Force-bearing bulkhead for fuselage of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle body force-bearing bulkhead. The overall structure comprises nacelles, a force-bearing bulkhead body and screws. The bearing bulkhead is of a C-shaped section structure, adopts a machining part or a forge piece and is a composite material part in the structural form; a connector machining part is arranged in the C-shaped frame of the force-bearing bulkhead, a threaded positioning hole is formed in the C-shaped frame, and the C-shaped frame is connected with the nacelle through a screw; the bearing bulkhead comprises a front main bearing frame and a rear main bearing frame, and lightening holes are formed in web faces of the front main bearing frame and the rear main bearing frame, so that the overall weight is reduced. On the one hand, the structural form is simple, and good rigidity and strength are achieved; compared with a machined part or a forged part, the composite material part has the advantages that the overall weight can be reduced, the production and manufacturing period is short, the cost is low, and the forming process is simple; on the other hand, the lightening holes are formed, so that the load capacity of the load cabin is increased; the C-shaped frame connector is connected with the nacelle end through a positioning screw, so that the fuselage and the nacelle end are firmly connected together, and force is guided to the force bearing frame from the nacelle.

Description

Technical Field

[0001] The present application relates to the field of UAV structural design, and in particular to a load-bearing bulkhead of a UAV fuselage. Background Art

[0002] With the widespread application of drones in various fields, the requirements for drone performance are also increasing. Drones are mainly composed of airframe structure, power system, flight control system, and avionics system. The airframe structure is an important part of drones. In the airframe structure, the load-bearing structure is mainly used to bear various loads during the flight of the drone. The performance of the load-bearing structure directly affects the flight safety of the drone.

[0003] The existing UAV body structure generally adopts traditional structural design methods, such as "I"-shaped profile structure or box-shaped structure. However, these structural designs often have problems, such as easy damage when overloaded, insufficient rigidity, and the weight of the nacelle is also too large. Therefore, in order to ensure that the UAV has the ability to resist damage in various working conditions, there is no structural damage caused by overload; to ensure that the UAV has high rigidity, maintains flight stability under extreme working conditions, has strong ability to resist deformation, and does not cause permanent deformation or plastic deformation; and to reduce the weight of the body while considering processing and production costs. Designing a body structure with higher strength, rigidity and load capacity is an urgent problem to be solved.

[0004] Therefore, innovative structural design solutions are needed to solve these problems. One solution is to adopt a "C" profile structure and use lightweight composite materials to manufacture the main load-bearing frame of the nacelle, and set reinforcing ribs inside the frame to enhance rigidity and stability and reduce weight. In addition, opening lightening holes on the web of the frame can increase the volume of the load compartment while reducing the weight of the nacelle. This new nacelle structural design can significantly improve the drone's ability to resist damage, enhance rigidity and stability, and reduce weight, thereby improving the flight safety and performance of the drone. Summary of the invention

[0005] The present invention provides a load-bearing bulkhead frame for a fuselage of an unmanned aerial vehicle, which solves the problems of heavy fuselage weight and insufficient stability by designing a novel load-bearing bulkhead frame structure.

[0006] To achieve the above objectives, this application provides the following solutions:

[0007] A load-bearing bulkhead of an unmanned aerial vehicle fuselage, the overall structure of which includes a nacelle, a load-bearing bulkhead, and screws; the load-bearing bulkhead is installed at the lower part of the nacelle, and the load-bearing bulkhead is connected to the nacelle to jointly bear the weight of the unmanned aerial vehicle.

[0008] Furthermore, the load-bearing bulkhead is a "C"-shaped cross-section structure, using machined parts or forgings, and the structural form is a composite material part.

[0009] Furthermore, a joint machined part is arranged in the "C"-shaped frame of the load-bearing bulkhead, and is provided with a threaded positioning hole, which is connected to the nacelle through the screws.

[0010] Furthermore, the load-bearing bulkhead frame includes a front main load-bearing frame and a rear main load-bearing frame, which are riveted together with the skin on the UAV fuselage to form a "box" shape as a whole.

[0011] Furthermore, lightening holes are provided on the web surfaces of the front main bearing frame and the rear main bearing frame to reduce the overall weight.

[0012] Beneficial effects of the technical solution of this application:

[0013] In the prior art, the main load-bearing bulkhead structure of the UAV fuselage generally adopts an "I"-shaped profile structure. The present application adopts a "C"-shaped profile structure. Compared with the "I"-shaped profile structure, the structure is simple and has better rigidity and strength.

[0014] The composite parts used in this application can reduce the overall weight by about 30% compared to machined parts or forged parts, and have a short production cycle, low cost and simple molding process.

[0015] The web surface of the "C"-shaped frame of the present application is provided with lightening holes, thereby increasing the load capacity of the load compartment.

[0016] The "C"-shaped frame joint of the present application is connected to the nacelle end using positioning screws, so that the fuselage and the nacelle are firmly connected together, and the force is guided from the nacelle to the load-bearing frame. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative labor.

[0018] Figure 1 It is a schematic diagram of the overall installation structure of the load-bearing bulkhead of a UAV fuselage;

[0019] Figure 2 It is a structural schematic diagram of a load-bearing bulkhead of a UAV fuselage;

[0020] Reference numerals:

[0021] 10. Nacelle; 20. Load-bearing bulkhead; 30. Screws; 21. Front main load-bearing frame; 22. Rear main load-bearing frame; 23. Lightening holes. DETAILED DESCRIPTION

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

[0023] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the present application is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0024] like Figure 1 to Figure 2 As shown, a load-bearing bulkhead of a UAV fuselage has an overall structure including a nacelle 10, a load-bearing bulkhead 20, and screws 30; the load-bearing bulkhead 20 is installed at the lower part of the nacelle 10, and the load-bearing bulkhead 20 is connected to the nacelle to jointly bear the weight of the UAV.

[0025] A further improvement is that the load-bearing bulkhead 20 is a "C"-shaped cross-section structure, using machined parts or forgings, and the structural form is a composite material part.

[0026] A further improvement is that a joint machined part is arranged in the "C"-shaped frame of the load-bearing bulkhead 20, and a threaded positioning hole is opened, which is connected to the nacelle 10 by screws 30.

[0027] A further improvement is that the load-bearing bulkhead 20 includes a front main load-bearing frame 21 and a rear main load-bearing frame 22, which are riveted together with the skin on the UAV fuselage to form a "box" shape as a whole, thereby maintaining the shape of the aircraft, supporting the skin, and improving the stability of the skin, so as to facilitate the UAV to withstand local aerodynamic loads.

[0028] A further improvement is that lightening holes 23 are provided on the web surfaces of the front main bearing frame 21 and the rear main bearing frame 22. The lightening holes 23 are evenly distributed on the web surfaces of the front main bearing frame 21 and the rear main bearing frame 22, thereby reducing the overall weight while bearing a certain in-plane shear force and normal stress.

[0029] It is worth noting that this embodiment only shows a structural layout of a UAV fuselage load-bearing bulkhead, but it does not mean that the UAV fuselage load-bearing bulkhead provided in this application has only this one form, and the specific structural form can be adjusted according to the specific UAV structure.

[0030] In the description of the present application, it should be understood that the terms "front", "back", "up", "down", "outside", "inside", "horizontal", "top", "bottom", "surface", "bottom layer", "top layer", "upper", "lower", "bottom", "top", "inside", "surface", "center", "right", "middle" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0031] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "connected", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be the internal connection of two elements. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0032] The embodiments described above are only descriptions of the preferred methods of the present application, and are not intended to limit the scope of the present application. Without departing from the design spirit of the present application, various modifications and improvements made to the technical solutions of the present application by those skilled in the art should all fall within the scope of protection determined by the claims of the present application.

Claims

1. A load-bearing bulkhead for an unmanned aerial vehicle fuselage, characterized in that: The overall structure includes a nacelle, a load-bearing bulkhead, and screws; the load-bearing bulkhead is a "C"-shaped profile structure, and the structural form is a composite material part, which is installed at the bottom of the nacelle. The load-bearing bulkhead is connected to the nacelle to jointly bear the weight of the UAV.

2. The UAV fuselage load-bearing bulkhead according to claim 1, characterized in that: A joint machined part is arranged in the "C"-shaped frame of the load-bearing bulkhead and is provided with a threaded positioning hole, and is connected to the nacelle through the screws.

3. The UAV fuselage load-bearing bulkhead according to claim 2, characterized in that: The load-bearing bulkhead frame includes a front main load-bearing frame and a rear main load-bearing frame, which are riveted together with the skin on the UAV fuselage to form a "box" shape as a whole.

4. The UAV fuselage load-bearing bulkhead according to claim 3, characterized in that: Lightening holes are provided on the web surfaces of the front main bearing frame and the rear main bearing frame to reduce the overall weight.

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