Aircraft power assembly and aircraft

Abstract

According to the aircraft power assembly and the aircraft, a heat dissipation window is arranged on the bottom face of a lower shell, heat dissipation fins and an electronic speed regulator are fixed in a surface-mounted mode, the heat dissipation fins can be led out of the heat dissipation window, the lower shell and an upper shell are spliced and matched, and the heat dissipation fins and the electronic speed regulator can be fixed in an installation space of the lower shell and the upper shell. And the heat dissipation fins are kept to be led out, so that the heat dissipation effect of the electronic speed regulator can be ensured. According to the aircraft power assembly and the aircraft, the radiating fins and the shell are arranged separately, the radiating fins can be replaced synchronously when the electronic speed regulator is replaced, the modularization degree is improved, and the expansibility of the aircraft power assembly is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to an aircraft power assembly and an aircraft. Background Art

[0002] At present, the power module of a rotor unmanned aerial vehicle mainly consists of a motor, an electronic speed controller and rotor blades. The power module needs to be fixedly installed on the fuselage and the arm of the unmanned aerial vehicle to drive the fuselage.

[0003] To improve the scope of application, some manufacturers will modularize the power module so that different motors, rotor blades, etc. can be selected and replaced according to different usage requirements. Among them, when replacing the motor, different electronic speed controllers also need to be selected according to the motor. After selecting different motors and electronic speed controllers, the heat dissipation requirements of the electronic speed controller will also change. In the prior art, its heat dissipation structure is set on the outer shell, and the replacement is difficult, which will limit the selectable range of its motor and electronic speed controller and is not conducive to the realization of the modular expansion ability. Summary of the Utility Model

[0004] Based on this, the purpose of the utility model is to provide an aircraft power assembly and an aircraft to solve the problems that the modular design of the power assembly of an unmanned aerial vehicle in the prior art is easily limited by the heat dissipation capacity and the expandable performance is insufficient.

[0005] On the one hand, the utility model provides an aircraft power assembly, including: an upper shell, a lower shell, an electronic speed controller, and heat dissipation fins. Among them,

[0006] The upper shell and the lower shell are spliced and matched up and down to form an installation space therebetween. The electronic speed controller is arranged in the installation space, and an arm docking structure is arranged on the first side of the installation space;

[0007] A motor mounting seat is arranged on the upper surface of the upper shell, and a heat dissipation window is arranged on the bottom surface of the lower shell. The setting position of the electronic speed controller corresponds to the setting position of the heat dissipation window;

[0008] The heat dissipation fins are fixedly attached to the electronic speed controller and are led out through the heat dissipation window.

[0009] Optionally, the upper shell and the lower shell also extend towards the first side and are open at the ends to form the arm docking structure.

[0010] Optionally, the arm docking structure is duckbill-shaped and is respectively composed of the upper shell and the lower shell up and down. An annular groove is arranged on the inner wall of the arm docking structure.

[0011] Optionally, reinforcing ribs are also arranged on the outer wall of the arm docking structure.

[0012] Optionally, a guiding groove is provided on the peripheral side of the heat dissipation opening window of the lower housing, and the extending direction of the guiding groove is the same as that of the heat dissipation channel of the heat dissipation fins.

[0013] Optionally, a navigation light opening window is provided on the second side of the installation space, and the second side is the opposite side of the first side.

[0014] Optionally, a banana plug is provided on the electronic speed controller, and the banana plug is arranged on the side close to the navigation light opening window, and the banana plug is used as a welding joint for the motor wire.

[0015] Optionally, a motor wire guiding hole is provided in the motor mounting seat, and the motor wire guiding hole is arranged on the side of the motor mounting seat away from the navigation light opening window.

[0016] The present utility model further provides an aircraft, which includes the above-mentioned aircraft power assembly.

[0017] Optionally, a thermal grease is provided between the electronic speed controller and the heat dissipation fins.

[0018] The aircraft power assembly provided by the present utility model is provided with a heat dissipation opening window on the bottom surface of the lower housing. The heat dissipation fins are fixedly attached to the electronic speed controller. The heat dissipation fins can be led out through the heat dissipation opening window. The lower housing is spliced and matched with the upper housing, and the heat dissipation fins and the electronic speed controller can be fixed in the installation space therein, and the leading-out of the heat dissipation fins can be maintained, so as to ensure the heat dissipation effect of the electronic speed controller. The aircraft power assembly of the present utility model separates the heat dissipation fins from the housing. When replacing the electronic speed controller, the heat dissipation fins can be replaced synchronously, improving the modularization degree and the expandability of the aircraft power assembly.

[0019] The aircraft provided by the present utility model includes the above-mentioned aircraft power assembly, and its heat dissipation fins are separated from the housing. When replacing the electronic speed controller, the heat dissipation fins can be replaced synchronously, improving the modularization degree and the expandability of the aircraft power assembly. Description of the Drawings

[0020] Figure 1 It is a schematic diagram of the module architecture of the aircraft power assembly in the present utility model;

[0021] Figure 2 It is a three-dimensional structure schematic diagram of the aircraft power assembly in the installed state in the present utility model;

[0022] Figure 3 It is a bottom surface structure schematic diagram of the aircraft power assembly in the installed state in the present utility model.

[0023] Description of the reference numerals: 10 - upper housing, 20 - lower housing, 30 - electronic speed governor, 40 - heat dissipation fins, 50 - motor, 51 - motor wires, 31 - banana plug, 60 - navigation light lamp shade, 21 - guiding groove, 22 - expansion port, 11 - reinforcing rib, 201 - annular groove.

[0024] The following specific embodiments will further illustrate the present invention in conjunction with the above-mentioned drawings. Specific embodiments

[0025] For the convenience of understanding the present invention, the present invention will be described more comprehensively below with reference to the relevant drawings. Several embodiments of the present invention are given in the drawings. However, the present invention can be implemented in many different forms and is not limited to the embodiments described herein. On the contrary, these embodiments are provided so that the disclosure of the present invention is more thorough and comprehensive.

[0026] It should be noted that when an element is referred to as being "fixedly provided on" another element, it can be directly on the other element or there can also be an intermediate element. When an element is considered to be "connected" to another element, it can be directly connected to the other element or there may be an intermediate element at the same time. The terms "vertical", "horizontal", "left", "right" and similar expressions used herein are for illustrative purposes only.

[0027] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those of ordinary skill in the technical field to which the present invention belongs. The terms used herein in the description of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "and / or" used herein includes any and all combinations of one or more of the related listed items.

[0028] To solve the problems in the prior art that the modular design of the power components of the unmanned aerial vehicle is easily limited by the heat dissipation capacity and the expandability is insufficient. The present invention provides a power component for an aircraft, which is provided with a heat dissipation opening on the bottom surface of the lower housing, the heat dissipation fins are fixedly attached to the electronic speed governor, the heat dissipation fins can be led out through the heat dissipation opening, the lower housing is spliced and matched with the upper housing, and the heat dissipation fins and the electronic speed governor can be fixed in the installation space therein, and the leading out of the heat dissipation fins is maintained, which can ensure the heat dissipation effect of the electronic speed governor. The heat dissipation fins are separated from the housing, and when the electronic speed governor is replaced, the heat dissipation fins can be replaced synchronously, improving the modular degree and the expandability of the power component of the aircraft.

[0029] Specifically, please refer to Figure 1 、 Figure 2 and Figure 3, in the aircraft power assembly of this embodiment, it includes: an upper housing 10, a lower housing 20, an electronic speed controller 30, and heat dissipation fins 40. The components are in a vertical structure, which is convenient for assembly.

[0030] The upper housing 10 and the lower housing 20 are spliced and matched up and down, and can be fixedly connected by screws to form an installation space therebetween. The electronic speed controller 30 can be enclosed in this installation space. An arm docking structure is provided on the first side of the installation space to fixedly connect the power assembly to the fuselage arm.

[0031] On the upper surface of the upper housing 10, there is a motor 50 mounting seat. On the bottom surface of the lower housing 20, there is a heat dissipation window. The setting position of the electronic speed controller 30 corresponds to the setting position of the heat dissipation window. During assembly, the heat dissipation fins 40 are fixedly attached to the electronic speed controller 30 and can be led out through the heat dissipation window to ensure the contact between the heat dissipation fins 40 and the external medium, and the heat dissipated by the electronic speed controller 30 is conducted to the external medium.

[0032] The lower housing 20 can also be used for the installation and positioning of the heat dissipation fins 40 and the electronic speed controller 30. On the inner surface of the lower housing 20, mounting seats corresponding to the heat dissipation fins 40 and the electronic speed controller 30 can be provided. The heat dissipation fins 40 and the electronic speed controller 30 are successively placed on the lower housing 20, and then the upper housing 10 is installed. The heat dissipation fins 40 and the electronic speed controller 30 are fixed in the installation space by the clamping of the upper housing 10 and the lower housing 20. Or the heat dissipation fins 40 and the electronic speed controller 30 are fixedly connected in advance and then installed into the lower housing 20 together.

[0033] To ensure the consistency of the housing, in this embodiment, the upper housing 10 and the lower housing 20 also extend towards the first side and have an open end to form an arm docking structure, so as to ensure that the arm docking structure and the upper housing 10 and the lower housing 20 are an integral structure, which can ensure its structural strength and reduce the complexity of the docking design at the same time.

[0034] To facilitate the docking with the arm, in this embodiment, the arm docking structure is duckbill-shaped and is respectively composed of the upper housing 10 and the lower housing 20 up and down. An annular groove 201 is provided on the inner wall of the arm docking structure, and bolt mounting holes are provided on the side. After docking with the arm, bolts are inserted through the bolt mounting holes, and the bolts are tightened to pre-tightly fix the duckbill-shaped arm docking structure on the arm. The annular groove 201 can increase the friction with the arm and improve the connection stability. When the bolt is not tightened, the duckbill-shaped arm docking structure is in an open state, which is convenient for the arm to be inserted. Among them, the distance between the upper and lower parts of the duckbill-shaped arm docking structure can be adaptively designed according to the structural strength of the housing, the size of the arm, etc.

[0035] A partition can be set between the arm docking structure and the installation space. The partition is provided with openings for wiring, while ensuring the dustproof effect and reducing the risk of dust entering the installation space through the side gaps of the duckbill-shaped arm docking structure and affecting the performance of the electronic speed controller 30.

[0036] To improve the strength of the arm docking structure, in this embodiment, reinforcing ribs 11 are further provided on the outer wall of the arm docking structure. The extending direction of the reinforcing ribs 11 is consistent with the extending direction of the arm docking structure and perpendicular to the annular groove 201 on the inner wall, which can ensure the wall thickness of each part of the arm docking structure, effectively improve the structural strength of the arm docking structure, and ensure the reliability of docking with the arm. Generally speaking, the reinforcing ribs 11 can be provided on both the upper shell 10 and the lower shell 20.

[0037] To reduce the blockage of the lower shell 20 to the heat dissipation fins 40 and ensure the heat dissipation effect, in this embodiment, a guiding groove 21 is provided on the periphery of the heat dissipation window of the lower shell 20, and the extending direction of the guiding groove 21 is consistent with the extending direction of the heat dissipation channels of the heat dissipation fins 40. In this embodiment, to facilitate the installation of the heat dissipation fins 40, its structure includes a main board and a plurality of fins extending upright from the main board. The main board is mounted and matched with the electronic speed controller 30, and the fins are arranged in an array to form multiple heat dissipation channels. The heat dissipation air flow circulates along the heat dissipation channels, and the guiding groove 21 extends to the bottom of the heat dissipation channels to ensure that the circulation area of the heat dissipation air flow can cover as much as possible the entire outer surface of the heat dissipation fins 40 and ensure the heat dissipation effect.

[0038] An expansion port 22 is also provided at the middle position of the bottom of the lower shell 20, which can be used as an exhaust port inside the installation space and can also be used for the installation of expansion components such as radars and vision sensors. Around the expansion port 22, screw holes are also provided to increase the connection stability between the upper shell 10 and the lower shell 20, and reinforcing ribs are also provided around the screw holes in the middle to ensure the structural strength of the screw holes, while reducing the wall thickness of the shell and the weight.

[0039] To facilitate the setting of the navigation lights, in this embodiment, a navigation light window is provided on the second side of the installation space. The second side is the opposite side of the first side, so as to set a navigation light cover 60 at the position of the navigation light window, and the navigation light window is jointly formed by the upper shell 10 and the lower shell 20 and can be fixed as the upper shell 10 and the lower shell 20 are docked.

[0040] To facilitate wiring, in this embodiment, a banana plug 31 is provided on the electronic speed controller 30, and the banana plug 31 is provided on the side close to the navigation light window. The banana plug 31 is used as the welding joint of the motor wire 51 and can also be used for the fixation of the navigation lights and the navigation light wiring.

[0041] For the convenience of welding operation, in this embodiment, a motor wire guiding hole is provided in the motor mounting base. The motor wire guiding hole is arranged on the side of the motor mounting base away from the navigation light opening window. Thus, when welding the motor wire, the position of the motor wire at the banana plug 31 can be biased inward, reducing the obstruction of the motor wire to the welding operation and ensuring the convenience of the welding operation.

[0042] The present utility model also provides an aircraft, which includes the above-mentioned aircraft power assembly. Its heat dissipation fins 40 can be synchronously replaced following the replacement of the motor 50 and the electronic speed controller 30, so as to select the best heat dissipation fins 40 to adapt to different heat dissipation requirements and improve the modular expandability of the power assembly.

[0043] To ensure the heat dissipation effect, a thermal grease is provided between the electronic speed controller 30 and the heat dissipation fins 40 to improve the heat dissipation speed and facilitate the flexible replacement of the thermal grease when its service life is exhausted.

[0044] The aircraft power assembly and the aircraft provided by the present utility model are provided with heat dissipation openings on the bottom surface of the lower housing. The heat dissipation fins are fixedly attached to the electronic speed controller. The heat dissipation fins can be led out through the heat dissipation openings. The lower housing is spliced and matched with the upper housing, and the heat dissipation fins and the electronic speed controller can be fixed in the installation space therein, while keeping the heat dissipation fins led out, which can ensure the heat dissipation effect of the electronic speed controller. Separating the heat dissipation fins from the housing can synchronously replace the heat dissipation fins when replacing the electronic speed controller, improving the modular degree and the expandability of the aircraft power assembly.

[0045] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present utility model. 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 can be combined in a suitable manner in any one or more embodiments or examples.

[0046] The above-described embodiments merely represent several specific implementation manners of the present utility model. The description is relatively specific and detailed, but it should not be construed as a limitation on the scope of the patent of the present utility model. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present utility model, several modifications and improvements can still be made, and these all belong to the protection scope of the present utility model. Therefore, the protection scope of the patent of the present utility model shall be subject to the appended claims.

Claims

1. An aircraft power assembly, characterized in that: include: Upper housing, lower housing, electronic speed regulator, heat sink fins, among which, The upper housing and the lower housing are spliced ​​and matched up and down to form an installation space therebetween, the electronic speed regulator is arranged in the installation space, and an organic arm docking structure is arranged on a first side of the installation space; The upper surface of the upper shell is provided with a motor mounting seat, the bottom surface of the lower shell is provided with a heat dissipation window, and the setting position of the electronic speed regulator corresponds to the setting position of the heat dissipation window; The heat dissipation fins are mounted and fixed to the electronic speed regulator and are led out from the heat dissipation window.

2. The aircraft power assembly according to claim 1, characterized in that: The upper shell and the lower shell are further extended toward the first side, and the ends are open to form the machine arm docking structure.

3. The aircraft power assembly according to claim 2, characterized in that: The arm docking structure is of duckbill type, and the upper and lower parts are respectively composed of the upper shell and the lower shell, and the inner wall of the arm docking structure is provided with an annular groove.

4. The aircraft power assembly according to claim 3, characterized in that: The outer wall of the arm docking structure is also provided with reinforcing ribs.

5. The aircraft power assembly according to claim 1, characterized in that: A guide groove is arranged around the heat dissipation window of the lower shell, and an extension direction of the guide groove is consistent with an extension direction of the heat dissipation channel of the heat dissipation fin.

6. The aircraft power assembly according to claim 1, characterized in that: A navigation light window is provided on the second side of the installation space, and the second side is an opposite side to the first side.

7. The aircraft power assembly according to claim 6, characterized in that: The electronic speed regulator is provided with a banana plug, and the banana plug is arranged on a side close to the navigation light window, and the banana plug is used as a welding joint of the motor line.

8. The aircraft power assembly according to claim 7, characterized in that: A motor wire guide hole is arranged in the motor mounting seat, and the motor wire guide hole is arranged on a side of the motor mounting seat away from the navigation light window.

9. An aircraft, characterized in that: An aircraft power assembly comprising any one of claims 1 to 8.

10. The aircraft according to claim 9, characterized in that Thermal conductive silicone grease is arranged between the electronic speed regulator and the heat dissipation fins.

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