Topological fuselage of unmanned aerial vehicle and unmanned aerial vehicle
Through the integrated molding of all carbon fiber composite drone topological fuselage structure, the problem of insufficient strength and stability of the existing drone fuselage is solved, and higher fuselage strength and stability are achieved, suitable for carrying heavy goods. and application of limited space.
Patent Information
- Application Number
- CN202411584965.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-07
- Publication Date
- 2025-01-17
AI Technical Summary
The strength and stability of the existing drone fuselage are low, and they cannot effectively carry cargo or equipment, which affects flight performance.
A drone topological body is designed, using a fully carbon fiber composite material to form the body and arm assembly. By strengthening the strength of the connecting arm and arm, and improving the consistency of the center and center of gravity of the fuselage through a symmetrical connection arm assembly. Ensure uniform lift.
It effectively improves the strength and stability of the drone fuselage, can maintain stable flight when some propellers fail, and is suitable for carrying heavier cargo or equipment, and is laid out in a limited space.
Smart Images
Figure CN119319942A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to an unmanned aerial vehicle topological fuselage and an unmanned aerial vehicle. Background Art
[0002] Drones mainly use radio remote control equipment or onboard computers to achieve autonomous flight. Compared with manned aircraft, drones have strong environmental adaptability, simple control, and low cost. They can be widely used in power inspection, agriculture, plant protection, express delivery, disaster relief, monitoring infectious diseases, surveying and mapping, etc. At present, the most widely used drones are six-axis drones.
[0003] In the prior art, the fuselage, as a key component of a UAV, plays a very important role in the flight process. Since it has to carry a large amount of cargo or equipment, the fuselage structure strength and stability are required to be high. However, the strength and stability of the existing fuselage are relatively low. Summary of the invention
[0004] The present invention provides a drone topology fuselage and a drone, which are used to solve the defects of low strength and stability of the fuselage in the prior art.
[0005] The present invention provides a drone topology fuselage, comprising: Two frames, the two frames are arranged opposite to each other along a first direction, each frame comprises an integrally formed body and two arm assemblies, the two arm assemblies are symmetrically connected to two sides of the body along a second direction, the arm assembly comprises a machine arm and a connecting arm, and an end of the machine arm away from the machine body is connected to an outer mounting seat; the bodies of the two frames are connected, the connecting arms of the two frames are close to each other, and the arms of the two frames are away from each other; the second direction is perpendicular to the first direction; The connecting assembly includes a first intermediate mounting seat and a second intermediate mounting seat located on both sides of the body along the second direction, the first intermediate mounting seat connecting the connecting arms of the two arm assemblies on the first side of the body along the second direction, and the second intermediate mounting seat connecting the connecting arms of the two arm assemblies on the second side of the body along the second direction.
[0006] According to a drone topology fuselage provided by the present invention, the arm assembly further comprises an arm root portion connected to the fuselage, and the aircraft arm and the connecting arm are connected to the arm root portion; The arm root has a first arc surface and a second arc surface opposite to each other along a third direction, and a cross section of the arm root gradually decreases from an end close to the body to an end away from the body, and the third direction is perpendicular to the first direction and the second direction.
[0007] According to a drone topological fuselage provided by the present invention, the curvature of the first curved surface is greater than the curvature of the second curved surface.
[0008] According to a drone topological fuselage provided by the present invention, the two connecting arms located on the same side of the fuselage along the second direction have a first preset angle.
[0009] According to a drone topological fuselage provided by the present invention, the fuselage arm and the connecting arm have a second preset angle.
[0010] According to a drone topological fuselage provided by the present invention, the fuselage has a first surface and a second surface relative to each other along a third direction, and the first surface and / or the second surface are / is an outwardly convex arc surface.
[0011] According to a drone topological fuselage provided by the present invention, the fuselage and the two arm assemblies are co-cured and formed by using all-carbon fiber composite materials.
[0012] According to a drone topological fuselage provided by the present invention, at least one of the first intermediate mounting seat and the connecting arm and the second intermediate mounting seat and the connecting arm is connected by glue rivets.
[0013] According to a drone topological fuselage provided by the present invention, the frame has a forming opening, and the forming opening is provided with a cover plate.
[0014] According to a drone topological fuselage provided by the present invention, the cross-section of the fuselage arm and / or the connecting arm gradually decreases from an end close to the fuselage to an end away from the fuselage.
[0015] The present invention also provides a drone, comprising any one of the drone topological fuselages described above.
[0016] According to a drone provided by the present invention, at least one of the outer mounting seat, the first middle mounting seat, and the second middle mounting seat is installed with two propellers arranged opposite to each other along a third direction.
[0017] The UAV topological fuselage provided by the present invention is formed in one piece with the fuselage and the arm assembly to strengthen the strength of the connecting arm and the fuselage arm, thereby effectively improving the strength of the fuselage; and the two arm assemblies are symmetrically connected to the two sides of the fuselage and the two frames are symmetrically arranged to ensure that the center of the fuselage is consistent with the center of gravity, so that the mounting seat on the arm assembly provides uniform lift for the UAV, thereby effectively improving stability.
[0018] The drone provided by the present invention has the drone topology body as described above, and therefore also has the various advantages as described above. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.
[0020] Figure 1 This is one of the three-dimensional structural schematic diagrams of the topological fuselage of the unmanned aerial vehicle provided by the present invention.
[0021] Figure 2 This is the second schematic diagram of the three-dimensional structure of the topological fuselage of the drone provided by the present invention.
[0022] Figure 3 It is a schematic diagram of the topological structure of the drone fuselage provided by the present invention.
[0023] Figure 4 It is a schematic diagram of the lateral structure of the topological fuselage of the unmanned aerial vehicle provided by the present invention.
[0024] Figure 5 This is one of the structural schematic diagrams of the rack provided by the present invention.
[0025] Figure 6 This is the second structural schematic diagram of the rack provided by the present invention.
[0026] Figure 7 This is the third structural schematic diagram of the rack provided by the present invention.
[0027] Reference numerals: 100, frame; 110, body; 111, first surface; 112, second surface; 113, molding port; 114, cover plate; 115, wire hole; 101, first frame; 102, second frame; 103, first arm assembly; 104, second arm assembly; 105, third arm assembly; 106, fourth arm assembly; 120, arm assembly; 121, machine arm; 122, connecting arm; 123, arm root; 1231, first arc surface; 1232, second arc surface; 210, first middle mounting seat; 220, second middle mounting seat; 230, outer mounting seat; 240, connecting piece. DETAILED DESCRIPTION
[0028] The following embodiments of the present invention are described in further detail in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.
[0029] In the description of the embodiments of the present invention, it should be noted 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 embodiments of the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limitations on the embodiments of the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.
[0030] In the description of the embodiments of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" 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 an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the embodiments of the present invention can be understood according to specific circumstances.
[0031] In the embodiments of the present invention, unless otherwise clearly specified and limited, the first feature being "above" or "below" the second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, the first feature being "above", "above" and "above" the second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. The first feature being "below", "below" and "below" the second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.
[0032] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the embodiment of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.
[0033] Combine the following Figure 1-Figure 7 Describe the drone topology fuselage of the present invention.
[0034] The embodiment of the first aspect of the present invention provides a drone topology fuselage, such as Figure 1 and Figure 5 As shown, the drone topology fuselage includes two racks 100 and a connection component connecting the two racks 100 .
[0035] Among them, the two racks 100 are arranged opposite to each other along the first direction, each rack 100 includes an integrally formed body 110 and two arm assemblies 120, the two arm assemblies 120 are symmetrically connected to both sides of the body 110 along the second direction, each arm assembly 120 includes an arm 121 and a connecting arm 122, and the end of the arm 121 away from the body 110 is connected to an outer mounting seat 230; the bodies 110 of the two racks 100 are connected, the connecting arms 122 of the two racks 100 are close to each other along the first direction, and the arms 121 of the two racks 100 are away from each other along the first direction; the connecting assembly includes a first intermediate mounting seat 210 and a second intermediate mounting seat 220 located on both sides of the body 110 along the second direction, the first intermediate mounting seat 210 connects the connecting arms 122 of the two arm assemblies 120 on the first side of the body 110 along the second direction, and the second intermediate mounting seat 220 connects the connecting arms 122 of the two arm assemblies 120 on the second side of the body 110 along the second direction.
[0036] For example, Figure 2 and Figure 3 As shown, the first direction is the X direction, and the second direction is the Y direction; the two racks 100 are respectively the first rack 101 and the second rack 102, and the first rack 101 and the second rack 102 are arranged opposite to each other along the X direction; the body 110 of the first rack 101 is the first body 110, and the two arm assemblies 120 of the first rack 101 are respectively the first arm assembly 103 and the second arm assembly 104, and the first arm assembly 103 and the second arm assembly 104 are symmetrically connected to both sides of the first body 110 along the Y direction; the body 110 of the second rack 102 is the second body 110, and the two arm assemblies 120 of the second rack 102 are respectively the third arm assembly 105 and the fourth arm assembly 106, and the first arm assembly 103 and the second arm assembly 104 are symmetrically connected to both sides of the first body 110 along the Y direction. The third arm assembly 105 and the fourth arm assembly 106 are symmetrically connected to both sides of the second body 110 along the Y direction; when the first frame 101 and the second frame 102 are connected, the connecting arm 122 of the first arm assembly 103 and the connecting arm 122 of the third arm assembly 105 are close to each other and connected through the first intermediate mounting seat 210, and the arm 121 of the first arm assembly 103 and the arm 121 of the third arm assembly 105 are far away from each other; and the connecting arm 122 of the second arm assembly 104 and the connecting arm 122 of the fourth arm assembly 106 are close to each other and connected through the second intermediate mounting seat 220, and the arm 121 of the second arm assembly 104 and the arm 121 of the fourth arm assembly 106 are far away from each other.
[0037] It can be understood that the body 110 and the two arm assemblies 120 are integrally formed to strengthen the strength of the connecting arm 122 and the arm 121, the connection strength of the connecting arm 122 and the body 110, and the connection strength of the arm 121 and the body 110, thereby effectively improving the strength of the fuselage.
[0038] One end of each arm 121 away from the body 110 is connected to an outer mounting seat 230, so the four frames 100 have a total of four outer mounting seats 230, the first middle mounting seat 210, the second middle mounting seat 220 and the four outer mounting seats 230 serve as motor seats (mounting seats), and the motor seats are equipped with driving parts, so the motor seats serve as a power system.
[0039] In each frame 100, two arm assemblies 120 are symmetrically connected to both sides of the body 110 along the Y direction; the two frames 100 are symmetrically distributed along the X direction, and the two frames 100 are connected to form a symmetrical structure about the ZY plane and a symmetrical structure about the ZX plane, so that the motor seat is symmetrically distributed in the ZY plane and symmetrically distributed in the ZX plane, thereby ensuring that the center of the fuselage is consistent with the center of gravity, which is convenient for providing uniform lift for the drone and effectively improving stability. It should be noted here that Z can be a third direction perpendicular to the first direction and the second direction.
[0040] The drone topological fuselage provided in the embodiment of the present invention is formed in one piece by the fuselage 110 and the arm assembly 120, thereby strengthening the connection strength between the connecting arm 122 and the arm 121 and effectively improving the strength of the fuselage; and the two arm assemblies 120 are symmetrically connected to the two sides of the fuselage 110 and the two frames 100 are symmetrically arranged to ensure that the center of the fuselage is consistent with the center of gravity, so that the mounting seat on the arm assembly 120 provides uniform lift for the drone, effectively improving stability.
[0041] In one embodiment of the present invention, the two connecting arms 122 located on the same side of the body 110 along the second direction have a first preset angle.
[0042] like Figure 3 As shown, the center line of the connecting arm 122 of the first arm assembly 103 and the center line of the connecting arm 122 of the third arm assembly 105 have a first preset angle α, and the center line of the connecting arm 122 of the second arm assembly 104 and the center line of the connecting arm 122 of the fourth arm assembly 106 also have a first preset angle. When the first frame 101 and the second frame 102 are connected, the first body 110, the connecting arm 122 of the first arm assembly 103, the connecting arm 122 of the third arm assembly 105, the second body 110, the connecting arm 122 of the fourth arm assembly 106, and the connecting arm 122 of the second arm assembly 104 form a polygonal structure to improve the connection strength between the first frame 101 and the second frame 102, thereby improving the fuselage strength and torsion resistance.
[0043] Optionally, the first preset angle α is 125°, and the connecting arm 122 of the first arm assembly 103 and the connecting arm 122 of the third arm assembly 105 are connected to the first intermediate mounting seat 210 at an angle of 125°, thereby enhancing the overall strength and anti-torsion capability based on the polygonal structure reinforcement.
[0044] Optionally, the machine arm 121 and the connecting arm 122 have a second preset angle.
[0045] It is understandable that in each arm assembly 120, the center line of the machine arm 121 and the center line of the connecting arm 122 have a second preset angle. Preferably, the machine arm 121 and the connecting arm 122 are symmetrically arranged along the first direction.
[0046] In this embodiment, Figure 1 and Figure 6 As shown, the arm assembly 120 also includes an arm root 123 connected to the body 110, the arm 121 and the connecting arm 122 are connected to the arm root 123, the connecting arm 122 is arranged obliquely relative to the arm root 123, and the distance between the connecting arm 122 and the body 110 along the second direction gradually increases from the end close to the arm root 123 to the end away from the arm root 123.
[0047] It can be understood that the arm root 123 of the first arm assembly 103, the arm root 123 of the second arm assembly 104, and the first body 110 region connecting the arm root 123 of the first arm assembly 103 and the arm root 123 of the second arm assembly 104 form a first side portion, the connecting arm 122 of the first arm assembly 103 serves as the second side portion, the connecting arm 122 of the third arm assembly 105 serves as the third side portion, the arm root 123 of the third arm assembly 105, the arm root 123 of the fourth arm assembly 106, and the arm root connecting the third arm assembly 105 123 and the second body 110 area of the arm root 123 of the fourth arm assembly 106 form a fourth side portion, the connecting arm 122 of the fourth arm assembly 106 serves as the fifth side portion, and the connecting arm 122 of the second arm assembly 104 serves as the sixth side portion; in this way, after the first frame 101 and the second frame 102 are connected, the first side portion, the second side portion, the third side portion, the fourth side portion, the fifth side portion and the sixth side portion form a hexagonal structure, which effectively improves the connection strength between the first frame 101 and the second frame 102, thereby improving the structural strength and torsional resistance of the fuselage.
[0048] According to an embodiment of the present invention, Figure 1 and Figure 7As shown, the connection assembly further includes a connection member 240, the machine body 110 is a long frame structure arranged along the first direction, when the first frame 101 and the second frame 102 are connected, the first machine body 110 and the second machine body 110 are connected by the connection member 240; the connection member 240 is a connection plate adapted to the cross section of the machine body 110, one end of the connection plate extends into the first machine body 110 and is connected to the first machine body 110, the second end of the connection plate extends into the second machine body 110 and is connected to the second machine body 110, and the first machine body 110 and the second machine body 110 are abutted against each other. For example, the connection member 240 can be an aluminum connection plate.
[0049] In one embodiment of the present invention, Figure 4 and Figure 6 As shown, the arm root 123 has a first arc surface 1231 and a second arc surface 1232 relative to each other along the third direction, and the cross-section of the arm root 123 along the first direction gradually decreases from the end close to the body 110 to the end away from the body 110, and the third direction is perpendicular to the first direction and the second direction.
[0050] It is understandable that if Figure 6 As shown, the third direction can be the height direction of the body 110, then the upper surface and the lower surface of the arm root 123 are both curved surfaces, and the arm root 123 gradually decreases from the body 110 to the arm 121. In this way, the rigidity of the frame 100 is improved by the curvature of the upper surface and the lower surface of the arm root 123.
[0051] Optionally, the first surface 111 of the arm root 123 is a surface close to the ground, and the curvature of the first curved surface 1231 of the arm root 123 close to the ground is greater than the curvature of the second curved surface 1232, thereby improving flight safety and reliability.
[0052] In one embodiment of the present invention, Figure 4 and Figure 6 As shown, the cross section of the machine arm 121 gradually decreases from the end close to the machine body 110 to the end away from the machine body 110, and the machine arm 121 is designed as a rectangular gradient structure, which can not only reduce weight, but also effectively transmit force and enhance the anti-torsion ability. It should be noted that the cross section of the connecting arm 122 can also gradually decrease from the end close to the machine body 110 to the end away from the machine body 110, and the connecting arm 122 is designed as a rectangular gradient structure, which can not only reduce weight, but also effectively transmit force and enhance the anti-torsion ability.
[0053] In this embodiment, Figure 1 and Figure 6As shown, the cross section of the body 110 is rectangular, and the body 110 has a first surface 111 and a second surface 112 relative to each other along the third direction. The first surface 111 and the second surface 112 are convex curved surfaces, and the body 110 is designed with curvatures at the top and bottom to further improve the rigidity of the body.
[0054] Optionally, the motor seats are symmetrically distributed in the ZY plane and symmetrically distributed in the ZX plane, so that the power system is symmetrically arranged corresponding to the fuselage structure, which is convenient for circuit layout and the lines are simpler and clearer.
[0055] For example, the body 110 is a hollow structure with an upper opening, a reinforcing rib plate is provided inside the body 110 , and a wire hole 115 is provided on the body 110 .
[0056] In one embodiment of the present invention, the frame 100 is formed by integrating the body 110 and the two arm assemblies 120 . Specifically, the body 110 and the two arm assemblies 120 are formed by co-curing all carbon fiber composite materials.
[0057] It should be noted that the frame 100 is co-cured and molded with all-carbon fiber composite materials. The frame 100 has high strength and light weight, realizing a lightweight design, reducing the number of parts, and improving assembly efficiency. In addition, general damage can be directly filled with composite materials, and the repair method is convenient without disassembling the fuselage, reducing maintenance costs and time, and improving support efficiency.
[0058] It should be noted that the frame 100 is formed by integrating the body 110 and the two arm assemblies 120 , so that the overall parts of the body are smaller, the difficulty of assembly is reduced, the production efficiency is improved, and maintenance is convenient.
[0059] Optionally, the first intermediate mounting seat 210 and the connecting arm 122 are connected by glue rivets, and the second intermediate mounting seat 220 and the connecting arm 122 are connected by glue rivets. The first intermediate mounting seat 210 and the second intermediate mounting seat 220 are made of carbon fiber.
[0060] Furthermore, the material of the outer mounting seat 230 may also be carbon fiber, and the outer mounting seat 230 and the machine arm 121 are connected by glue rivets.
[0061] In one embodiment of the present invention, Figure 6 As shown, the frame 100 is formed with a molding opening 113 , and the molding opening 113 is provided with a cover plate 114 .
[0062] For example, the frame 100 is formed by integrating a body 110 and two arm assemblies 120 , and a molding opening 113 is formed at the arm root 123 of the arm assembly 120 . In order to ensure the sealing of the inner cavity of the arm assembly 120 , a cover plate 114 is provided at the molding opening 113 of the arm root 123 .
[0063] Optionally, the cover plate 114 and the body 110 may also be connected by glue riveting.
[0064] An embodiment of the second aspect of the present invention provides a drone, comprising a propeller and a drone topological fuselage provided by any of the above embodiments, wherein the propeller is arranged on the drone topological fuselage.
[0065] Specifically, the first middle mounting seat 210, the second middle mounting seat 220 and the outer mounting seats 230 on the four arms 121 are all equipped with propellers; the first middle mounting seat 210, the second middle mounting seat 220 and the outer mounting seats 230 serve as motor seats, and the propellers are driven to rotate through the driving parts on the motor seats to provide vertical lift for the drone.
[0066] Furthermore, at least one of the outer mounting seat 230 , the first middle mounting seat 210 , and the second middle mounting seat 220 is mounted with two propellers that are arranged opposite to each other along the third direction.
[0067] It can be understood that the topological fuselage of the drone ensures sufficient power, the propellers do not interfere with each other, the propellers are symmetrically distributed in the ZY plane, and symmetrically distributed in the ZX plane, thereby ensuring that the center of the fuselage is consistent with the center of gravity and improving the stability of the drone.
[0068] Optionally, the first middle mounting seat 210, the second middle mounting seat 220 and the four outer mounting seats 230 are all equipped with drive shafts, and propellers are installed on the drive shafts. Then the first middle mounting seat 210, the second middle mounting seat 220 and the four outer mounting seats 230 have a total of six drive shafts, and each drive shaft has two propellers arranged at intervals along the third direction. Therefore, the topological fuselage of the drone in this embodiment has six axes and twelve propellers (i.e., six drive shafts and twelve propellers), which can provide strong vertical lift for the drone, allowing the drone to carry heavier cargo or equipment.
[0069] It should be noted that the fuselage strength of the existing drone is relatively low, and each motor seat of the arm 121 can only be equipped with one propeller, so that the drone cannot fly stably when some propellers fail. In this embodiment, the fuselage 110 and the arm assembly 120 are integrally formed, and the motor seats are symmetrically distributed in the ZY plane and the ZX plane, ensuring that the center of the fuselage is consistent with the center of gravity, effectively improving the strength and rigidity of the fuselage, so that the redundant design of multiple propellers can enable the drone to maintain stable flight when some propellers fail, thereby improving the safety and reliability of flight.
[0070] It should be noted that the drone of this embodiment can provide strong vertical lift and can carry heavier cargo or equipment. Under the same power conditions, the size of the drone of this embodiment is smaller, so it is suitable for layout in limited space occasions, such as meeting the size requirements of the fire truck compartment and improving the convenience of vehicle-mounted movement.
[0071] The drone provided by the embodiment of the present invention has the characteristics of small size and weight, and is easy to transport and maintain.
[0072] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims
1. A drone topology fuselage, characterized in that: include: Two frames, the two frames are arranged opposite to each other along a first direction, each frame comprises an integrally formed body and two arm assemblies, the two arm assemblies are symmetrically connected to two sides of the body along a second direction, the arm assembly comprises a machine arm and a connecting arm, and an end of the machine arm away from the machine body is connected to an outer mounting seat; the bodies of the two frames are connected, the connecting arms of the two frames are close to each other, and the arms of the two frames are away from each other; the second direction is perpendicular to the first direction; The connecting assembly includes a first intermediate mounting seat and a second intermediate mounting seat located on both sides of the body along the second direction, the first intermediate mounting seat connecting the connecting arms of the two arm assemblies on the first side of the body along the second direction, and the second intermediate mounting seat connecting the connecting arms of the two arm assemblies on the second side of the body along the second direction.
2. The drone topology fuselage according to claim 1, characterized in that: The arm assembly also includes an arm root portion connected to the machine body, and the machine arm and the connecting arm are connected to the arm root portion; The arm root has a first arc surface and a second arc surface opposite to each other along a third direction, and a cross section of the arm root gradually decreases from an end close to the body to an end away from the body, and the third direction is perpendicular to the first direction and the second direction.
3. The drone topology fuselage according to claim 2, characterized in that: The curvature of the first curved surface is greater than the curvature of the second curved surface.
4. The drone topology fuselage according to any one of claims 1 to 3, characterized in that: The two connecting arms located on the same side of the body along the second direction have a first preset angle, and / or, The machine arm and the connecting arm have a second preset angle.
5. The drone topology fuselage according to any one of claims 1 to 3, characterized in that: The body has a first surface and a second surface opposite to each other along a third direction, and the first surface and / or the second surface is an outwardly convex arc surface.
6. The drone topology fuselage according to any one of claims 1 to 3, characterized in that: The machine body and the two arm assemblies are co-cured and formed by using all-carbon fiber composite materials, and / or, At least one of the first intermediate mounting seat and the connecting arm and the second intermediate mounting seat and the connecting arm is connected by glue rivets.
7. The drone topology fuselage according to claim 1, characterized in that: The frame has a forming opening, and the forming opening is provided with a cover plate.
8. The drone topology fuselage according to any one of claims 1 to 3, characterized in that: The cross section of the machine arm and / or the connecting arm gradually decreases from an end close to the machine body to an end away from the machine body.
9. A drone, characterized in that: Comprising a drone topological fuselage as described in any one of claims 1 to 8.
10. The drone according to claim 9, characterized in that: At least one of the outer mounting seat, the first middle mounting seat, and the second middle mounting seat is mounted with two propellers that are arranged opposite to each other along a third direction.