Unmanned aerial vehicle hatch cover and unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle hatch cover and an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle hatch cover comprises a framework and light filling pieces embedded in the framework, the framework comprises a frame and a plurality of connecting rods arranged in the frame, the connecting rods divide the frame into a plurality of filling grooves, and the light filling pieces are embedded in the filling grooves. The cabin cover weight of the unmanned aerial vehicle can be reduced, and the overall performance of the unmanned aerial vehicle is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle cabin cover and unmanned aerial vehicle. BACKGROUND

[0002] As a kind of efficient, flexible aircraft, fixed-wing unmanned aerial vehicle is widely used in disaster monitoring, agricultural plant protection and other fields.In the design of unmanned aerial vehicle, weight management is one of the key factors determining its performance.

[0003] As one of the main structural components of unmanned aerial vehicle, the weight of fuselage shell has a profound impact on the overall performance of unmanned aerial vehicle.The traditional unmanned aerial vehicle hatch plate is made of metal material (such as aluminum alloy), which can meet the requirements of structural strength, but has obvious shortcomings in weight control. CONTENT OF THE UTILITY MODEL

[0004] The purpose of the present application is to provide an unmanned aerial vehicle cabin cover and unmanned aerial vehicle, which can reduce the weight of unmanned aerial vehicle cabin cover and improve the overall performance of unmanned aerial vehicle.

[0005] The embodiment of the present application is realized as follows:

[0006] In one aspect of the embodiment of the present application, an unmanned aerial vehicle cabin cover is provided, comprising a skeleton and a lightweight filler embedded in the skeleton, the skeleton comprising a frame and a plurality of connecting rods arranged in the frame, the connecting rods separating the frame into a plurality of filling grooves, and the lightweight filler being embedded in the filling grooves.

[0007] Optionally, as one of the implementable ways, the connecting rod comprises a first connecting rod and a second connecting rod arranged in cross, and the two ends of the first connecting rod and the two ends of the second connecting rod are connected to the frame respectively.

[0008] Optionally, as one of the implementable ways, the skeleton and the lightweight filler are connected to form a main plate of unmanned aerial vehicle cabin cover, and the first fiber cloth and the second fiber cloth are laid on both sides of the main plate respectively.

[0009] Optionally, as one of the implementable ways, the main plate is bonded to the first fiber cloth and the second fiber cloth on both sides respectively.

[0010] Optionally, as one of the implementable ways, the lightweight filler and the joint of the filling groove are bonded.

[0011] Optionally, as one of the implementable ways, the lightweight filler comprises at least one of balsa wood, polyvinyl chloride foam and polymethacrylimide foam.

[0012] Optionally, as an implementable mode, the framework is provided with a plurality of mounting holes, and the mounting holes are connected with the fuselage.

[0013] Optionally, as an implementable mode, the first fiber cloth is provided with a first through hole corresponding to the mounting hole.

[0014] Optionally, as an implementable mode, the second fiber cloth is provided with a second through hole corresponding to the mounting hole.

[0015] Another aspect of the embodiment of the present application provides a UAV, comprising a fuselage and the UAV hatch cover as any one of the above.

[0016] The beneficial effects of the embodiment of the present application include:

[0017] The UAV hatch cover and the UAV provided by the present application comprise a framework and a light filling piece embedded in the framework. The framework comprises a frame and a plurality of connecting rods arranged in the frame. The connecting rods separate the frame into a plurality of filling grooves, and the light filling piece is embedded in the filling grooves. By combining the light filling piece and the framework, the overall weight of the hatch cover is significantly reduced, meeting the requirement of the UAV for light weight. The design of the frame and the connecting rods of the framework enhances the overall rigidity and anti-deformation capability of the hatch cover, which can effectively resist various mechanical loads in flight. BRIEF DESCRIPTION OF DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiments. It should be understood that the following drawings only show some embodiments of the present application, and therefore should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can also be obtained without creative labor on the basis of these drawings.

[0019] Figure 1 The structural schematic diagram of the UAV hatch cover provided by the embodiment of the present application is shown in the figure.

[0020] Figure 2 The structural schematic diagram of the UAV hatch cover main plate in the UAV hatch cover provided by the embodiment of the present application is shown in the figure.

[0021] Figure 3 The structural schematic diagram of the framework in the UAV hatch cover provided by the embodiment of the present application is shown in the figure.

[0022] Icon: 100 - UAV hatch; 110 - UAV hatch main plate; 111 - skeleton; 1111 - frame; 1112 - connecting rod; 1112a - first connecting rod; 1112b - second connecting rod; 1113 - filling slot; 1114 - mounting hole; 112 - lightweight filler; 120 - first fiber cloth; 121 - first through hole; 130 - second fiber cloth; 131 - second through hole. DETAILED DESCRIPTION

[0023] To make the objectives, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some but not all of the embodiments of the present application. The components of the embodiments of the present application described and shown in the drawings herein can be arranged and designed in various different configurations.

[0024] Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the claimed present application, but only represents selected embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative labor are within the scope of protection of the present application.

[0025] It should be noted that: similar reference numerals and letters represent similar items in the following drawings, therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings. In addition, the terms "first", "second", "third" and the like are only used to distinguish description, and cannot be understood as indicating or implying relative importance.

[0026] In the description of the present application, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set", "mount", "connected", "connected" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be the communication inside two elements. For those of ordinary skill in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0027] Please refer to Figure 1 , Figure 2 and Figure 3 , the present embodiment provides a UAV hatch 100, comprising a skeleton 111 and a lightweight filler 112 embedded in the skeleton 111, the skeleton 111 comprises a frame 1111 and a plurality of connecting rods 1112 arranged in the frame, the connecting rods 1112 separate the frame into a plurality of filling slots 1113, and the lightweight filler 112 is embedded in the filling slot 1113.

[0028] Specifically, the unmanned aerial vehicle cabin cover 100 of the present application comprises a framework 111 and a lightweight filler 112 embedded in the framework 111. The framework 111 comprises a frame 1111 and a plurality of connecting rods 1112 arranged in the frame, the connecting rods 1112 divide the frame into a plurality of filling grooves 1113, and the lightweight filler 112 is embedded in the filling grooves 1113. Through the careful design of the framework 111 structure, the connecting rods 1112 are reasonably divided into a plurality of filling areas, and the lightweight filler 112 is embedded, which not only guarantees the structural stability of the cabin cover as a whole, but also greatly reduces the weight. The framework 111 is made of high-strength and low-density materials, such as carbon fiber composite materials, which have excellent tensile and compressive properties and can withstand various stresses in flight. The lightweight filler 112 can be made of foam materials or honeycomb composite materials, which not only have light weight, but also have certain auxiliary functions such as buffering and heat insulation.

[0029] Compared with the traditional aluminum alloy cabin cover, the unmanned aerial vehicle cabin cover 100 of the present application effectively reduces its own weight by using lightweight materials. This optimizes the weight of the unmanned aerial vehicle, directly improves the endurance of the unmanned aerial vehicle, and can extend the flight time and expand the operation range under the same energy reserve. It has great advantages whether in large-area agricultural plant protection tasks or in long-time disaster monitoring scenarios. The lighter unmanned aerial vehicle cabin cover 100 makes the unmanned aerial vehicle more agile during flight, and when facing complex and variable flight environments, it can quickly respond to instructions and accurately complete actions, greatly improving the control performance of the unmanned aerial vehicle and reducing the risk of flight accidents. Due to the reduction in weight, the gravitational potential energy that needs to be overcome during flight is reduced, thereby reducing energy consumption. This means that not only the energy cost of a single flight is reduced during long-term use, but also the frequency of frequent charging or replacing batteries is reduced, improving the use efficiency of the unmanned aerial vehicle and saving a lot of operating costs for users. The unique combination structure of the framework 111 and the filler does not sacrifice the structural strength in pursuit of lightweight. The reasonable design of the framework 111 and the use of high-strength materials ensure that the cabin cover can remain intact under conditions such as vibration, airflow impact, and slight collision during flight, effectively protecting the internal components of the unmanned aerial vehicle and prolonging the service life of the unmanned aerial vehicle. The frame 1111 can be rectangular, circular, etc.

[0030] The unmanned aerial vehicle hatch 100 provided in the application comprises a framework 111 and a light filling piece 112 embedded in the framework 111, the framework 111 comprises a frame 1111 and a plurality of connecting rods 1112 arranged in the frame, the connecting rods 1112 separate the frame into a plurality of filling grooves 1113, and the light filling piece 112 is embedded in the filling grooves 1113. By combining the light filling piece 112 and the framework 111, the overall weight of the hatch is significantly reduced, meeting the light weight requirement of the unmanned aerial vehicle. The design of the frame 1111 and the connecting rods 1112 of the framework 111 enhances the overall rigidity and anti-deformation ability of the hatch, which can effectively resist various mechanical loads in flight.

[0031] In an embodiment of the application, as shown in Figure 1 、 Figure 2 and Figure 3 , the connecting rod 1112 comprises a first connecting rod 1112a and a second connecting rod 1112b arranged in cross, and the two ends of the first connecting rod 1112a and the two ends of the second connecting rod 1112b are connected to the frame.

[0032] Specifically, the cross arrangement of the first connecting rod 1112a and the second connecting rod 1112b makes the force conduction path multi-dimensional, when encountering external forces such as airflow impact and vibration in flight, the force is quickly dispersed along the connecting rods 1112 in different directions to the frame everywhere, avoiding stress concentration, greatly enhancing the overall rigidity of the hatch, and ensuring flight safety.

[0033] In an embodiment of the application, as shown in Figure 1 、 Figure 2 and Figure 3 , the framework 111 and the light filling piece 112 are connected to form an unmanned aerial vehicle hatch main plate 110, and the first fiber cloth 120 and the second fiber cloth 130 are arranged on both sides of the unmanned aerial vehicle hatch main plate 110.

[0034] The first fiber cloth 120 and the second fiber cloth 130 can resist external wear, scratches and a certain degree of impact, resist "small bumps" in daily flight, and prolong the service life of the hatch main plate.

[0035] The adhesion of the first fiber cloth 120 and the second fiber cloth 130 can further bind the internal structure and improve the overall structural strength; and the fine texture thereof helps to optimize the airflow on the surface of the hatch, reduce the flight resistance, and make the unmanned aerial vehicle fly more smoothly.

[0036] In an embodiment of the application, as shown in Figure 1 、 Figure 2 and Figure 3 , the main plate is adhered to the first fiber cloth 120 and the second fiber cloth 130 on both sides.

[0037] Specifically, the bonding process eliminates interlayer displacement, making the fiber cloth and the main plate an inseparable whole. No matter how bumpy or vibrational the environment is, the layers of the structure will always bear force synchronously. The close bonding ensures efficient force transmission between different layers. When a local force is applied, it can quickly spread to the entire canopy, avoiding the risk of local damage caused by stress concentration.

[0038] In an embodiment of the present application, as shown in Figure 1 、 Figure 2 and Figure 3 , the lightweight filler 112 and the filler groove 1113 are bonded at the joint.

[0039] Specifically, the bonding makes the lightweight filler 112 and the filler groove 1113 an integral whole, preventing displacement and falling of the filler due to vibration during flight, ensuring that the internal structure of the canopy remains stable and the mechanical properties remain stable. Close bonding reduces gaps, effectively buffers vibration and absorbs noise, creating a relatively quiet and stable operating environment for the UAV and improving flight comfort and component stability.

[0040] In an embodiment of the present application, as shown in Figure 1 、 Figure 2 and Figure 3 , the lightweight filler 112 includes at least one of balsa wood, polyvinyl chloride foam, and polymethacrylimide foam.

[0041] Specifically, different lightweight materials have different characteristics. Balsa wood has both strength and lightness, making it suitable for scenarios that are sensitive to cost and have moderate strength requirements. Polyvinyl chloride foam has good flexibility and thermal insulation, providing thermal protection for canopies with more electronic components. Polymethacrylimide foam has excellent compression resistance and thermal insulation, making it suitable for high-demand flight missions and meeting the customization needs of different UAVs. These materials have a density much lower than traditional metals, greatly reducing the weight of the canopy and improving the performance of the UAV.

[0042] In an embodiment of the present application, as shown in Figure 1 、 Figure 2 and Figure 3 , the framework 111 is provided with a plurality of mounting holes 1114, which are connected to the fuselage through the mounting holes 1114.

[0043] Further, the first fiber cloth 120 is provided with a first through hole 121 corresponding to the mounting hole 1114.

[0044] Further, the second fiber cloth 130 is provided with a second through hole 131 corresponding to the mounting hole 1114.

[0045] The first fiber cloth 120 is provided with a first through hole 121 corresponding to the mounting hole 1114, avoiding the fiber cloth from shielding the mounting hole 1114, ensuring the connector to pass through smoothly, realizing seamless assembly of the cabin cover and the fuselage, and improving the installation efficiency.

[0046] The second fiber cloth 130 is provided with a second through hole 131 corresponding to the mounting hole 1114, and cooperates with the first fiber cloth 120 to ensure smooth installation. The bilateral through hole design is symmetrical and corresponding, removes obstacles from two directions, ensures the connector to pass through vertically and stably, and strengthens the stability and accuracy of the connection between the cabin cover and the fuselage.

[0047] The embodiment of the present application further discloses a UAV, which comprises a fuselage and the UAV cabin cover 100 in the foregoing embodiment. The UAV comprises the same structure and beneficial effects as the UAV cabin cover 100 in the foregoing embodiment. The structure and beneficial effects of the UAV cabin cover 100 have been described in detail in the foregoing embodiment, and will not be described here again.

[0048] The above only describes the preferred embodiments of the present application and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An unmanned hatch cover, characterized in that, The skeleton comprises a frame and a plurality of connecting rods arranged in the frame, the connecting rods separate the frame into a plurality of filling slots, and the lightweight filler is arranged in the filling slots.

2. The drone pod door of claim 1, wherein, The connecting rods comprise first connecting rods and second connecting rods arranged in cross, and the two ends of the first connecting rods and the two ends of the second connecting rods are connected to the frame.

3. The drone pod door of claim 1, wherein, The skeleton and the lightweight filler are connected to form a UAV hatch main plate, and the two sides of the UAV hatch main plate are respectively paved with a first fiber cloth and a second fiber cloth.

4. The drone pod door of claim 3, wherein, The two sides of the main plate are respectively bonded with the first fiber cloth and the second fiber cloth.

5. The drone pod door of claim 1, wherein, The lightweight filler and the joints of the filling slots are bonded.

6. The drone pod door of claim 1, wherein, The lightweight filler comprises at least one of balsa wood, polyvinyl chloride foam and polymethacrylimide foam.

7. The drone pod door of claim 4, wherein, A plurality of mounting holes are arranged on the skeleton, and the mounting holes are connected to the fuselage.

8. The drone pod door of claim 7, wherein, A first through hole corresponding to the mounting hole is arranged on the first fiber cloth.

9. The drone pod door of claim 7, wherein, A second through hole corresponding to the mounting hole is arranged on the second fiber cloth.

10. A drone, characterized in that, The UAV hatch comprises a fuselage and the UAV hatch of any one of claims 1-9.

Images