Multifunctional unmanned aerial vehicle body force bearing structure

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a multifunctional unmanned aerial vehicle body force bearing structure. The structure aims at optimizing the loading capacity and the flight efficiency of the unmanned aerial vehicle, and meanwhile the capacity of the unmanned aerial vehicle for adapting to different task requirements is improved. The fuselage is made of composite materials and fixedly connected with at least one force bearing structure square tube, the square tubes are made of thin-wall aluminum materials or carbon fiber composite materials, and therefore the weight is reduced, and the structural strength is improved. According to the design, a traditional weight-increasing multi-frame and stringer design is abandoned, a rivet fixing mode is adopted, and the structural rigidity and stability of the whole machine are remarkably improved. The rivet nuts are pre-installed on the upper surface of the force bearing structure, and various devices can be conveniently and rapidly expanded and installed according to requirements. Besides, due to the adoption of the standardized aluminum square tube, the purchasing and production processes are simplified, the system is suitable for various types of unmanned aerial vehicles, and the application performance in the fields of communication relay, aerial photography, resource exploration, military and the like is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and particularly to a load-bearing structure of a multi-functional unmanned aerial vehicle body. Background Art

[0002] The airframe structure of an unmanned aerial vehicle (UAV) is a crucial component in its design. It not only provides the physical framework of the UAV but also plays a key role in withstanding and distributing various forces encountered during flight. These forces include the weight of the UAV itself, the weight of the equipment carried, the dynamic loads during flight, and the external forces brought by environmental factors. In traditional UAV designs, to ensure the structural stability and reliability, multiple frame-truss structures are usually adopted to maintain the shape of the fuselage and fix various types of equipment.

[0003] However, this traditional design method has a series of problems and defects:

[0004] 1. Increased structural weight: To meet the requirements of strength and stiffness, traditional UAV designs have to add more frame-truss structures, which directly leads to an increase in the weight of the airframe structure. The additional weight reduces the payload capacity of the UAV because the maximum takeoff weight of the UAV is limited and must include the weight of the battery, sensors, and other mission-specific equipment.

[0005] 2. Impact on flight performance: As the weight of the airframe structure increases, the flight speed, agility, and endurance of the UAV will all be negatively affected. More importantly, the heavy body reduces the fuel efficiency or power utilization efficiency of the UAV, thus limiting its continuous operation ability in the air.

[0006] Increased production complexity: The design and manufacture of multiple frame-truss bars are more complex and require precise machining and assembly. This not only increases the production cost but also extends the production cycle. In addition, the complex structure also brings additional challenges in maintenance and repair.

[0007] 3. Limited flexibility: Once the design is fixed, the adaptability of the UAV to different mission loads and operating requirements will be limited. The heavier and more complex airframe structure reduces the adaptability of the UAV to new tasks. Cost-effectiveness reduction: The additional expenses for materials and production, combined with the complexity of operation and maintenance, result in a decline in overall cost-effectiveness. These factors may weaken the competitiveness of the UAV in the market, especially for those cost-sensitive application scenarios.

[0008] Therefore, while traditional UAV airframe designs ensure the required structural integrity and functionality, they clearly present numerous challenges that need to be addressed. These challenges are prompting the search for new design concepts and material applications, such as the use of lightweight, high-strength composite materials and the development of multifunctional integrated structural components, in order to create more efficient, lightweight, and highly adaptable UAV airframes. With the rapid advancement of electronic technology and materials, UAVs are finding widespread application in fields such as communication relay, aerial photography, resource exploration, and military operations. The UAV airframe structure serves as the backbone and load-bearing foundation of the drone. It not only secures and supports the other components of the drone, connecting the entire aircraft into a cohesive whole, but also withstands the loads transmitted from the connected components, the loads on the equipment within the airframe, the mission payload, and the aircraft's own gravity and inertia. Conventional UAVs employ multiple frames and stringers to maintain the airframe's shape and secure the equipment, which adds significant structural weight. This increased weight impacts the drone's flight speed and payload. Summary of the Invention

[0009] The present invention provides a multifunctional UAV body load-bearing structure to solve the problem, and the existing

[0010] The present application provides a multifunctional UAV body load-bearing structure, comprising:

[0011] A first load-bearing structure and a second load-bearing structure, wherein the first load-bearing structure and the second load-bearing structure are both composed of an equal number of load-bearing structure square tubes;

[0012] A limiting member, through which adjacent square tubes of the load-bearing structure are connected;

[0013] The first load-bearing structure and the second load-bearing structure are fixed on the fuselage of the UAV and are used to bear the load of the UAV.

[0014] A further improvement of the present application is that limiting holes are provided on the side walls at both ends of the load-bearing structure square tube for clamping the limiting member.

[0015] A further improvement of the present application is that the limiting member includes a limiting connecting plate, a limiting opening and closing arm, and a limiting hook. A through hole is provided in the middle of the limiting connecting plate, the limiting opening and closing arm passes through the through hole, and the center of the limiting opening and closing arm is limited within the through hole. The limiting hook is at the end of the limiting opening and closing arm and is used to pass through the limiting hole and limit to the square tube of the load-bearing structure.

[0016] A further improvement of the present application is that the limiting opening and closing arms include a first limiting opening and closing arm, a second limiting opening and closing arm, a third limiting opening and closing arm, and a fourth limiting opening and closing arm; wherein, the first limiting opening and closing arm and the third limiting opening and closing arm are integrally connected; the second limiting opening and closing arm and the fourth limiting opening and closing arm are integrally connected, and the first limiting opening and closing arm and the third limiting opening and closing arm are movably connected to the second limiting opening and closing arm and the fourth limiting opening and closing arm; the overall structure is in an X shape.

[0017] The beneficial effects of the present application are as follows:

[0018] 1. By combining the use of the load-bearing structure square tube and the limiting member, multiple load-bearing structure square tubes can be quickly spliced and disassembled according to requirements, facilitating transformation and upgrading.

[0019] 2. Force distribution: When multiple load-bearing mechanism square tubes are used in combination through the limiting member, the limiting connecting plate can support at the interfaces of two butt-jointed load-bearing structure square tubes, effectively preventing the inward deformation of the load-bearing structure square tube orifice and improving the overall stability.

[0020] 3. Installation convenience: The limiting member greatly simplifies the installation process. Without additional tools or complex alignment procedures, the rapid assembly and disassembly of the structure can be completed only through simple manual operations.

[0021] 4. Adaptability: Due to the unique X shape and adjustable opening and closing arm design of the limiting member, it can be applicable to load-bearing structure square tubes of different sizes and models, enhancing its applicability on various unmanned aerial vehicle platforms.

[0022] 5. Enhanced stability: The X-shaped structure of the limiting member provides good mechanical distribution, making the load-bearing more uniform and reducing structural fatigue or damage caused by uneven stress.

[0023] 6. Improved flight performance: By reducing the weight of the airframe and optimizing the load-bearing structure, the unmanned aerial vehicle exhibits better flight performance and endurance in various tasks. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings required for use in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0025] Figure 1 It is a schematic diagram of the installation of the load-bearing structure provided by the present invention;

[0026] Figure 2 It is a schematic diagram of the splicing of the load-bearing structure provided by the present invention;

[0027] Figure 3 It is a schematic structural diagram of the limiting member of the load-bearing structure provided by the present invention;

[0028] Reference numerals:

[0029] 1. Airframe body; 21. First load-bearing structure; 22. Second load-bearing structure; 3. Load-bearing structure square tube; 4. Limiting hole; 5. Rivet nut hole; 61. Limiting connecting plate; 62. Limiting hook; 631. First limiting opening and closing arm; 632. Second limiting opening and closing arm; 633. Third limiting opening and closing arm; 634. Fourth limiting opening and closing arm. Detailed implementation manners

[0030] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0031] To make the above objects, features, and advantages of the present application more obvious and understandable, the following will be combined with Figures 1 to 3 Describe a multi-functional unmanned aerial vehicle body load-bearing structure of the present invention.

[0032] A multi-functional unmanned aerial vehicle body load-bearing structure includes: a first load-bearing structure 21 and a second load-bearing structure 22, wherein both the first load-bearing structure 21 and the second load-bearing structure 22 are composed of the same number of load-bearing structure square tubes 3;

[0033] Limiting member, adjacent load-bearing structure square tubes 3 are connected by the limiting member;

[0034] The first load-bearing structure 21 and the second load-bearing structure 22 are fixed on the airframe body 1 of the unmanned aerial vehicle and are used to bear the load of the unmanned aerial vehicle.

[0035] In the solution of the present application, limiting holes 4 are provided on the side walls at both ends of the load-bearing structure square tube 3 for clamping the limiting member.

[0036] The limiting member includes a limiting connecting plate 61, a limiting opening and closing arm, and a limiting hook 62. A through hole is provided in the middle of the limiting connecting plate 61. The limiting opening and closing arm passes through the through hole, and the center of the limiting opening and closing arm is restricted within the through hole. The limiting hook 62 is at the end of the limiting opening and closing arm and is used to pass through the limiting hole and be restricted on the load-bearing structure square tube 3.

[0037] The limiting expansion and contraction arms consist of four main parts: a first limiting expansion and contraction arm 631, a second limiting expansion and contraction arm 632, a third limiting expansion and contraction arm 633, and a fourth limiting expansion and contraction arm 634. These expansion and contraction arms are paired to form two groups (the first limiting expansion and contraction arm 631 and the third limiting expansion and contraction arm 633 form one group, and the second limiting expansion and contraction arm 632 and the fourth limiting expansion and contraction arm 634 form another group), and the two expansion and contraction arms in each group are fixed together through an integrated connection.

[0038] The two sets of expansion and contraction arms are connected by a movable joint, forming a flexible X-shaped structure. This structural design allows the expansion and contraction arms to move relative to each other when subjected to force, thereby changing the shape and tension of the overall structure.

[0039] When the operator pinches the first and fourth limiting arms 631, 634 inward relative to each other, the X-shaped structure's linkage effect causes the second and third limiting arms 632, 633 to open outward. Similarly, when the second and third limiting arms 632, 633 are pinched inward relative to each other, the first and fourth limiting arms 631, 634 open outward. This opposing movement provides a simple mechanical locking mechanism, allowing the entire structure to be quickly and securely installed on the load-bearing square tube 3.

[0040] This design greatly simplifies the installation process, requiring no additional tools or complicated alignment procedures, and the structure can be quickly assembled and disassembled with simple manual operations.

[0041] In summary, this limited expansion and contraction arm with a unique X-shaped structure not only ensures the simplicity and safety of connection, but also improves the practicality and flexibility of the UAV's load-bearing structure, making it more adaptable to changing application scenarios and needs.

[0042] It is worth noting that the load-bearing structure can replace the trusses inside the conventional fuselage to reduce the internal structure of the fuselage. The load-bearing structure square tube 3 can be made of standard conventional aluminum square tube or thin-walled composite carbon fiber square tube, which does not require special processing and production and is easy to purchase and use.

[0043] The load-bearing square tube 3 is connected to the fuselage 1 by adhesive bonding and rivets, facilitating installation and eliminating interference with mold assembly during fuselage production. Rivet nut holes 5 are provided on the upper surface of the load-bearing square tube, allowing for secure installation to the fuselage, allowing for later expansion and installation of various equipment panels, making it even more convenient to use.

[0044] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A multi-functional drone airframe load-bearing structure, characterized in that, Comprising: A first load-bearing structure and a second load-bearing structure, wherein both the first load-bearing structure and the second load-bearing structure are composed of the same number of load-bearing structure square tubes; A limiting member, and adjacent load-bearing structure square tubes are connected by the limiting member; The first load-bearing structure and the second load-bearing structure are fixed on the fuselage of the unmanned aerial vehicle for carrying the load of the unmanned aerial vehicle.

2. The multi-functional UAV airframe load-bearing structure according to claim 1, characterized in that Limiting holes are provided on the side walls at both ends of the load-bearing structure square tube for clamping the limiting member.

3. The multi-functional UAV airframe load-bearing structure according to claim 2, wherein, The limiting member includes a limiting connecting plate, a limiting opening and closing arm, and a limiting hook. A through hole is provided in the middle of the limiting connecting plate. The limiting opening and closing arm passes through the through hole, and the center of the limiting opening and closing arm is restricted within the through hole. The limiting hook is at the end of the limiting opening and closing arm for passing through the limiting hole and being restricted on the load-bearing structure square tube.

4. A multi-functional UAV airframe load-bearing structure according to claim 3, characterized in that, The limiting opening and closing arm includes a first limiting opening and closing arm, a second limiting opening and closing arm, a third limiting opening and closing arm, and a fourth limiting opening and closing arm; wherein, the first limiting opening and closing arm and the third limiting opening and closing arm are integrally connected; the second limiting opening and closing arm and the fourth limiting opening and closing arm are integrally connected, and the first limiting opening and closing arm and the third limiting opening and closing arm are movably connected to the second limiting opening and closing arm and the fourth limiting opening and closing arm together; the whole is in an X-shaped structure.

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