Aircraft body and aircraft

Abstract

The utility model relates to the technical field of low-altitude traffic equipment, in particular to an aircraft body and an aircraft. The end face of a main beam body is provided with at least two upper auxiliary beams and at least two lower auxiliary beams in parallel; the two ends of the upper auxiliary beam and the two ends of the lower auxiliary beam are connected with the main beam body and gradually get away from the main beam body when extending in the directions of the middle beam bodies of the upper auxiliary beam and the lower auxiliary beam, so that the upper auxiliary beam and the lower auxiliary beam are in an arch shape and are connected with the main beam body. An upper reinforcing beam is arranged on one side of the main beam body, and a lower reinforcing beam is arranged on the other side of the main beam body; expansion frames are arranged at the two ends of the main beam body, are hollow and are provided with expansion pipelines; the whole structure is compact, the structural strength of a machine body is improved, and safety is enhanced; the air resistance in the flight process is reduced while the partial view space of the cabin is prevented from being shielded; the expansion frame can be matched with an expansion unit, and the adaptability of the aircraft body to the aircraft in various scenes is improved.

Description

Technical Field

[0001] This utility model relates to the field of low-altitude transportation equipment technology, specifically to an aircraft body and an aircraft. Background Technology

[0002] Currently, mainstream urban aircraft include fixed-wing, multi-rotor, compound-wing, and tiltrotor aircraft. Fixed-wing aircraft are traditional aircraft with rich experience, but they require runways for takeoff and landing, which places stringent requirements on the takeoff and landing sites. Multi-rotor aircraft have a simple structure and high safety. Compared with fixed-wing aircraft, they can take off and land vertically, which greatly reduces the requirements for takeoff and landing sites. At present, multi-rotor aircraft have been widely used in various fields.

[0003] Chinese utility model patent publication number CN211969736U discloses a multi-rotor aircraft fuselage and the multi-rotor aircraft itself. The fuselage includes a body unit and several pairs of arms. The arms are arranged circumferentially along the body unit. Each pair of arms includes a first arm and a second arm arranged vertically along the body unit. The first and second arms are aligned vertically along the body unit, and their outer ends are coaxial and used to mount rotor assemblies. Specifically, two rotor propellers are mounted on two independent upper and lower arms. By adjusting the distance between the upper and lower arms, the distance between the upper and lower propellers can be adjusted, thus eliminating the need to increase the size of the motor mount to adjust the distance between the upper and lower propellers. This solves the technical problem that existing coaxial dual-propeller aircraft require increasing the size of the motor mount to increase the distance between the upper and lower propellers when the propeller size is large, resulting in increased structural weight.

[0004] However, the existing technologies mentioned above have a relatively complex overall framework and lack a clear cockpit structure design. As for the aircraft body, the frame also seriously affects the cockpit pilot's field of vision and the space utilization within the frame structure is insufficient. The design and space utilization of the fuselage units in the above solutions are unreasonable and cannot meet the manned needs of multi-rotor aircraft. The field of vision for sightseeing or piloting during flight is poor.

[0005] There is an urgent need to develop a technical solution to address the aforementioned technical problems. Utility Model Content

[0006] The purpose of this utility model is to provide an aircraft body and aircraft, which has a compact overall structure, improves the structural strength of the body, and enhances safety; it can avoid obstructing the field of vision of the cockpit and reduce air resistance during flight; it forms a cage-like structure to improve the structural strength of the body; it optimizes the use of space within the body, making reasonable and efficient use of valuable body space; and it can be freely expanded with expansion units to improve the adaptability of the aircraft to various scenarios.

[0007] To achieve the above objectives, this utility model provides the following technical solution;

[0008] An aircraft fuselage includes a main beam, with at least two upper and lower sub-beams arranged parallel to each other on its end faces. Both ends of the upper and lower sub-beams are connected to the main beam, and as they extend towards their respective central beam sections, they gradually move away from the main beam, forming an arched connection with it. An upper reinforcing beam is provided on one side of the main beam, connecting to and supporting the upper sub-beams. A lower reinforcing beam is provided on the other side of the main beam, connecting to and supporting the lower sub-beams. Extension frames are provided at both ends of the main beam, each frame being hollow and equipped with extension pipes.

[0009] Furthermore, multiple upper connecting beams are provided between the upper sub-beams; multiple lower connecting beams are provided between the lower sub-beams.

[0010] Furthermore, the extension frame is provided with a quick-release structure at its end. The quick-release structure includes a quick-release sleeve with fitting openings at both ends. One fitting opening of the quick-release sleeve is provided with a mounting lock opening, which connects to the extension frame. The other fitting opening of the quick-release sleeve is provided with an assembly lock opening, which extends and connects to external components.

[0011] Furthermore, the main beam body has a hollow channel inside, and electrical compartments are set at both ends of a set of main beam bodies, with accommodating space inside each electrical compartment; the internal spaces of the electrical compartments located at both ends of the main beam body are connected by a connecting cavity through the hollow channel inside the main beam body; the expansion pipe connects to the internal space of the electrical compartment.

[0012] Furthermore, it also includes a power supply, which is pluggable and mounted in the electrical compartment.

[0013] An aircraft comprising the aforementioned aircraft body.

[0014] Furthermore, it includes a bottom shell assembly, which is installed at the main beam body;

[0015] Furthermore, the main beam body is provided with a lower assembly beam connected to the lower sub-beam; multiple bottom support beams are provided between the lower assembly beams; the bottom of the bottom shell assembly is connected to the bottom support beams.

[0016] Furthermore, the main beam body is provided with an upper assembly beam connected to the upper sub-beam, and the bottom shell kit is provided with an assembly edge, which is installed at the main beam body and the upper assembly beam.

[0017] Furthermore, it also includes a power mechanism, which is connected to the extension frame.

[0018] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0019] This utility model features a compact overall structure. The main beam serves as the primary frame structure, with a set of main beams spanning the entire fuselage structure, enhancing structural strength and safety. The parallel arched upper and lower sub-beams utilize an arched structure to prevent obstruction of the cockpit's field of vision and effectively reduce air resistance during flight. The upper and lower reinforcing beams, together with the main beams, form a cage-like structure, further enhancing the structural strength of the fuselage. It can be freely expanded with an extension frame to accommodate power components or other attachments or detection units, and the expansion channels enable concealed electrical connections, improving the aircraft's adaptability to various flight scenarios. Attached Figure Description

[0020] Figure 1 This is a three-dimensional structural diagram of the aircraft body of this utility model;

[0021] Figure 2 for Figure 1 Enlarged view of point A in the middle;

[0022] Figure 3 This is a schematic diagram of the planar structure of the aircraft body of this utility model;

[0023] Figure 4 This is a schematic diagram of the internal structure of the aircraft body of this utility model;

[0024] Figure 5 This is a three-dimensional structural diagram of the aircraft of this utility model;

[0025] Figure 6 This is a three-dimensional structural diagram of the aircraft of this utility model from another perspective;

[0026] Figure 7 This is a schematic diagram of the planar structure of the aircraft of this utility model. Detailed Implementation

[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0028] In this embodiment, reference Figures 1-7As shown, an aircraft fuselage includes a main beam 1, with at least two upper sub-beams 2 and lower sub-beams 3 arranged parallel to each other on the end face of the main beam 1; both ends of the upper sub-beams 2 and lower sub-beams 3 are connected to the main beam 1, and as the ends of the upper sub-beams 2 and lower sub-beams 3 extend towards their respective central beams, they gradually move away from the main beam 1, so that the upper sub-beams 2 and lower sub-beams 3 are connected to the main beam 1 in an arch shape; an upper reinforcing beam 41 is provided on one side of the main beam 1, which connects to and supports the upper sub-beams 2, and a lower reinforcing beam 42 is provided on the other side of the main beam 1, which connects to and supports the lower sub-beams 3; extension frames 12 are provided at both ends of the main beam 1, and the extension frames 12 are hollow inside and have extension pipes 12.

[0029] The aircraft airframe features a compact overall structure. The main beam 1 serves as the primary frame structure, with a set of main beams running across the entire airframe to enhance structural strength and safety. The parallel arched upper sub-beam 2 and lower sub-beam 3 employ an arched structure to prevent obstruction of the cockpit's field of vision and effectively reduce air resistance during flight. The upper reinforcing beam 41 and lower reinforcing beam 42, together with the main beam 1, form a cage-like structure, further enhancing the airframe's structural strength. The aircraft can be freely extended with the extension frame 12 to accommodate power components or other attachments or detection units, and the extension pipe 121 enables concealed electrical connections, improving the airframe's adaptability to various flight scenarios.

[0030] In this embodiment, multiple upper connecting beams 21 are provided between the upper sub-beams 2; multiple lower connecting beams 31 are provided between the lower sub-beams 3; the upper connecting beams 21 and the lower connecting beams 31 are used to connect the parallel upper sub-beams 2 and lower sub-beams 3, thereby improving the stability of the upper sub-beams 2 and lower sub-beams 3, further optimizing the structural strength of the body, and improving the safety of the body.

[0031] In this embodiment, the extension frame 12 is provided with a quick-release structure 13 at its end. The quick-release structure 13 includes a quick-release sleeve 131. The quick-release sleeve 131 has fitting openings 133 at both ends. A mounting lock opening 132 is provided at one fitting opening 133 of the quick-release sleeve 131. The mounting lock opening 132 is connected to the extension frame 12. A mounting lock opening 134 is provided at the other fitting opening 133 of the quick-release sleeve 131. The mounting lock opening 134 is extended to connect to external components.

[0032] Specifically, the quick-release structure 13 is a sleeve-type structure. The two ends of the quick-release sleeve 131 are sleeve openings 133. The bolts are used to install the latches 132 and the assembly locks 134 for quick disassembly and assembly, which facilitates functional expansion and maintenance, and broadens the application scenarios of the machine.

[0033] In this embodiment, the main beam 1 has a hollow channel inside, and electrical compartments 11 are provided at both ends of a set of main beams 1. Each electrical compartment 11 has a accommodating space inside. The internal spaces of the electrical compartments 11 located at both ends of the main beam 1 are connected by a connecting cavity 111 through the hollow channel inside the main beam 1. The expansion pipe 121 connects to the internal space of the electrical compartments 11.

[0034] Specifically, the electrical compartment 11 is located at both ends of the main beam 1. The space of the electrical compartment 11 is used to house electrical circuits, etc. It is set with front and rear compartments to facilitate one backup. The power supply and signal lines inside the electrical compartment 11 located at both ends of the main beam 1 are connected to the hollow channel of the main beam 1 through the connecting cavity 111, so as to realize the concealed installation of electrical control components and lines, making reasonable and efficient use of valuable airframe space. With the expansion pipe 121, the electrical lines of the extended external devices can be further concealed, avoiding the external or exposed installation of electrical equipment, improving operational stability, avoiding damage to key electrical components and lines caused by accidents during flight, and improving flight safety.

[0035] In this embodiment, a power supply 7 is also included, which is pluggably mounted on the electrical bay 11. The power supply 7 is provided with a plug-in handle 71. The pluggable power supply 7, together with the dual-bay electrical bay 11, enables rapid battery swapping and replenishment. Combined with the power management control circuit in the prior art, it can realize hot-swap of dual batteries and one backup function, further improving the safety and stability of flight.

[0036] An aircraft comprising the aforementioned aircraft body.

[0037] In this embodiment, a bottom shell kit 5 is included, which is installed on the main beam 1. The bottom shell kit 5 is preferably a seat kit, installed on the main beam 1, providing a reserved design for a pilot's seat on the aircraft.

[0038] In this embodiment, the main beam body 1 is provided with a lower assembly beam 15 connected to the lower sub-beam 3; a plurality of bottom support beams 16 are provided between the lower assembly beams 15; the bottom of the bottom shell kit 5 is connected to the bottom support beams 16.

[0039] Specifically, the lower assembly beam 15 further enhances the structural strength of the lower sub-beam 3 and the main beam 1, and supports and positions the bottom shell assembly 5 through multiple bottom support beams 16, ensuring the weight and structural safety of the bottom shell assembly 5 and improving the overall safety of the aircraft.

[0040] In this embodiment, the main beam body 1 is provided with an upper assembly beam 14 connected to the upper sub-beam 2, and the bottom shell kit 5 is provided with an assembly edge 51, which is installed at the main beam body 1 and the upper assembly beam 14.

[0041] Specifically, the upper assembly beam 14 further enhances the structural strength of the main beam 1 and the upper sub-beam 2, and provides an assembly position for the assembly edge 51 of the bottom shell kit 5, which facilitates the quick positioning and installation of the bottom shell kit 5 and reduces the difficulty of installation.

[0042] This embodiment also includes a power unit 6, which is connected to the extension frame 12. Specifically, the power unit 6 can be a propeller, ducted fan, or other drive device that can provide power to the aircraft. The relevant wiring of the power unit 6 can be connected to the electrical compartment 11 via the extension pipe 121. The propeller and ducted fan used in the aircraft are existing technologies, and their internal hardware structure, electrical control structure, and working principle will not be described in detail in this embodiment.

[0043] The specific embodiments described herein are merely illustrative examples illustrating the spirit of this utility model. Those skilled in the art to which this utility model pertains may make various modifications or additions to the described specific embodiments or use similar methods to replace them, without departing from the scope defined by the spirit of this utility model.

Claims

1. An aircraft fuselage, characterized in that, The main beam (1) is provided with at least two upper sub-beams (2) and lower sub-beams (3) on its end face. Both ends of the upper sub-beams (2) and lower sub-beams (3) are connected to the main beam (1). As the upper sub-beams (2) and lower sub-beams (3) extend toward their respective middle beams, they gradually move away from the main beam (1) so that the upper sub-beams (2) and lower sub-beams (3) are connected to the main beam (1) in an arch shape. The main beam (1) has an upper reinforcing beam (41) on one side, which connects to and supports the upper sub-beam (2). The main beam (1) has a lower reinforcing beam (42) on the other side, which connects to and supports the lower sub-beam (3). The main beam (1) has an extension frame (12) at both ends, which is hollow inside and has an extension pipe (121).

2. The aircraft fuselage according to claim 1, characterized in that, Multiple upper connecting beams (21) are provided between the upper sub-beams (2); multiple lower connecting beams (31) are provided between the lower sub-beams (3).

3. The aircraft fuselage according to claim 1, characterized in that, The extension frame (12) is provided with a quick-release structure (13) at its end. The quick-release structure (13) includes a quick-release sleeve (131). The quick-release sleeve (131) has fitting openings (133) at both ends. The fitting opening (133) on one side of the quick-release sleeve (131) is provided with an installation lock opening (132). The installation lock opening (132) is connected to the extension frame (12). The fitting opening (133) on the other side of the quick-release sleeve (131) is provided with an assembly lock opening (134). The assembly lock opening (134) is extended to connect to external components.

4. The aircraft fuselage according to claim 1, characterized in that, The main beam (1) has a hollow channel inside, and electrical compartments (11) are provided at both ends of a set of main beams (1). The electrical compartments (11) have a accommodating space inside. The internal spaces of the electrical compartments (11) located at both ends of the main beam (1) are connected by a connecting cavity (111) through the hollow channel inside the main beam (1). The expansion pipe (121) connects to the internal space of the electrical compartments (11).

5. The aircraft fuselage according to claim 4, characterized in that, It also includes a power supply (7), which is pluggable and assembled in the electrical compartment (11).

6. An aircraft, characterized in that, The aircraft includes the aircraft body as described in any one of claims 1-5.

7. An aircraft according to claim 6, characterized in that, Includes a bottom shell assembly (5), which is installed at the main beam body (1).

8. An aircraft according to claim 7, characterized in that, The main beam (1) is provided with a lower assembly beam (15) connected to the lower sub-beam (3); multiple bottom support beams (16) are provided between the lower assembly beams (15); the bottom of the bottom shell assembly (5) is connected to the bottom support beams (16).

9. An aircraft according to claim 7, characterized in that, The main beam body (1) is provided with an upper assembly beam (14) connected to the upper sub-beam (2), and the bottom shell kit (5) is provided with an assembly edge (51), which is installed at the main beam body (1) and the upper assembly beam (14).

10. An aircraft according to claim 7, characterized in that, It also includes a power mechanism (6), which is connected to the extension frame (12).

Images