is provided on the bracket, locking tongue is provided on the box, the box is installed on the bracket by inserting the locking assembly; Three-dimensional damping mechanism, the three-dimensional damping mechanism is provided in the inside of the box, for installing flight control board.

2. The UAV flight control box of claim 1, wherein, The locking assembly includes: Locking shaft, one end of the locking shaft is rotatably connected with the bracket, and the other end is a free end; Locking ring, the locking ring is sleeved on the locking shaft and is threadedly connected with the locking shaft, and the end surface of the locking ring is formed with an outer ring and an inner ring extending in the axial direction thereof, the locking shaft can make the end of the locking tongue inserted between the outer ring and the inner ring by rotating a preset angle, and the locking ring can make the upper surface of the locking tongue abut against the inner wall of the outer ring and the lower surface of the locking tongue abut against the outer wall of the inner ring by threadedly rotating around the locking shaft.

3. The UAV flight control box of claim 2, wherein, The locking tongue is in arc shape.

4. The UAV flight control box of claim 3, wherein, The locking assembly further includes a stop ring, the stop ring is sleeved on the locking shaft and is circumferentially limited with the locking shaft, and the end of the stop ring and the locking ring close to each other is respectively provided with a sawtooth, the stop ring is moved close to / distant from the locking ring along the axial direction of the locking shaft to make the sawtooth engage with each other / away from each other.

5. The UAV flight control box of claim 4, wherein, The locking assembly further includes a compression spring, the compression spring is sleeved on the locking shaft, one end of the compression spring abuts against the free end, and the other end of the compression spring abuts against the end surface of the stop ring.

6. The UAV flight control box according to any one of claims 1-5, wherein, The other side of the bracket is provided with a limiting pin, and the box is provided with a limiting hole opposite to the limiting pin.

7. The UAV flight control box according to any one of claims 1-5, wherein, The three-dimensional damping mechanism includes: Box body, the box body is installed on the inner bottom wall of the box by a lower damping member, and the box body is used for installing a flight control board; Side support, the side support is installed on the inner bottom wall of the box, and the side support and the side wall of the box body are connected by a side damping member; Upper support, the upper support is installed on the upper end of the side support, and the upper support and the upper end of the box body are connected by an upper damping member.

8. The UAV flight control box of claim 7, wherein, The box body includes a lower box body, a plate seat, an upper box body and a top cover connected in sequence from top to bottom, the lower end surface of the lower box body is connected with the box by a lower damping member, and the axis of the lower damping member is vertically arranged;The side wall of the lower box body is connected with the side support by a side damping member, and the axis of the side damping member is horizontally arranged;The upper damping members are uniformly distributed around the top cover and are respectively connected with the upper support, the axis of the upper damping member is horizontally arranged, and the axes of adjacent two upper damping members are perpendicular.

9. The UAV flight control box of claim 8, wherein, A filling port is formed in the top cover.

10. The UAV flight control box according to any one of claims 1-5, wherein, The box includes box walls connected with each other, the adjacent two box walls are concave-convex matched, and conductive rubber pads are arranged on the matching surfaces, and the box wall is further provided with a grounding column.

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