Fuselage frame structure and unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a fuselage frame structure and an unmanned aerial vehicle. The fuselage frame structure comprises a frame body, the frame body is of a square frame structure, four mounting pieces are mounted at the four corners of the frame body, the ends, away from the frame body, of the four mounting pieces are detachably connected with fuselage arm assemblies, and power assemblies are mounted on the four fuselage arm assemblies correspondingly. Compared with a fuselage in the prior art, the fuselage frame structure provided by the utility model comprises the frame body and the mounting pieces mounted at the four corners of the frame body, so that the strength of the fuselage frame structure is greatly improved, the bending strength and the torsional strength of the fuselage structure are higher, and the flight stability of the unmanned aerial vehicle is enhanced; meanwhile, the mounting piece is detachably connected with the arm assembly, when the arm assembly is damaged, the arm assembly can be quickly disassembled and independently maintained, and the maintenance cost is greatly reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and in particular to a fuselage frame structure and an unmanned aerial vehicle. Background Art

[0002] The power motor in the current technology is connected to the drone body through the arm, and then transmits power to the drone. While the power motor provides power to the drone, it also introduces vibration. The existing fuselage frame structure is not strong enough, which can easily cause the drone to become unstable and explode, thereby affecting the flight safety of the drone.

[0003] When the drone explodes, the arm assembly is the main stress point, so it receives the greatest impact and has the highest damage rate. Since the arm assembly in the current technology is directly connected to the fuselage frame, when the arm assembly is damaged, the arm assembly can only be replaced together with the drone fuselage frame, which greatly increases the maintenance cost.

[0004] The information disclosed in this background technology section is only intended to increase the understanding of the overall background of the utility model, and should not be regarded as acknowledging or suggesting in any form that the information constitutes the prior art already known to ordinary technicians in this field. Utility Model Content

[0005] The purpose of the utility model is to overcome the deficiencies in the prior art and to provide a fuselage frame structure and a UAV, so as to solve the technical problems existing in the related art that the fuselage frame structure is insufficient in strength and the arm assembly can only be replaced as a whole with the fuselage frame after being damaged.

[0006] In order to solve the above technical problems, the utility model is implemented by adopting the following technical solutions:

[0007] On the one hand, the utility model provides a fuselage frame structure, including a frame body, which is a square frame structure, and four mounting parts are installed at its four corners. The four mounting parts are detachably connected to an arm assembly at one end away from the frame body, and power assemblies are respectively installed on the four arm assemblies.

[0008] Furthermore, the frame body and the four mounting parts are integrally formed.

[0009] Furthermore, one end of the four mounting parts is detachably connected to the frame body, and the other end is detachably connected to the four arm assemblies.

[0010] Furthermore, the frame body includes a first supporting member and a second supporting member that are arranged opposite to each other, and a first connecting member and a second connecting member are respectively connected to both ends of the first supporting member and the second supporting member. The first connecting member and the second connecting member are also arranged opposite to each other, and a cavity for accommodating the body is formed between the first supporting member, the first connecting member, the second supporting member and the second connecting member.

[0011] Furthermore, the four mounting members are respectively clamped between the first support member and the first connecting member, the first connecting member and the second support member, the second support member and the second connecting member, and the second connecting member and the first support member.

[0012] Furthermore, batteries are suspended outside the first support member and the second support member.

[0013] Furthermore, a landing gear connecting piece is installed at the bottom of each of the four mounting pieces, and a landing gear is installed at the bottom of each of the four landing gear connecting pieces.

[0014] Furthermore, a first half sleeve is provided at one end of the four mounting parts away from the frame body, and a second half sleeve adapted to the first half sleeve is provided at one end of the four arm assemblies close to the four mounting parts, wherein the adjacent first half sleeve and the second half sleeve can form a complete sleeve.

[0015] Furthermore, the four arm assemblies are all movably sleeved with sleeves, the four sleeves are all provided with external threads, and the inner walls of the four sleeves are all provided with internal threads matching the four sleeves.

[0016] On the other hand, the utility model provides a drone, comprising the above-mentioned fuselage frame structure.

[0017] Compared with the prior art, the utility model has the following beneficial effects:

[0018] Compared with the fuselage in the prior art, the fuselage frame structure provided by the utility model includes a frame body and mounting parts installed at the four corners of the frame body, which greatly improves the strength of the fuselage frame structure, makes the fuselage structure more resistant to bending and torsion, and enhances the flight stability of the UAV; at the same time, the mounting parts are detachably connected to the arm assembly. When the arm assembly is damaged, the arm assembly can be quickly removed and repaired separately, which greatly reduces the maintenance cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a structural schematic diagram of the fuselage frame structure provided by an embodiment of the utility model;

[0020] Figure 2 is a top view of the drone provided by an embodiment of the utility model;

[0021] Figure 3 It is a schematic diagram of the structure of the drone provided by the embodiment of the utility model;

[0022] Figure 4 It is a schematic diagram of the structure of the sleeve and the casing provided in the embodiment of the utility model;

[0023] Figure 5 It is a structural schematic diagram of the fuselage frame structure provided by an embodiment of the utility model;

[0024] In the figure: 1: frame body; 2: mounting member; 3: arm assembly; 4: power assembly; 5: battery; 6: landing gear connecting member; 7: landing gear; 8: first half sleeve; 9: second half sleeve; 10: sleeve; 11: first support member; 12: second support member; 13: first connecting member; 14: second connecting member. DETAILED DESCRIPTION

[0025] The utility model is further described below in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the utility model, and cannot be used to limit the protection scope of the utility model.

[0026] In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present utility model 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 therefore cannot be understood as a limitation on the present utility model. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present utility model, unless otherwise specified, "multiple" means two or more.

[0027] Embodiment 1:

[0028] like Figure 1 and Figure 2 As shown, this embodiment provides a fuselage frame structure, including a frame body 1, wherein the frame body 1 is a square frame structure, and four mounting parts 2 are installed at its four corners, and one end of the four mounting parts 2 away from the frame body 1 is detachably connected to an arm assembly 3, and the four arm assemblies 3 are respectively installed with power assemblies 4.

[0029] In this embodiment, the frame body 1 and the four mounting parts 2 are integrally formed.

[0030] Specifically, one end of the four mounting parts 2 is mounted on the frame body 1, and the other end is detachably connected to the four arm assemblies 3. In this embodiment, the frame body 1 and the four mounting parts 2 mounted at the four corners of the frame body 1 are used as an integral component, which greatly improves the strength of the fuselage frame structure, makes the fuselage structure more resistant to bending and torsion, and enhances the flight stability of the UAV.

[0031] When the aircraft explodes, since the arm assembly 3 is the component that is mainly impacted, the arm assembly 3 and the power assembly 4 thereon have a high damage rate. Therefore, the mounting member 2 and the arm assembly 3 in this embodiment adopt a detachable connection structure. When the arm assembly 3 is damaged, only the damaged single arm assembly 3 can be replaced, which greatly reduces the maintenance cost.

[0032] In this embodiment, a landing gear connecting member 6 is installed at the bottom of the four mounting members 2, and a landing gear 7 is installed at the bottom of the four landing gear connecting members 6.

[0033] In this embodiment, the four mounting parts 2 are each provided with a first half sleeve 8 at one end away from the frame body 1, and the four arm assemblies 3 are each provided with a second half sleeve 9 adapted to the first half sleeve 8 at one end close to the four mounting parts 2, wherein the adjacent first half sleeve 8 and the second half sleeve 9 can form a complete sleeve.

[0034] In this embodiment, sleeves 10 are movably sleeved on the four arm assemblies 3, external threads are arranged on the four sleeves, and internal threads matching the four sleeves are opened on the inner walls of the four sleeves 10.

[0035] Specifically, the sleeve 10 is a hollow structure with an internal thread formed inside. The first half-sleeve and the second half-sleeve have external threads matched with the internal threads on their outer walls. When the arm assembly 3 needs to be fixedly connected to the mounting member 2, the sleeve 10 can be moved until it is threaded and locked with the sleeve composed of the first half-sleeve 8 and the second half-sleeve 9. Similarly, when the damaged arm assembly 3 needs to be removed, the sleeve 10 can be moved backward until the first half-sleeve 8 and the second half-sleeve 9 are separated, so that the arm assembly 3 can be quickly removed.

[0036] Embodiment 2:

[0037] Different from the first embodiment, the fuselage frame structure provided in this embodiment includes a frame body 1 and four mounting parts 2, one end of the four mounting parts 2 is detachably connected to the frame body 1, and the other end is detachably connected to the four arm assemblies 3.

[0038] Specifically, the frame body 1 includes a first support member 11 and a second support member 12 that are relatively arranged, and the first support member 11 and the second support member 12 are respectively connected to the first connecting member 13 and the second connecting member 14 at both ends, the first connecting member 13 and the second connecting member 14 are also relatively arranged, and a cavity for accommodating the body is formed between the first support member 11, the first connecting member 13, the second support member 12 and the second connecting member 14.

[0039] Specifically, the UAV body is disposed on the frame body 1 , and more specifically, the UAV body is disposed in a receiving cavity surrounded by the first supporting member 11 , the first connecting member 13 , the second supporting member 12 and the second connecting member 14 .

[0040] In this embodiment, the four mounting members 2 are respectively clamped between the first support member 11 and the first connecting member 13, the first connecting member 13 and the second support member 12, the second support member 12 and the second connecting member 14, and the second connecting member 14 and the first support member 11.

[0041] In this embodiment, batteries 5 are suspended on the outside of the first support member 11 and the second support member 12. Compared with the prior art in which the batteries 5 are arranged on the inside of the first support member 11 and the second support member 12, this outer side suspension method makes it more convenient and quick to take out the batteries 5, and there is no need to worry about the deformation and damage of the frame body 1 making it impossible to take out the batteries 5.

[0042] Specifically, one end of the mounting member 2 provided in the present embodiment is detachably connected to the frame body 1, and the other end is detachably connected to the arm assembly 3. Regardless of whether the frame body 1, the mounting member 2, or the arm assembly 3 is damaged, the damaged parts can be removed separately for repair and replacement, which greatly saves costs.

[0043] Embodiment three:

[0044] This embodiment provides a drone, comprising the fuselage frame structure described in any one of Embodiments 1 and 2.

[0045] Compared with the prior art, the fuselage frame structure in this embodiment has higher bending and torsional strength, and the UAV has good flight stability. At the same time, the mounting part 2 and the arm assembly 3 are detachably connected. When the arm assembly 3 is damaged, the arm assembly 3 can be quickly removed and repaired separately, which greatly reduces the maintenance cost.

[0046] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" 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 a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

Claims

1. A fuselage frame structure, characterized in that: The invention comprises a frame body (1), wherein the frame body (1) is a square frame structure, and four mounting parts (2) are mounted at its four corners, and one end of the four mounting parts (2) away from the frame body (1) is detachably connected to an arm assembly (3), and the four arm assemblies (3) are respectively mounted with power assemblies (4).

2. The fuselage frame structure according to claim 1, characterized in that: The frame body (1) and the four mounting parts (2) are integrally formed.

3. The fuselage frame structure according to claim 1, characterized in that: One end of the four mounting parts (2) is detachably connected to the frame body (1), and the other end is detachably connected to the four machine arm assemblies (3).

4. The fuselage frame structure according to claim 3, characterized in that: The frame body (1) comprises a first support member (11) and a second support member (12) which are arranged opposite to each other, the first support member (11) and the second support member (12) are respectively connected to two ends of a first connecting member (13) and a second connecting member (14), the first connecting member (13) and the second connecting member (14) are also arranged opposite to each other, and a cavity for accommodating the body is formed between the first support member (11), the first connecting member (13), the second support member (12) and the second connecting member (14).

5. The fuselage frame structure according to claim 4, characterized in that: The four mounting members (2) are respectively clamped between the first support member (11) and the first connecting member (13), the first connecting member (13) and the second support member (12), the second support member (12) and the second connecting member (14), and the second connecting member (14) and the first support member (11).

6. The fuselage frame structure according to claim 5, characterized in that: Batteries (5) are suspended on the outside of the first support member (11) and the second support member (12).

7. The fuselage frame structure according to claim 1, characterized in that: A landing gear connecting member (6) is installed at the bottom of each of the four mounting members (2), and a landing gear (7) is installed at the bottom of each of the four landing gear connecting members (6).

8. The fuselage frame structure according to claim 1, characterized in that: A first half sleeve (8) is disposed at one end of each of the four mounting parts (2) away from the frame body (1), and a second half sleeve (9) adapted to the first half sleeve (8) is disposed at one end of each of the four arm assemblies (3) close to the four mounting parts (2), wherein adjacent first half sleeves (8) and second half sleeves (9) can form a complete sleeve.

9. The fuselage frame structure according to claim 8, characterized in that: The four arm assemblies (3) are all movably sleeved with sleeves (10), the four sleeves are all provided with external threads, and the inner walls of the four sleeves (10) are all provided with internal threads matching the four sleeves.

10. A drone, characterized in that: The invention comprises the fuselage frame structure according to any one of claims 1 to 9.

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