Aircraft rack

Abstract

The invention relates to the technical field of aircrafts, in particular to an aircraft rack which comprises two frame type supports. The two supporting plates are arranged in the middle of the two frame-type supports so as to connect the two frame-type supports into a whole; the two ends of the reinforcing shaft are fixed to the two frame type supports through connecting parts respectively, and the reinforcing shaft penetrates through the two supporting plates. According to the aircraft frame, the two frame type supports are arranged, the strength of the aircraft arm part can be effectively improved, the two frame type supports are connected together through the two supporting plates, a containing space used for installing equipment can be defined in the center of the aircraft frame, the light weight is achieved, and meanwhile the aircraft arm part can be conveniently installed. The heat dissipation effect after equipment in the central area of the rack is installed can be improved, the reinforcing shaft penetrates through the two supporting plates and is fixed to the two external frame type supports, the overall strength of the rack can be greatly improved, and then the aircraft rack has the high strength and the light weight.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and specifically to an aircraft frame. Background Art

[0002] An aircraft is a device that flies within the atmosphere or in outer space (space). The frame structure is the basic framework that supports the aircraft. It is the core component of the aircraft to bear external loads and maintain overall stiffness and stability, and is closely related to flight safety, performance, durability, etc. At present, aircraft frames generally have the problems of high self-weight or low strength. How to balance the weight and strength of the frame while ensuring the toughness and stability of the frame has always been an important problem faced in the field of aircraft manufacturing.

[0003] Prior arts such as a multi-rotor unmanned aircraft disclosed in CN114728693B (each pair of first arms can be in an unfolded state or a folded state; when in the unfolded state, each pair of first arms are radially unfolded relative to the central body; when in the folded state, each pair of first arms are folded up and down, and the rotation axes of the rotor devices of each pair of first arms are substantially coplanar to prevent interference with components such as the central body or occupying a large space) and a frame structure of an aircraft disclosed in CN109383778B (including a frame main body, arms, propeller assemblies, and propeller protection assemblies, wherein the frame main body is connected to one end of the arms; the propeller assemblies are respectively connected to the other end of the arms and the propeller protection assemblies; and the propeller protection assemblies are used to protect the propeller assemblies and also used as landing gears) all have some common characteristics. First, the abdominal area of these aircraft frames is heavy, and the arm parts are thin, with insufficient overall support force and it is difficult to form a good protection effect on the propeller structure. Second, the abdominal area of these aircraft frames is too closed and compact, which will not only increase materials and weight, but also reduce the heat dissipation effect of the internal equipment, and at the same time increase the disassembly and assembly difficulty of the internal equipment, making it inconvenient to layout the internal installed equipment according to actual usage requirements. In view of this, we propose an aircraft frame. Summary of the Invention

[0004] The purpose of the embodiments of the present invention is to provide an aircraft frame, which solves the problem that the aircraft frames in the prior art cannot balance the weight and strength of the frame while ensuring the toughness and stability of the frame.

[0005] To achieve the above purpose, the present invention provides the following technical solutions:

[0006] An aircraft frame includes two frame brackets;

[0007] Two support plates are arranged in the middle position between the two frame brackets to connect the two frame brackets into a whole;

[0008] The reinforcing shaft is fixed to two frame brackets at both ends respectively through connecting components, and the reinforcing shaft penetrates through two support plates.

[0009] As a preferred technical solution, the frame bracket includes two first support rods and two second support rods. The two first support rods are respectively fixedly connected to both ends of the support plate. Connecting blocks are fixedly connected to both ends of the first support rod. The two second support rods are symmetrically arranged with the center line of the first support rod as the axis of symmetry, and both ends of the second support rod are respectively fixedly connected to the two connecting blocks, so that the first support rod and the second support rod are connected end to end to form a rectangular frame structure.

[0010] As a preferred technical solution, the two frame brackets are symmetrically arranged with the center line of the support plate as the axis of symmetry. One end of the two coaxially arranged connecting blocks is used to install a motor and a propeller, and landing cones are installed at the opposite ends.

[0011] As a preferred technical solution, the first support rod, the second support rod, the support plate and the reinforcing shaft are all made of carbon fiber reinforced composite material. The first support rod is rod-shaped, the second support rod is tubular, a sleeve is fixedly connected to the connecting block, the sleeve is sleeved on the second support rod, and a through hole for wire routing is provided at the end of the second support rod penetrating through the sleeve.

[0012] As a preferred technical solution, a plurality of mounting holes are formed in the support plate, and a mounting frame is installed through bolts. The mounting frame includes a vertical plate and a horizontal plate formed on the vertical plate. A hole perpendicular to the mounting hole is formed in the horizontal plate for mounting a support plate.

[0013] As a preferred technical solution, a buffer block is fixedly connected to the position where the hole is provided on the vertical plate. The buffer block is made of a flexible material. A plurality of weight reduction holes and a plurality of buffer holes are formed in the support plate, and the buffer holes are used for installing buffer pads.

[0014] As a preferred technical solution, the reinforcing shaft is a hollow shaft, and wire routing ports are provided at both ends and the middle position of the reinforcing shaft to facilitate the entry and exit of wires.

[0015] As a preferred technical solution, the connecting component includes a first connecting sleeve. One end of the first connecting sleeve is sleeved on one end of the reinforcing shaft and locked by bolts. A through hole is formed in the other end of the first connecting sleeve. Two second connecting pipes are fixedly connected to the circumferential side of the first connecting sleeve. The two second connecting pipes are respectively sleeved on the middle positions of the two second support rods.

[0016] As a preferred technical solution, the second support rod is in a straight shape or a V shape, and the shape of the second connecting pipe is adapted to the shape of the second support rod.

[0017] As a preferred technical solution, two supports are fixedly installed on the reinforcing shaft, and electric landing gears are installed on both supports. One side of the two supports facing each other is fixedly connected to the support plate through bolts.

[0018] With the above technical solution, the present invention provides an aircraft frame, which has at least the following beneficial effects:

[0019] (1) For this aircraft frame, by setting two frame-shaped brackets, the strength of the arm part can be effectively increased. By connecting the two frame-shaped brackets together with two support plates, a receiving space for installing equipment can be formed at the center of the frame. While achieving lightweight, the heat dissipation effect after installing equipment in the central area of the frame can be improved. By passing the reinforcing shaft through the two support plates and fixing it to the two external frame-shaped brackets, the overall strength of the frame can be greatly improved, so that the aircraft frame combines high strength and lightweight.

[0020] (2) For this aircraft frame, by setting a plurality of mounting holes on the support plate, it is convenient for the installation of the mounting frame and the support plate, and thus it is convenient for the disassembly and assembly of equipment, etc. The difficulty of equipment disassembly and assembly is reduced, and it is convenient for users to layout the equipment according to actual usage requirements, improving the convenience of use.

[0021] (3) For this aircraft frame, the structures such as the frame-shaped brackets, support plates, reinforcing shafts, and connecting parts are easy to install and are all detachable, which is convenient for assembling the aircraft frame. After the frame is damaged, it is convenient to replace the damaged structures, improving the overall convenience of use of the aircraft frame. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of this application:

[0023] Figure 1 It is a schematic diagram of the overall structure of an embodiment of the present invention;

[0024] Figure 2 It is a schematic diagram of the frame in an embodiment of the present invention;

[0025] Figure 3 It is a schematic diagram of the frame-shaped bracket and the reinforcing shaft in an embodiment of the present invention;

[0026] Figure 4 It is a schematic diagram of the second strut being in a straight shape in an embodiment of the present invention;

[0027] Figure 5 It is a schematic diagram of the support plate in an embodiment of the present invention;

[0028] Figure 6 It is a first perspective schematic diagram of the vertical plate in an embodiment of the present invention;

[0029] Figure 7 This is the second perspective schematic diagram of the vertical plate in the embodiment of the present invention;

[0030] Figure 8 This is the schematic diagram of the connecting component in the embodiment of the present invention.

[0031] In the figure: 1. Frame-type support; 101. First strut; 102. Second strut; 103. Connecting block; 104. Landing cone; 105. Sleeve; 2. Support plate; 201. Mounting hole; 202. Weight-reducing hole; 203. Buffer hole; 204. Mounting frame; 2041. Vertical plate; 2042. Horizontal plate; 2043. Buffer block; 205. Support plate; 3. Reinforcing shaft; 301. Wire routing opening; 4. Connecting component; 401. First connecting sleeve; 402. Connecting frame; 403. Second connecting pipe; 5. Accommodating space; 6. Support; 7. Landing gear. Detailed implementation manners

[0032] The following further describes the implementation manners of the present disclosure in detail in conjunction with the drawings and embodiments. The detailed descriptions and drawings of the following embodiments are used to exemplarily illustrate the principles of the present disclosure, but cannot be used to limit the scope of the present disclosure. The present disclosure can be implemented in many different forms, not limited to the specific embodiments disclosed herein, but including all technical solutions falling within the scope of the claims.

[0033] These embodiments are provided by the present disclosure to make the present disclosure thorough and complete, and to fully express the scope of the present disclosure to those skilled in the art. It should be noted that: unless otherwise specifically stated, the relative arrangements of the components and steps set forth in these embodiments, the components of the materials, the numerical expressions and values should be construed as merely exemplary, rather than as limitations.

[0034] It should be noted that in the description of the present disclosure, unless otherwise stated, the meaning of "a plurality" is greater than or equal to two; the terms "upper", "lower", "left", "right", "inner", "outer", etc. indicate the orientation or positional relationship only for the convenience of describing the present disclosure and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be construed as a limitation of the present disclosure. When the absolute position of the described object changes, the relative position relationship may also change accordingly.

[0035] In addition, the "first", "second" and similar terms used in the present disclosure do not represent any order, quantity or importance, but are only used to distinguish different parts. "Vertical" is not strictly vertical, but within the allowable error range. "Parallel" is not strictly parallel, but within the allowable error range. The terms "including" or "comprising" and the like mean that the elements before the term cover the elements listed after the term, and do not exclude the possibility of also covering other elements.

[0036] It should also be noted that in the description of the present disclosure, unless otherwise clearly specified and limited, the terms "installed", "connected", and "coupled" 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 directly connected, or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present disclosure can be understood according to specific circumstances.

[0037] Technologies, methods, and devices known to those of ordinary skill in the relevant fields may not be discussed in detail, but where appropriate, the technologies, methods, and devices should be regarded as part of the specification.

[0038] Please refer to Figures 1-8 , an embodiment of the present invention provides an aircraft frame, including:

[0039] Two frame brackets 1, the frame brackets 1 are rectangular, the two frame brackets 1 are symmetrically arranged up and down, and a propeller structure is respectively connected to eight diagonal positions of the two frame brackets 1. By using the two frame brackets 1 to support the eight propellers, the strength at the arm and the stability of the propeller structure can be effectively improved;

[0040] Two support plates 2, arranged at the middle positions of the two frame brackets 1, and the four corners of the support plates 2 are respectively fixed to the frame brackets 1 to fix the two frame brackets 1 into a whole, so that the aircraft fuselage position has sufficient strength and stability; and

[0041] A strengthening shaft 3, both ends of the strengthening shaft 3 are respectively fixed to the two frame brackets 1 through connecting components 4, and the strengthening shaft 3 penetrates through the two support plates 2 to improve the overall strength of the frame.

[0042] In this embodiment, the area surrounded by the two support plates 2 and the two frame brackets 1 is used to install mechanisms such as an equipment compartment, a gimbal, and a battery. Since the area between the two support plates 2 and the two frame brackets 1 is not a closed fuselage mechanism, the heat dissipation effect and light weight of the aircraft can be improved.

[0043] As a preferred embodiment, the frame bracket 1 includes two first struts 101 and two second struts 102. The two first struts 101 are respectively fixedly connected to both ends of the two support plates 2, and connection blocks 103 are fixedly connected to both ends of the first strut 101. The two second struts 102 are symmetrically arranged with the center line of the first strut 101 as the axis of symmetry, and both ends of the second strut 102 are respectively fixedly connected to the two connection blocks 103, so that the first strut 101 and the second strut 102 are connected end to end to form a rectangular frame structure.

[0044] It should be noted that the first support rod 101, the second support rod 102, the support plate 2 and the reinforcing shaft 3 are all made of carbon fiber reinforced composite material (CFRP), which can reduce weight while ensuring the mechanical properties of the frame, thereby improving the load capacity and flight performance of the aircraft.

[0045] Furthermore, the two frame brackets 1 are symmetrically arranged up and down with the center line of the support plate 2 as the axis of symmetry. Therefore, the connecting blocks 103 provided on the two frame brackets 1 are coaxial and symmetric in pairs. Specifically, the eight connecting blocks 103 are divided into four groups in total, and each group of connecting blocks 103 is coaxial and symmetric. One end of each group of connecting blocks 103 opposite to each other is used to install the motor and the propeller, so that the aircraft is in an eight-rotor configuration. Landing cones 104 are installed at the opposite ends of each group of connecting blocks 103. There are a total of eight landing cones 104, which can protect the propellers and improve the safety of the aircraft during takeoff and landing.

[0046] In addition, there is a mounting position for the propeller protection mechanism between the connecting block 103 and the first support rod 101 and the second support rod 102, so that the propeller protection structure can be detachably mounted on the frame bracket 1, further improving the protection effect on the propellers and the safety during the use of the aircraft.

[0047] As a preferred embodiment, the first support rod 101 is rod-shaped to ensure the strength of the frame, and the second support rod 102 is tubular with a hollow interior, which is convenient for wire routing and at the same time reduces the overall weight of the frame.

[0048] Furthermore, a sleeve 105 is fixedly connected to the connecting block 103. The sleeve 105 is sleeved on the second support rod 102. The end of the second support rod 102 penetrates through the sleeve 105 and is provided with a through hole for wire routing, which is convenient for leading the wire from the inside of the frame to the propeller motor, hiding the wire routing to improve the overall safety and aesthetics of the aircraft.

[0049] As a preferred embodiment, the two support plates 2 are symmetrically arranged with the center line of the first support rod 101 as the axis of symmetry. The ends of the support plates 2 are respectively fixedly connected to two of the first support rods 101 in the two frame brackets 1. The height of the support plates 2 determines the height difference between the two frame brackets 1.

[0050] Furthermore, a rectangular accommodation space 5 is formed between the two support plates 2 and the four first support rods 101 for installing equipment. A plurality of mounting holes 201 are formed in the support plates 2. A mounting bracket 204 can be mounted on the mounting holes 201 through bolts. The mounting bracket 204 includes a vertical plate 2041 and a horizontal plate 2042 formed on the vertical plate 2041. A hole coaxial with the mounting hole 201 is formed in the vertical plate 2041 for mounting the vertical plate 2041 onto the support plate 2. A hole perpendicular to the mounting hole 201 is formed in the horizontal plate 2042 for mounting a support plate 205. Four groups of holes are formed in the support plate 205 for docking with the horizontal plate 2042 respectively. During installation, first, four mounting brackets 204 are symmetrically mounted on the two support plates 2 such that the horizontal plates 2042 on the four mounting brackets 204 are at the same horizontal height. Then, the support plate 205 is horizontally placed on the horizontal plate 2042. The holes on both sides of the support plate 205 are aligned with the holes on the horizontal plate 2042. Then, the support plate 205 is mounted on the horizontal plate 2042 through bolts, achieving the purpose of facilitating disassembly and assembly.

[0051] As a preferred embodiment, a buffer block 2043 is fixedly connected to the position where the hole is formed on the vertical plate 2041. The buffer block 2043 is made of a flexible material and is used for buffering and damping the forces between the vertical plate 2041 and the support plate 2 and between the equipment and the vertical plate 2041.

[0052] In addition, a plurality of weight-reducing holes 202 are formed in the support plates 2. The weight-reducing holes 202 have different shapes, which can reduce the weight of the support plates 2 while ensuring the strength of the support plates 2 and improving the heat dissipation effect of the equipment.

[0053] In addition, a plurality of buffer holes 203 are also formed in the support plates 2 for installing buffer pads to protect structures such as the equipment cabin.

[0054] As a preferred embodiment, the reinforcing shaft 3 is a hollow shaft with a hollow interior, which is convenient for wire routing and improves lightweight at the same time. Wire routing openings 301 are formed at both ends and the middle position of the reinforcing shaft 3 to facilitate the entry and exit of wires. The reinforcing shaft 3 is perpendicular to the support plate 2 and is arranged at the middle position of the aircraft frame, which can effectively improve the overall strength of the frame.

[0055] As a preferred embodiment, the connecting member 4 includes a first connecting sleeve 401. One end of the first connecting sleeve 401 is sleeved on one end of the reinforcing shaft 3 and locked by bolts. A through hole is formed in the other end of the first connecting sleeve 401 for wire routing. Two second connecting pipes 403 are fixedly connected to the circumferential side of the first connecting sleeve 401 through a connecting frame 402. The two second connecting pipes 403 are symmetrically arranged with the center line of the first connecting sleeve 401 as the axis of symmetry. The two second connecting pipes 403 are respectively sleeved on the middle positions of the two second support rods 102, and the second support rods 102 are locked by bolts, so as to connect the second support rods 102 with the reinforcing shaft 3 together, which can greatly improve the overall strength of the frame.

[0056] Please structure Figure 3 and Figure 4 As shown, the second support rod 102 is in a straight shape or a V shape, and the shape of the second connecting pipe 403 is adapted to the shape of the second support rod 102. When the second support rod 102 is in a V shape, the second support rod 102 is formed by splicing two straight rods, which is convenient for inserting the second support rod 102 into the second connecting pipe 403.

[0057] In addition, two supports 6 are fixedly installed on the reinforcing shaft 3. The two supports 6 are symmetrically arranged, and electric landing gears 7 are rotatably installed on both of the two supports 6. One side of the two supports 6 facing each other is fixedly connected to the support plate 2 by bolts respectively to improve the stability of the supports 6 and the electric landing gears 7.

[0058] For this aircraft frame, by providing two frame brackets 1, the strength of the arm part can be effectively increased. By connecting the two frame brackets 1 together through two support plates 2, a receiving space 5 for installing equipment can be formed at the center position of the frame. While achieving lightweight, the heat dissipation effect after installing equipment in the central area of the frame can be improved. By passing the reinforcing shaft 3 through the two support plates 2 and fixing it to the two external frame brackets 1, the overall strength of the frame can be greatly improved, so that the aircraft frame has both high strength and lightweight.

[0059] So far, the embodiments of the present disclosure have been described in detail. In order to avoid obscuring the concept of the present disclosure, some details well known in the art have not been described. Those skilled in the art can clearly understand how to implement the technical solutions disclosed here based on the above description.

[0060] Although some specific embodiments of the present disclosure have been described in detail by way of examples, those skilled in the art should understand that the above examples are only for illustration and not for limiting the scope of the present disclosure. Those skilled in the art should understand that the above embodiments can be modified or equivalent substitutions can be made to some technical features without departing from the scope and spirit of the present disclosure. In particular, as long as there is no structural conflict, the technical features mentioned in each embodiment can be combined in any way.

Claims

1. An aircraft fuselage, characterized in that, The frame includes: Two frame brackets (1); Two support plates (2), arranged at the middle positions of the two frame brackets (1) to connect the two frame brackets (1) into an integral whole; A reinforcing shaft (3), with both ends respectively fixed to the two frame brackets (1) through connecting components (4), and the reinforcing shaft (3) penetrates through the two support plates (2).

2. The aircraft frame according to claim 1, wherein, The frame bracket (1) includes two first support rods (101) and two second support rods (102). The two first support rods (101) are respectively fixedly connected to both ends of the support plate (2). Connecting blocks (103) are fixedly connected to both ends of the first support rod (101). The two second support rods (102) are symmetrically arranged with the center line of the first support rod (101) as the axis of symmetry, and both ends of the second support rod (102) are respectively fixedly connected to the two connecting blocks (103), so that the first support rod (101) and the second support rod (102) are connected end to end to form a rectangular frame structure.

3. The aircraft fuselage according to claim 2, characterized in that, The two frame brackets (1) are symmetrically arranged with the center line of the support plate (2) as the axis of symmetry. One end of the two coaxially arranged connecting blocks (103) opposite to each other is used for installing a motor and a propeller, and landing cones (104) are installed at the opposite ends.

4. The aircraft frame according to claim 2, wherein, The first support rod (101), the second support rod (102), the support plate (2), and the reinforcing shaft (3) are all made of carbon fiber reinforced composite materials. The first support rod (101) is rod-shaped, the second support rod (102) is tubular, a sleeve (105) is fixedly connected to the connecting block (103), the sleeve (105) is sleeved on the second support rod (102), and the end of the second support rod (102) penetrates through the sleeve (105) and is provided with a through hole for wire routing.

5. The aircraft frame according to claim 1, characterized in that, A plurality of mounting holes (201) are formed on the support plate (2). An installation frame (204) is installed through bolts in the mounting holes (201). The installation frame (204) includes a vertical plate (2041) and a horizontal plate (2042) formed on the vertical plate (2041). A hole perpendicular to the mounting hole (201) is formed on the horizontal plate (2042) for installing a support plate (205).

6. The aircraft fuselage according to claim 5, characterized in that, A buffer block (2043) is fixedly connected to the position where the hole is formed on the vertical plate (2041). The buffer block (2043) is made of a flexible material. A plurality of weight reduction holes (202) and a plurality of buffer holes (203) are formed on the support plate (2). The buffer holes (203) are used for installing buffer pads.

7. The aircraft fuselage according to claim 1, characterized in that, The reinforcing shaft (3) is a hollow shaft, and wire routing openings (301) are formed at both ends and the middle position of the reinforcing shaft (3) to facilitate the entry and exit of wires.

8. The aircraft frame according to claim 1, characterized in that, The connecting component (4) includes a first connecting sleeve (401). One end of the first connecting sleeve (401) is sleeved on one end of the reinforcing shaft (3) and locked through bolts. A through hole is formed at the other end of the first connecting sleeve (401). Two second connecting pipes (403) are fixedly connected to the circumferential side of the first connecting sleeve (401) through a connecting frame (402). The two second connecting pipes (403) are respectively sleeved on the middle positions of the two second support rods (102).

9. The aircraft frame according to claim 8, characterized in that, The second support rod (102) is in a straight shape or a V shape, and the shape of the second connecting pipe (403) is adapted to the shape of the second support rod (102).

10. The aircraft fuselage according to claim 1, characterized in that, Two supports (6) are fixedly installed on the reinforcing shaft (3), electric landing gears (7) are installed on both of the two supports (6), and one side of each of the two supports (6) facing each other is fixedly connected to the support plate (2) by bolts.

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