An unmanned aircraft cabin section of a truss-like structure
The UAV cabin section, designed with a truss-like structure, achieves modular splicing, lightweight and high-strength cabin structure, solving the shortcomings of existing UAV cabins in terms of assembly, maintenance and functional expansion, and improving the stability and heat dissipation performance of the cabin.
Patent Information
- Application Number
- CN202522105357.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-29
- Publication Date
- 2026-08-25
- Estimated Expiration
- 2035-09-29
AI Technical Summary
Existing UAV cabin structures are inadequate in terms of modular assembly, lightweight design, ease of maintenance, and functional expansion, making it difficult to meet the equipment layout requirements of different mission payloads. Furthermore, their heat dissipation and electromagnetic compatibility designs are insufficient.
The design adopts a truss-like structure, and achieves lightweight and high strength of the compartment by modularly splicing the cabin frame and wall panel components, combined with sliding plug-in and threaded fixing, and setting reinforcing ribs and fixing holes. At the same time, heat dissipation holes and mounting holes are opened on the wall panels to improve functional integration.
It improves the modular assembly convenience and maintenance efficiency of the UAV cabin, enhances structural stability and heat dissipation capacity, meets the equipment layout requirements of different mission payloads, and improves the overall load-bearing capacity and service life of the cabin.
Smart Images
Figure CN224676430U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) structural design, and in particular to a UAV cabin section with a truss-beam structure. Background Technology
[0002] As one of the fastest-growing aircraft in recent years, drones have been widely used in aerospace, logistics and transportation, disaster relief, environmental monitoring and national defense. With the continuous expansion of application scenarios, the types and complexity of drone mission payloads are constantly increasing, which puts forward higher requirements for drone airframe structures. They not only need to have strong load-bearing capacity and structural rigidity, but also need to take into account lightweighting and modularization to improve endurance and maintenance efficiency.
[0003] Existing UAV cabin structures typically employ integral molding or modular panel structures. Integral molding cabins are generally manufactured through integral molding or welding processes, possessing high strength and uniform stress performance. However, they are structurally heavy, have high processing costs, and often require extensive repairs or even complete replacement when local damage occurs, making maintenance difficult. Traditional truss-type cabin sections use circular bulkhead beams and long trusses as the cabin skeleton, with the skin fixed and connected by fasteners such as rivets, isolating the enclosed space from the outside world to form a cylindrical cabin. These sections often combine steel, alloys, or composite materials, offering advantages in high strength and durability, structural stability, and high reliability, but are not easy to install and disassemble.
[0004] In the actual use of drones, the cabin design still faces many challenges. First, there is a lack of modularity and maintainability. Traditional cabins lack flexible disassembly and replacement methods. Once a part is damaged, it often requires the entire cabin to be replaced or extensively disassembled, resulting in high maintenance costs and time. Second, the internal space for equipment installation and the number of interfaces are limited, making it difficult to meet the flexible equipment layout requirements of different mission payloads. Furthermore, as the number of electronic devices carried by drones continues to increase, the design requirements for heat dissipation, ventilation, and electromagnetic compatibility of the cabin are also becoming more stringent. If the structure fails to properly consider these issues, it can easily lead to overheating or interference of internal equipment, thereby affecting the stable operation of the system.
[0005] To address the aforementioned issues, some researchers have attempted to incorporate truss structure concepts into UAV cabin design. Truss-style design, by arranging the cabin frame and wall panels in a truss-like manner, allows the cabin to maintain lightweight while achieving higher specific strength and overall stiffness. It also allows for the formation of regular channels or openings internally, facilitating both equipment installation and heat dissipation. However, the application of this type of structure in small UAV cabins is limited, and existing designs still have shortcomings in terms of assembly methods, lightweighting, and functional integration.
[0006] Therefore, how to design a drone cabin structure that combines modularity, lightweight design, structural stability, and functional expandability has become a technical problem that urgently needs to be solved in this field. Utility Model Content
[0007] To address the shortcomings of the existing technology, this utility model provides a truss-like structure for unmanned aerial vehicle (UAV) cabin sections, aiming to solve the problems existing in the prior art in terms of modular assembly, strength and weight balance, maintenance convenience, and functional expansion.
[0008] To achieve the above objectives, the technical solution adopted by this utility model is: a truss-like structure unmanned aerial vehicle (UAV) segment, including an upper segment comprising a first frame, a second frame, and a wall panel a assembly connected between the first frame and the second frame; and a lower segment comprising a third frame, a fourth frame, and a wall panel b assembly connected between the third frame and the fourth frame, wherein the third frame is slidably inserted into the second frame and fixedly connected by a pin.
[0009] Based on the above structural design, the beneficial effects of this utility model are as follows: by setting cabin frames and wall panel components in the upper and lower cabin sections respectively, the cabin structure is arranged in a truss-like manner, which can effectively improve the strength and rigidity of the overall cabin; by sliding and inserting the third cabin frame with the second cabin frame and fixing it with threaded screws, modular splicing of the cabin sections is realized, making assembly and disassembly more convenient and significantly improving maintenance and replacement efficiency.
[0010] Furthermore, the inner walls of the first compartment frame, the second compartment frame, the third compartment frame, and the fourth compartment frame are provided with a plurality of reinforcing ribs, and each reinforcing rib has a wall panel fixing hole in the middle.
[0011] Based on the above, by arranging reinforcing blocks and setting wall panel fixing holes at key stress points of the cabin frame, it is not only convenient to quickly position and install the wall panels, but also to form additional structural reinforcement in local areas, making the connection between the cabin frame and the wall panels more stable and reliable, avoiding cabin deformation or loosening caused by insufficient local connection strength, thereby further improving the overall load-bearing capacity and structural stability of the cabin.
[0012] Furthermore, the first cabin frame is integrally formed by four long sides of the same length and four short sides of the same length spaced apart in sequence, and the top surface of the first cabin frame is provided with a plurality of first internal support fixing holes, which are respectively opened at the middle position of each long side.
[0013] Based on the above, the regular frame structure formed by the alternating distribution of long and short sides gives the first cabin frame symmetrical and balanced stress characteristics, enabling it to maintain structural stability under flight loads. At the same time, the first internal support fixing hole is arranged in the middle of the long side, allowing the internal support to be directly installed in the position where the cabin is most stressed. This not only ensures the reliable fixing of the support components to the cabin, but also helps to distribute the load and reduce local stress concentration, thereby further improving the overall strength and service life of the cabin section.
[0014] Furthermore, the second cabin frame is integrally formed by four long sides of the same length and four short sides of the same length spaced apart in sequence. The side of the second cabin frame is provided with a plurality of inter-frame fixing holes, which are respectively opened at both ends of each long side. The inner side of the second cabin frame is provided with a plurality of second inner support fixing holes, which are respectively opened at both ends of two opposite long sides. The second cabin frame is provided with a plurality of inter-frame through holes, which are respectively arranged between the second inner support fixing holes and located below the corresponding inter-frame fixing holes. Based on the above, the frame structure formed by alternating long and short sides ensures that the second compartment frame maintains overall stress balance. Fixing holes between the frames are arranged at both ends of the long side, facilitating reliable connection between the second compartment frame and adjacent compartment frames via screws. Fixing holes for the second internal support are provided at both ends of the opposite long side, allowing the internal support to be installed securely and achieve symmetrical support. Furthermore, through holes are added below the fixing holes, which not only facilitates sliding insertion and screw tightening between adjacent compartment frames but also enhances the positioning accuracy and strength at the compartment frame connections, thereby improving the overall splicing reliability and load-bearing capacity of the compartment sections.
[0015] Furthermore, the third compartment frame is integrally formed by four long sides and four short sides of the same length spaced apart in sequence. The top of the third compartment frame is provided with several connecting blocks, which are respectively set at both ends of each long side and inserted into the inter-frame through holes of the second compartment frame by sliding insertion. Each connecting block has a pin fixing hole in the middle. The pin passes through the inter-frame fixing hole and the pin fixing hole in sequence to fix the third compartment frame and the second compartment frame.
[0016] Based on the above, by setting connecting blocks at both ends of the long side of the third compartment frame, it can be slidably inserted into the inter-frame through holes of the second compartment frame and maintain stable positioning. The connecting block is provided with a pin fixing hole in the middle, which cooperates with the inter-frame fixing hole on the second compartment frame, so that the two can be fastened with screws to form a firm connection, avoiding loosening or displacement under flight load. At the same time, the frame structure with alternating long and short sides ensures the overall symmetry and stress balance of the third compartment frame, thereby further improving the overall strength and connection reliability after the upper and lower compartments are spliced.
[0017] Furthermore, both the wall panel a assembly and the wall panel b assembly include a plurality of wall panels and a plurality of wall panel reinforcing members. The plurality of wall panels are arranged sequentially at intervals along the long and short sides of the first, second, third, and fourth compartment frames, and are respectively installed on the wall panel fixing holes. Adjacent wall panels are connected by the wall panel reinforcing members.
[0018] Based on the above, by evenly distributing the wall panels between the long and short sides of each compartment frame, a regular integral structure is formed on the outer wall of the compartment, thereby ensuring the balance of the compartment under stress. Adjacent wall panels are directly connected by wall panel reinforcements, forming a continuous stress path between the wall panels. This not only improves the bonding strength between the wall panels and the compartment frame, but also effectively enhances the overall rigidity and stability of the compartment. At the same time, this modular design facilitates the assembly and replacement of wall panels, which helps to improve the modularity and maintenance convenience of the compartment.
[0019] Furthermore, the wall panel has several parallel elongated holes and several horizontally arranged round holes. The elongated holes are used for heat dissipation of the internal equipment of the UAV compartment, and the round holes are used for the installation and fixing of the internal support of the compartment.
[0020] Based on the above, by opening parallel, elongated holes in the wall panel, the heat dissipation efficiency inside the compartment can be significantly improved, allowing the heat generated by electronic equipment or power units during operation to be released in a timely manner, avoiding the impact of overheating on equipment performance. At the same time, setting horizontally arranged circular holes in the wall panel provides a standardized interface for the arrangement and fixing of internal supports, making equipment installation more convenient and secure, improving the space utilization and functional integration of the compartment, thereby achieving the design goal of lightweight and multifunctional integration.
[0021] To more clearly illustrate the above-mentioned features of this utility model and the objectives it aims to achieve, the present utility model will be further described below in conjunction with the accompanying drawings and specific embodiments. Attached Figure Description
[0022] Figure 1 This is a schematic diagram of the structure of this utility model; Figure 2 This is a structural schematic diagram of the first compartment frame; Figure 3 This is a structural schematic diagram of the second compartment frame; Figure 4 This is a structural schematic diagram of the third compartment frame; Figure 5 This is a schematic diagram of the internal structure of this utility model. Detailed Implementation
[0023] like Figures 1-5As shown, this utility model is a design for a UAV cabin section with a truss-like structure, including an upper cabin section 1 and a lower cabin section 2. The upper cabin section 1 includes a first cabin frame 11, a second cabin frame 12, and a wall panel a assembly 13 connected between the first cabin frame 11 and the second cabin frame 12. The lower cabin section 2 includes a third cabin frame 21, a fourth cabin frame 22, and a wall panel b assembly 23 connected between the third cabin frame 21 and the fourth cabin frame 22. The third cabin frame 21 is slidably inserted into the second cabin frame 12 and fixedly connected by a pin.
[0024] The inner walls of the first compartment frame 11, the second compartment frame 12, the third compartment frame 21 and the fourth compartment frame 22 are provided with a plurality of reinforcing ribs 7, and each reinforcing rib 7 has a wall panel fixing hole 8 in the middle.
[0025] The first cabin frame 11 is integrally formed by four long sides of the same length and four short sides of the same length, which are distributed at intervals in sequence. The top surface of the first cabin frame 11 is provided with a plurality of first internal support fixing holes 110, which are respectively opened at the middle position of each long side.
[0026] The second cabin frame 12 is integrally formed by four long sides of the same length and four short sides of the same length, which are arranged alternately. The side of the second cabin frame 12 is provided with a plurality of inter-frame fixing holes 120, which are respectively opened at both ends of each long side. The inner side of the second cabin frame 12 is provided with a plurality of second inner support fixing holes 121, which are respectively opened at both ends of two opposite long sides. The second cabin frame 12 is provided with a plurality of inter-frame through holes 122, which are respectively arranged between the second inner support fixing holes 121 and located below the corresponding inter-frame fixing holes 120.
[0027] The third compartment frame 21 is integrally formed by four long sides and four short sides of the same length spaced apart in sequence. The top of the third compartment frame 21 is provided with a plurality of connecting blocks 211. The plurality of connecting blocks 211 are respectively disposed at both ends of each long side and are inserted into the inter-frame through holes 122 of the second compartment frame 12 by sliding insertion. Each connecting block 211 has a pin fixing hole 212 in the middle. The pin passes through the inter-frame fixing hole 120 and the pin fixing hole 212 in sequence to fix the third compartment frame 21 and the second compartment frame 12.
[0028] Both wall panel a assembly 13 and wall panel b assembly 23 include a plurality of wall panels 3 and a plurality of wall panel reinforcing members 4. The plurality of wall panels 3 are arranged sequentially at intervals along the long and short sides of the first compartment frame 11, the second compartment frame 12, the third compartment frame 21 and the fourth compartment frame 22, and are respectively installed on the wall panel fixing holes 8. Two adjacent wall panels 3 are connected by the wall panel reinforcing members 4.
[0029] The wall panel 3 has several parallel elongated holes 30 and several horizontally arranged round holes 31. The elongated holes 30 are used for heat dissipation of the internal equipment of the UAV compartment, and the round holes 31 are used for the installation and fixing of the internal support of the compartment.
[0030] In summary, the specific embodiments of this utility model are as follows: First, the lower compartment 2 is pre-assembled. The third compartment frame 21 and the fourth compartment frame 22 are connected by the wall panel b assembly 23 to form the frame structure of the lower compartment. During this process, each wall panel 3 in the wall panel b assembly 23 is installed in the wall panel fixing holes 8 of the third compartment frame 21 and the fourth compartment frame 22 in sequence and fastened with screws. Adjacent wall panels 3 are reinforced and connected by wall panel reinforcing members 4 so that the lower compartment forms a continuous load-bearing whole.
[0031] Next, the upper section 1 is pre-assembled. The first frame 11 and the second frame 12 are connected by the wall panel a assembly 13 to form the frame structure of the upper section. The wall panels 3 in the wall panel a assembly 13 are also installed in the wall panel fixing holes 8 of the first frame 11 and the second frame 12 in sequence, and are fastened with screws. The rigid connection between adjacent wall panels 3 is achieved by the wall panel reinforcement 4, thereby constructing a stable upper section.
[0032] Then, during the segment assembly process, the third frame 21 is slidably inserted into the inter-frame through-hole 122 of the second frame 12, and the connecting block 211 is inserted and aligned with the corresponding position of the inter-frame fixing hole 120. Through the cooperation of the pin fixing hole 212 and the inter-frame fixing hole 120, screws are used to fasten and complete the splicing of the upper segment 1 and the lower segment 2, so that the two parts of the structure form an integral cabin.
[0033] During the operation of the cabin section, the elongated holes 30 on the wall panel 3 serve to dissipate heat, ensuring that the equipment inside the UAV cabin can dissipate heat in time during operation and preventing overheating. The round holes 31 are used for the installation and fixation of the brackets, so that the electronic devices or power components inside the cabin can be installed stably and maintain balanced stress. The reinforcing blocks 7 provide additional reinforcement at both ends of the long side and the middle of the short side of the cabin frame, making the connection between the cabin frame and the wall panel more secure, thereby ensuring that the cabin section has high overall strength and stability during flight.
[0034] In summary, this utility model achieves the goals of lightweight, high strength, and modular assembly through the workflow of "modular splicing of the upper and lower sections - continuous connection of wall panels and reinforcing members - functional design of heat dissipation holes and mounting holes," thus meeting the comprehensive requirements of UAVs for cabin strength, heat dissipation, and internal installation under complex working conditions.
[0035] The above description is only the optimal solution embodiment of this utility model and is not intended to limit this utility model. Various modifications or substitutions made by those skilled in the art to this utility model without departing from the essence and protection scope of this utility model should also be within the protection scope of this utility model.
Claims
1. A type of unmanned aerial vehicle (UAV) cabin section with a truss-like structure, comprising an upper cabin section (1) and a lower cabin section (2), characterized in that: The upper section (1) includes a first frame (11), a second frame (12), and a wall panel a assembly (13) connected between the first frame (11) and the second frame (12). The lower section (2) includes a third frame (21), a fourth frame (22), and a wall panel b assembly (23) connected between the third frame (21) and the fourth frame (22). The third frame (21) is slidably inserted into the second frame (12) and fixedly connected by a pin.
2. The unmanned aerial vehicle (UAV) cabin section with a truss-like structure according to claim 1, characterized in that: The inner walls of the first compartment frame (11), the second compartment frame (12), the third compartment frame (21) and the fourth compartment frame (22) are provided with a number of reinforcing ribs (7), and each reinforcing rib (7) has a wall panel fixing hole (8) in the middle.
3. The unmanned aerial vehicle (UAV) cabin section with a truss-like structure according to claim 1, characterized in that: The first cabin frame (11) is formed by four long sides of the same length and four short sides of the same length, which are distributed in sequence and integrally formed. The top surface of the first cabin frame (11) is provided with a number of first inner support fixing holes (110), and the number of first inner support fixing holes (110) are respectively opened at the middle position of each long side.
4. The unmanned aerial vehicle (UAV) cabin section with a truss-like structure according to claim 1, characterized in that: The second cabin frame (12) is integrally formed by four long sides of the same length and four short sides of the same length arranged in sequence at intervals. The side of the second cabin frame (12) is provided with a plurality of inter-frame fixing holes (120), which are respectively opened at both ends of each long side. The inner side of the second cabin frame (12) is provided with a plurality of second inner support fixing holes (121), which are respectively opened at both ends of two opposite long sides. The second cabin frame (12) is provided with a plurality of inter-frame through holes (122), which are respectively arranged between the second inner support fixing holes (121) and located below the corresponding inter-frame fixing holes (120).
5. The unmanned aerial vehicle (UAV) cabin section with a truss-like structure according to claim 4, characterized in that: The third compartment frame (21) is integrally formed by four long sides of the same length and four short sides of the same length arranged in sequence at intervals. The top of the third compartment frame (21) is provided with several connecting blocks (211). Several connecting blocks (211) are respectively set at both ends of each long side and are inserted into the inter-frame through hole (122) of the second compartment frame (12) by sliding insertion. Each connecting block (211) has a pin fixing hole (212) in the middle. The pin passes through the inter-frame fixing hole (120) and the pin fixing hole (212) in sequence to fix the third compartment frame (21) and the second compartment frame (12).
6. The unmanned aerial vehicle (UAV) cabin section with a truss-like structure according to claim 2, characterized in that: Both the wall panel a assembly (13) and the wall panel b assembly (23) include a number of wall panels (3) and a number of wall panel reinforcing members (4). The wall panels (3) are arranged sequentially and spaced apart along the long and short sides of the first compartment frame (11), the second compartment frame (12), the third compartment frame (21) and the fourth compartment frame (22), and are respectively installed on the wall panel fixing holes (8). Two adjacent wall panels (3) are connected by the wall panel reinforcing members (4).
7. The unmanned aerial vehicle (UAV) cabin section with a truss-like structure according to claim 6, characterized in that: The wall panel (3) has several parallel elongated holes (30) and several horizontally arranged round holes (31). The elongated holes (30) are used for heat dissipation of the internal equipment of the UAV compartment, and the round holes (31) are used for the installation and fixing of the internal support of the compartment.