Aircraft rack

Abstract

The utility model provides an aircraft frame which is characterized in that an arm lower framework, an arm upper framework and an arm middle framework are respectively led to a motor mounting platform at a chassis, a longitudinal beam and a front-back extension connecting position of the chassis and the longitudinal beam, so that the mounting stability of a motor and wings can be ensured; the two longitudinal beams are arranged above the chassis in parallel at intervals, so that a web firmware mounting area is formed between the two longitudinal beams and can be used for mounting firmware such as a battery and a main controller. According to the aircraft frame provided by the utility model, the belly fixing piece mounting area is arranged at the top of the frame, so that the mounting and fixing reliability of a modular assembly mounted in the belly fixing piece mounting area can be effectively improved while the convenience in disassembly and assembly is ensured, and the use convenience and reliability of an aircraft are improved; and the reliability of the vehicle arm formed by the plurality of frameworks is high, so that the reliability of the aircraft can be effectively guaranteed.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to an aircraft frame. Background Technology

[0002] With the rapid development of aviation technology and other related technologies, drone technology has gradually matured and is widely used in various fields. Small drones, due to their ease of operation, low cost, portability, and deployment, have received increasing attention and application. In fields such as aerial photography, environmental monitoring, agricultural plant protection, and social rescue surveillance, small drones have demonstrated enormous potential and value.

[0003] As the application scenarios for small drones continue to expand, higher demands are being placed on the modularity and scalability of the rack. Modular design allows users to easily assemble and disassemble according to actual needs, while scalability allows users to add or upgrade peripherals (cameras, batteries, communicators, etc.) and functions without changing the basic structure of the rack.

[0004] Among them, racing drones are the main type of drone racing sports. They have high speeds and high requirements for structural strength. At the same time, they have higher scalability. In the existing technology, racing drones have a variety of docking structures on the frame to facilitate the assembly and replacement of peripherals. The setting of docking structures will reduce the structural strength of the frame and reduce the reliability of the racing drone. Utility Model Content

[0005] Based on this, the purpose of this utility model is to provide an aircraft frame to solve the problem of insufficient overall structural reliability of the frame of a highly expandable UAV in the prior art due to the setting of multiple docking structures.

[0006] This utility model provides an aircraft frame, including: a chassis, and longitudinal beams disposed above the chassis, wherein,

[0007] The chassis includes a lower frame of the arm extending outward from the four corners of the chassis, and an extension frame extending forward and backward from the front and rear ends of the chassis, with a motor mounting platform provided at the end of the lower frame of the arm.

[0008] Two longitudinal beams are arranged side by side at intervals to form a web fastener installation area between the two longitudinal beams, and the front and rear ends of the longitudinal beams extend downward in a streamlined manner to the end of the extension frame and are connected to the extension frame to form an integral structure.

[0009] The main body of the longitudinal beam is an upright plate structure, and the longitudinal beam also includes an upper frame of the arm that extends from the outer wall of the longitudinal beam to the corresponding motor mounting platform;

[0010] The connection points between the front and rear ends of the longitudinal beam and the corresponding extended skeleton also include the arm frame extending to the corresponding motor mounting platform.

[0011] Optionally, a first reinforcing rib is also provided between the roots of the lower frame of the arm located on the same side.

[0012] Optionally, a first hollow structure is provided in the middle of the root of the lower frame of the arm.

[0013] Optionally, the lower surface of the lower frame of the arm also includes a weight-reducing groove extending from the first hollow structure to the end.

[0014] Optionally, the upper frame of the robotic arm is located directly above the lower frame of the robotic arm.

[0015] Optionally, the longitudinal beam further includes an inner support frame extending from the lower surface of the longitudinal beam to the corresponding extension frame, wherein the root position of the inner support frame is aligned with the root position of the corresponding upper frame of the boom, and the gap between the inner support frame and the corresponding extension frame and the longitudinal beam is matched.

[0016] Optionally, the inner support frame of a single longitudinal beam includes two front inner support frames and one rear inner support frame. A front fastener mounting plate is also provided in the gap between the two front inner support frames and the longitudinal beam. The two front fastener mounting plates provided on the two longitudinal beams are arranged in a mirror symmetrical manner.

[0017] Optionally, the rear end of the longitudinal beam is further provided with a vertically extending rear fastener mounting plate at the connection position between the rear end of the longitudinal beam and the corresponding extended frame.

[0018] Optionally, the main plate of the chassis is further provided with a second hollow structure.

[0019] Optionally, two of the extended skeletons are arranged side by side at intervals along the same direction, and their ends are connected by a cross skeleton to form an integral structure.

[0020] The aircraft frame provided by this utility model includes: a chassis and longitudinal beams disposed above the chassis. The lower arm frame, upper arm frame, and middle arm frame are respectively led out from the chassis, the longitudinal beams, and the front and rear extension connection points of the chassis and the longitudinal beams to the motor mounting platform, ensuring the installation stability of the motors and wings. Two longitudinal beams are arranged side-by-side at intervals to form a mounting area for the belly fasteners between them. This area can be used for the installation of fasteners such as batteries, main controllers, and cameras. The belly fasteners can be easily installed and removed from above, and their weight is fully loaded onto the frame body, avoiding fatigue damage to movable installation components and ensuring reliable fixation. During aircraft operation, the belly fastener mounting area tends to clamp, further improving the fixation reliability of the belly fasteners. The aircraft frame provided by this utility model has the belly fastener mounting area located at the top of the frame. While ensuring convenient disassembly and assembly, it can also effectively improve the installation and fixing reliability of modular components installed in the belly fastener mounting area, thereby improving the ease of use and reliability of the aircraft. In addition, the arm is composed of multiple frames, which can effectively improve the structural strength of the arm and ensure the reliability of the aircraft. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the main three-dimensional structure of the aircraft frame in this embodiment of the utility model;

[0022] Figure 2 This is a three-dimensional structural diagram of the bottom surface of the aircraft frame in an embodiment of this utility model;

[0023] Figure 3 This is a side view of the aircraft frame structure in an embodiment of the present utility model;

[0024] Figure 4 This is a bottom view of the aircraft frame structure in an embodiment of the present invention.

[0025] The following detailed description, in conjunction with the accompanying drawings, will further illustrate this utility model. Detailed Implementation

[0026] To facilitate understanding of this utility model, a more complete description will be given below with reference to the accompanying drawings. Several embodiments of this utility model are shown in the drawings. However, this utility model can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided so that the disclosure of this utility model will be more thorough and complete.

[0027] It should be noted that when a component is said to be "fixed to" another component, it can be directly on the other component or there may be an intervening component. When a component is said to be "connected to" another component, it can be directly connected to the other component or there may be an intervening component. The terms "vertical," "horizontal," "left," "right," and similar expressions used in this document are for illustrative purposes only.

[0028] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0029] To address the issues of insufficient reliability of modular UAV frame structures and inconvenient modular assembly and disassembly in existing technologies, this invention provides an aircraft frame. The frame features lower arm frames, upper arm frames, and middle arm frames extending from the chassis, longitudinal beams, and the front and rear extension connections between the chassis and longitudinal beams to a motor mounting platform, ensuring the stability of the motor and wing installations. Two longitudinal beams are positioned parallel to each other above the chassis, forming a mounting area for components such as batteries and main controllers. Positioning this mounting area at the top of the frame ensures ease of assembly and disassembly while effectively improving the reliability of modular components installed there, thus enhancing the aircraft's usability and reliability.

[0030] Specifically, such as Figures 1 to 4 The diagram shown is a structural schematic of the aircraft frame in this embodiment, including a chassis 100 and a longitudinal beam 200 disposed above the chassis 100. The front and rear ends of the chassis 100 are respectively curved upward and extend forward and backward to form an extension frame 122. The front and rear ends of the longitudinal beam 200 are respectively streamlined downward to the end of the extension frame 122 and are connected with the extension frame 122 to form an integral structure, forming a main receiving cavity between the chassis 100 and the longitudinal beam 200.

[0031] The chassis 100 includes a lower arm frame 110 extending outward from each of the four corners of the chassis 100, with a motor mounting platform 300 at the end of each lower arm frame 110. The main body of the longitudinal beam 200 is a vertical plate structure, and the longitudinal beam 200 also includes an upper arm frame 210 extending from the outer wall of the longitudinal beam 200 to the corresponding motor mounting platform 300. The connection points between the front and rear ends of the longitudinal beam 200 and the corresponding extended frame 120 also include a middle arm frame 310 extending to the corresponding motor mounting platform 300. Each arm consists of three frames, which effectively ensures the structural strength of the arm, while the spacing design between the frames effectively reduces the overall weight, ensuring the realization of lightweight characteristics.

[0032] The main housing cavity can be used for the installation of batteries, main controllers, sensors, etc. In order to meet the requirements of easy disassembly in the modular design, in this embodiment, two longitudinal beams 200 are arranged side by side at intervals to form a belly fastener installation area between the two longitudinal beams 200. The belly fastener can be pre-assembled on the belly fastener support frame, vertically embedded into the belly fastener installation area through the belly fastener support frame, and then fixed by the mounting holes and screws on the longitudinal beams 200.

[0033] To improve the structural stability of the boom, in this embodiment, such as Figure 2 and Figure 4 As shown, a first reinforcing rib 113 is also provided between the roots of the lower frame 110 of the arm on the same side, and the gap between the first reinforcing rib 113 and the main board of the chassis 100 is matched, which can reduce the weight increase of the first reinforcing rib 113 on the overall frame. The combination line of the outer edge of the first reinforcing rib 113 and the outer edge of the lower frame 110 of the arm is a streamlined curve, which can improve its aerodynamic performance and increase the reinforcing range of the first reinforcing rib 113 on the lower frame 110 of the arm, thereby enhancing the strengthening effect on the structural strength.

[0034] To further reduce the weight of the frame, in this embodiment, the root dimension of the lower frame 110 of the arm is relatively large, and a first hollow structure 111 is provided in the middle of the root of the lower frame 110 of the arm, which can reduce its weight while ensuring its structural strength.

[0035] To further reduce the weight of the frame, the lower surface of the lower frame 110 of the arm also includes a weight-reducing groove 112 extending from the first hollow structure 111 to the end, which can ensure its structural strength while further reducing its weight.

[0036] To improve vertical consistency, in this embodiment, the upper frame 210 of the robotic arm is located directly above the lower frame 110 of the robotic arm, resulting in symmetrical stress distribution. This reduces stress damage caused by stress deviation and improves the structural reliability of the robotic arm.

[0037] To further improve the reliability of the connection between the chassis 100 and the longitudinal beam 200, the longitudinal beam 200 also includes an inner support frame 220 extending from the lower surface of the longitudinal beam 200 to the corresponding extension frame 120. The root position of the inner support frame 220 is aligned with the root position of the corresponding upper frame 210 of the boom, which can strengthen the structural strength of the main stress area and improve the support effect.

[0038] The internal support frame 220 is matched with the corresponding extension frame 120 and longitudinal beam 100 to reduce weight.

[0039] Please refer to Figure 3 The inner support frame 220 of a single longitudinal beam 200 includes two front inner support frames and one rear inner support frame. A front fastener mounting plate 400 is also provided in the gap between the two front inner support frames and the longitudinal beam 200. The two front fastener mounting plates 400 on the two longitudinal beams 200 are mirror-symmetrically arranged and can be used for mounting fasteners such as lenses.

[0040] To improve the rack's scalability, in this embodiment, such as Figure 2 and Figure 3 As shown, the rear end of the longitudinal beam 200 and the corresponding extension frame 120 are also provided with a vertically extending rear fastener mounting plate 121.

[0041] To further reduce the weight of the frame, in this embodiment, the main plate of the chassis 100 is also provided with a second hollow structure 101. Specifically, there are four second hollow structures 101 arranged in a grid pattern, and multiple mounting holes are provided around them for the installation of other functional components.

[0042] Since the two longitudinal beams 200 are arranged side by side and spaced apart, in order to improve the overall strength of the frame, in this embodiment, two extension frames 120 are arranged side by side and spaced apart, and the ends are connected into an integral structure by a horizontal frame 122, which connects the left and right structures at the front and rear ends of the frame into an integral structure, thereby improving its structural strength and improving the installation and fixing stability of the components set at the front and rear ends of the frame.

[0043] The aircraft frame provided by this utility model features lower arm frames, upper arm frames, and middle arm frames extending from the chassis, longitudinal beams, and the front and rear extension connections between the chassis and longitudinal beams to the motor mounting platform, ensuring the installation stability of the motors and wings. Two longitudinal beams are positioned above the chassis, spaced apart side-by-side, forming a mounting area for the main components (such as batteries and main controllers). Positioning this mounting area at the top of the frame ensures ease of assembly and disassembly while effectively improving the reliability of the modular components installed there, thus enhancing the aircraft's usability and reliability. Furthermore, the arm's multiple frames allow for even distribution of structural stress during movement, effectively increasing the arm's structural strength and ensuring the aircraft's reliability.

[0044] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0045] The embodiments described above are merely illustrative of several specific implementations of this utility model, and while the descriptions are detailed, they should not be construed as limiting the scope of this utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model patent should be determined by the appended claims.

Claims

1. An aircraft frame, characterized in that, include: The chassis, and the longitudinal beams disposed above the chassis, wherein, The chassis includes a lower frame of the arm extending outward from the four corners of the chassis, and an extension frame extending forward and backward from the front and rear ends of the chassis, with a motor mounting platform provided at the end of the lower frame of the arm. Two longitudinal beams are arranged side by side at intervals to form a web fastener installation area between the two longitudinal beams, and the front and rear ends of the longitudinal beams extend downward in a streamlined manner to the end of the extension frame and are connected to the extension frame to form an integral structure. The main body of the longitudinal beam is an upright plate structure, and the longitudinal beam also includes an upper frame of the arm that extends from the outer wall of the longitudinal beam to the corresponding motor mounting platform; The connection points between the front and rear ends of the longitudinal beam and the corresponding extended skeleton also include the arm frame extending to the corresponding motor mounting platform.

2. The aircraft frame according to claim 1, characterized in that, A first reinforcing rib is also provided between the roots of the lower frame of the arm located on the same side.

3. The aircraft frame according to claim 1, characterized in that, The lower frame of the arm has a first hollow structure in the middle of its root.

4. The aircraft frame according to claim 3, characterized in that, The lower surface of the lower frame of the arm also includes a weight-reducing groove extending from the first hollow structure to the end.

5. The aircraft frame according to claim 1, characterized in that, The upper frame of the robotic arm is located directly above the lower frame of the robotic arm.

6. The aircraft frame according to claim 1, characterized in that, The longitudinal beam also includes an inner support frame extending from the lower surface of the longitudinal beam to the corresponding extension frame. The root position of the inner support frame is aligned with the root position of the corresponding upper frame of the boom. The gap between the inner support frame and the corresponding extension frame and the longitudinal beam is matched.

7. The aircraft frame according to claim 6, characterized in that, The inner support frame of a single longitudinal beam includes two front inner support frames and one rear inner support frame. A front fastener mounting plate is also provided in the gap between the two front inner support frames and the longitudinal beam. The two front fastener mounting plates provided on the two longitudinal beams are arranged in a mirror symmetrical manner.

8. The aircraft frame according to claim 1, characterized in that, The rear end of the longitudinal beam is also provided with a vertically extending rear fastener mounting plate at the connection position between it and the corresponding extended frame.

9. The aircraft frame according to claim 1, characterized in that, The main plate of the chassis is also provided with a second hollow structure.

10. The aircraft frame according to claim 1, characterized in that, The extended skeleton is provided in two parallel rows with intervals along the same direction, and the ends are connected by a cross skeleton to form an integral structure.

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