A high-voltage resistant electronic speed controller for fuel cell drones
By using a combination of silicon carbide MOSFET devices, thermally conductive copper pipes, and heat sink fins, the problems of insufficient voltage withstand capability and poor heat dissipation in traditional electronic speed controllers are solved, thus extending the service life of electronic speed controllers.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- SICHUAN LIGHT GREEN TECH CO LTD
- Filing Date
- 2025-06-06
- Publication Date
- 2026-05-26
AI Technical Summary
The insufficient voltage withstand capability and poor heat dissipation of silicon-based MOSFET devices in traditional electronic speed controllers lead to a reduced lifespan of the electronic speed controller.
Silicon carbide MOSFET devices are used to replace traditional silicon-based MOSFET devices, and thermally conductive copper pipes and heat sink fins are set on the silicon carbide MOSFET devices to conduct heat away by heat transfer between the thermally conductive copper pipes and heat sink fins.
This improves the pressure resistance and heat dissipation capacity of the electronic speed controller, extending its service life.
Smart Images
Figure CN224290450U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a high-voltage resistant electronic speed controller (ESC) for fuel cell UAVs. Background Technology
[0002] Existing hydrogen fuel cell drones use traditional electronic speed controllers to control motor speed. Traditional electronic speed controllers have the following drawbacks: First, the voltage withstand capability of the traditional silicon-based MOSFET devices used on the circuit board is insufficient. The voltage fluctuation range of the fuel cell inside the drone is large, ranging from 30-400V. This voltage causes a breakdown rate of over 30% for traditional silicon-based MOSFET devices, affecting the lifespan of the electronic speed controller. Second, under high-voltage conditions, the temperature rise of traditional electronic speed controllers can reach 85℃. The poor heat dissipation of the traditional silicon-based MOSFET devices within the electronic speed controller further reduces its lifespan. Utility Model Content
[0003] The technical problem to be solved by this utility model is to provide a high-voltage resistant electronic speed controller for fuel cell drones, which solves the technical problem that the silicon-based MOSFET devices used in traditional electronic speed controllers have insufficient voltage withstand capability and poor heat dissipation, resulting in a reduced lifespan of the electronic speed controller.
[0004] To achieve the above objectives, the technical solution adopted by this utility model is as follows:
[0005] A high-voltage resistant electronic speed controller for a fuel cell drone includes a circuit board, a mounting housing, a silicon carbide MOSFET device mounted on the circuit board, a first heat dissipation mechanism disposed on the silicon carbide MOSFET device, and a second heat dissipation mechanism disposed on the mounting housing and in contact with the first heat dissipation mechanism; the circuit board is mounted inside the mounting housing.
[0006] Furthermore, the first heat dissipation mechanism includes a first thermally conductive copper sheet disposed at the bottom of the silicon carbide MOSFET device, a second thermally conductive copper sheet disposed at the top of the silicon carbide MOSFET device, and a plurality of thermally conductive copper pipes disposed on the second thermally conductive copper sheet and respectively in contact with the second heat dissipation mechanism.
[0007] Furthermore, the second heat dissipation mechanism includes a heat-conducting plate disposed inside the mounting housing and in contact with the heat-conducting copper pipe, and a plurality of heat dissipation fins respectively connected to the heat-conducting plate and respectively located outside the mounting housing.
[0008] Furthermore, a heat dissipation groove is formed between two adjacent heat dissipation fins.
[0009] Furthermore, a medium-filled gap is formed between the heat-conducting copper tube and the heat-conducting plate.
[0010] Furthermore, the heat-conducting copper tube is U-shaped.
[0011] Furthermore, the mounting housing includes a housing that connects to an external drone, and a cover attached to the housing; a circuit board is mounted between the housing and the cover; and a second heat dissipation mechanism is located on the cover.
[0012] Furthermore, the housing is provided with a first threaded connecting block, and the cover is provided with a second threaded connecting block that is adapted to the first threaded connecting block. Bolts are internally threadedly connected to the first threaded connecting block and the second threaded connecting block.
[0013] Furthermore, the shell is equipped with a third threaded connection block for connecting to an external drone.
[0014] Furthermore, a wiring inlet and a wiring outlet are formed between the housing and the cover.
[0015] Compared with the prior art, the present invention has the following beneficial effects:
[0016] This utility model has a simple structure, a scientific and reasonable design, and is easy to use. Based on the traditional electronic speed controller circuit board, this utility model uses silicon carbide MOSFET devices to replace traditional silicon-based MOSFET devices. Compared with traditional silicon-based MOSFET devices, silicon carbide MOSFET devices have higher withstand voltage and improve the service life of the electronic speed controller. This utility model has a heat-conducting copper pipe on the silicon carbide MOSFET device and heat dissipation fins on the mounting shell. The heat is conducted from inside the electronic speed controller to the outside by heat transfer between the heat-conducting copper pipe and the heat dissipation fins, which improves the heat dissipation capacity of the silicon carbide MOSFET device and further improves the service life of the electronic speed controller. Attached Figure Description
[0017] Figure 1 This is a three-dimensional assembly drawing of the structure of this utility model.
[0018] Figure 2 This is a schematic diagram after the disassembly of the present invention.
[0019] Figure 3 This is a bottom view of the shell cover.
[0020] Figure 4 This is a schematic diagram showing the medium filling gap located between the heat-conducting copper tube and the heat-conducting plate.
[0021] Figure 5 This is a schematic diagram showing the threaded connection between the first threaded connecting block and the second threaded connecting block.
[0022] The names corresponding to the reference numerals in the attached figures are as follows:
[0023] 1-Mounting shell, 2-Circuit board, 3-Silicon carbide MOSFET device, 4-First thermally conductive copper sheet, 5-Second thermally conductive copper sheet, 6-Temperature conductive copper pipe, 7-Dielectric filling gap, 8-Heat-conducting plate, 9-Heat dissipation fins, 10-Heat dissipation slot, 11-Shell, 12-Shell cover, 14-First threaded connecting block, 15-Second threaded connecting block, 16-Bolt, 17-Third threaded connecting block, 18-Line inlet, 19-Line outlet. Detailed Implementation
[0024] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.
[0025] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.
[0026] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; of course, they can also refer to a mechanical connection or an electrical connection; furthermore, they can refer to a direct connection, an indirect connection through an intermediate medium, or a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.
[0027] Example 1.
[0028] like Figure 1-5 As shown, the present invention provides a high-voltage resistant electronic control device for fuel cell drones, including a circuit board 2, a mounting shell 1, a silicon carbide MOSFET device 3 mounted on the circuit board 2, a first heat dissipation mechanism disposed on the silicon carbide MOSFET device 3, and a second heat dissipation mechanism disposed on the mounting shell 1 and in contact with the first heat dissipation mechanism; the circuit board 2 is mounted inside the mounting shell 1.
[0029] The model number of silicon carbide MOSFET device 3 is C2M0080120D.
[0030] This utility model has a simple structure, a scientific and reasonable design, and is easy to use. Based on the traditional electronic speed controller circuit board, this utility model uses silicon carbide MOSFET devices to replace traditional silicon-based MOSFET devices. Compared with traditional silicon-based MOSFET devices, silicon carbide MOSFET devices have higher withstand voltage and improve the service life of the electronic speed controller. This utility model has a heat-conducting copper pipe on the silicon carbide MOSFET device and heat dissipation fins on the mounting shell. The heat is conducted from inside the electronic speed controller to the outside by heat transfer between the heat-conducting copper pipe and the heat dissipation fins, which improves the heat dissipation capacity of the silicon carbide MOSFET device and further improves the service life of the electronic speed controller.
[0031] Example 2.
[0032] like Figure 1-5 As shown, the present invention provides a high-voltage resistant electronic control device for fuel cell drones, including a circuit board 2, a mounting shell 1, a silicon carbide MOSFET device 3 mounted on the circuit board 2, a first heat dissipation mechanism disposed on the silicon carbide MOSFET device 3, and a second heat dissipation mechanism disposed on the mounting shell 1 and in contact with the first heat dissipation mechanism; the circuit board 2 is mounted inside the mounting shell 1.
[0033] The first heat dissipation mechanism includes a first thermally conductive copper sheet 4 disposed at the bottom of the silicon carbide MOSFET device 3, a second thermally conductive copper sheet 5 disposed at the top of the silicon carbide MOSFET device 3, and a plurality of thermally conductive copper pipes 6 disposed on the second thermally conductive copper sheet 5 and respectively in contact with the second heat dissipation mechanism.
[0034] In this embodiment 2, the first thermally conductive copper sheet 4 and the second thermally conductive copper sheet 5 dissipate heat from the bottom and top of the silicon carbide MOSFET device 3, respectively. The first thermally conductive copper sheet 4 transfers heat from the silicon carbide MOSFET device 3 to the housing 11, and the housing 11 dissipates the heat conducted from the first thermally conductive copper sheet 4 to the outside. The second thermally conductive copper sheet 5 transfers heat from the silicon carbide MOSFET device 3 to the thermally conductive copper pipe 6, and the thermally conductive copper pipe 6 conducts heat to the heat dissipation fins 9, and the heat dissipation fins 9 dissipate the heat to the outside.
[0035] A silicon carbide MOSFET device 3 is disposed throughout the circuit board 2.
[0036] Example 3.
[0037] like Figure 1-5As shown, the present invention provides a high-voltage resistant electronic control device for fuel cell drones, including a circuit board 2, a mounting shell 1, a silicon carbide MOSFET device 3 mounted on the circuit board 2, a first heat dissipation mechanism disposed on the silicon carbide MOSFET device 3, and a second heat dissipation mechanism disposed on the mounting shell 1 and in contact with the first heat dissipation mechanism; the circuit board 2 is mounted inside the mounting shell 1.
[0038] The first heat dissipation mechanism includes a first thermally conductive copper sheet 4 disposed at the bottom of the silicon carbide MOSFET device 3, a second thermally conductive copper sheet 5 disposed at the top of the silicon carbide MOSFET device 3, and a plurality of thermally conductive copper pipes 6 disposed on the second thermally conductive copper sheet 5 and respectively in contact with the second heat dissipation mechanism.
[0039] The second heat dissipation mechanism includes a heat-conducting plate 8 disposed inside the mounting housing 1 and in contact with the heat-conducting copper pipe 6, and a plurality of heat dissipation fins 9 respectively connected to the heat-conducting plate 8 and located outside the mounting housing 1.
[0040] In this embodiment 3, the heat sink 9 transfers heat to the second heat-conducting copper sheet 5 through the heat-conducting plate 8 to dissipate heat from the silicon carbide MOSFET device 3 to the outside. The heat sink 9 and the heat-conducting plate 8 are integrally connected.
[0041] Example 4.
[0042] like Figure 1-5 As shown, the present invention provides a high-voltage resistant electronic control device for fuel cell drones, including a circuit board 2, a mounting shell 1, a silicon carbide MOSFET device 3 mounted on the circuit board 2, a first heat dissipation mechanism disposed on the silicon carbide MOSFET device 3, and a second heat dissipation mechanism disposed on the mounting shell 1 and in contact with the first heat dissipation mechanism; the circuit board 2 is mounted inside the mounting shell 1.
[0043] The first heat dissipation mechanism includes a first thermally conductive copper sheet 4 disposed at the bottom of the silicon carbide MOSFET device 3, a second thermally conductive copper sheet 5 disposed at the top of the silicon carbide MOSFET device 3, and a plurality of thermally conductive copper pipes 6 disposed on the second thermally conductive copper sheet 5 and respectively in contact with the second heat dissipation mechanism.
[0044] The second heat dissipation mechanism includes a heat-conducting plate 8 disposed inside the mounting housing 1 and in contact with the heat-conducting copper pipe 6, and a plurality of heat dissipation fins 9 respectively connected to the heat-conducting plate 8 and located outside the mounting housing 1.
[0045] A heat dissipation slot 10 is formed between two adjacent heat dissipation fins 9.
[0046] In this embodiment 4, a heat dissipation groove 10 is formed between two adjacent heat dissipation fins 9, which facilitates the flow of outside air between the two adjacent heat dissipation fins 9 and improves the heat dissipation efficiency of the heat dissipation fins 9.
[0047] Example 5.
[0048] like Figure 1-5 As shown, the present invention provides a high-voltage resistant electronic control device for fuel cell drones, including a circuit board 2, a mounting shell 1, a silicon carbide MOSFET device 3 mounted on the circuit board 2, a first heat dissipation mechanism disposed on the silicon carbide MOSFET device 3, and a second heat dissipation mechanism disposed on the mounting shell 1 and in contact with the first heat dissipation mechanism; the circuit board 2 is mounted inside the mounting shell 1.
[0049] The first heat dissipation mechanism includes a first thermally conductive copper sheet 4 disposed at the bottom of the silicon carbide MOSFET device 3, a second thermally conductive copper sheet 5 disposed at the top of the silicon carbide MOSFET device 3, and a plurality of thermally conductive copper pipes 6 disposed on the second thermally conductive copper sheet 5 and respectively in contact with the second heat dissipation mechanism.
[0050] The second heat dissipation mechanism includes a heat-conducting plate 8 disposed inside the mounting housing 1 and in contact with the heat-conducting copper pipe 6, and a plurality of heat dissipation fins 9 respectively connected to the heat-conducting plate 8 and located outside the mounting housing 1.
[0051] A medium-filled gap 7 is formed between the heat-conducting copper tube 6 and the heat-conducting plate 8.
[0052] In this embodiment 5, the medium-filling gap 7 is used to fill the heat-conducting medium, such as phase-change thermal grease, to improve the heat transfer efficiency between the heat-conducting copper pipe 6 and the heat-conducting plate 8, thereby improving the overall heat dissipation capacity of the electronic speed controller. The heat-conducting copper pipe 6 contacts the heat-conducting plate 8 through the heat-conducting medium filled in the medium-filling gap 7. Several heat-conducting copper pipes 6 are in contact with the heat-conducting plate 8 along the length of the heat-conducting plate 8.
[0053] Example 6.
[0054] like Figure 1-5 As shown, the present invention provides a high-voltage resistant electronic control device for fuel cell drones, including a circuit board 2, a mounting shell 1, a silicon carbide MOSFET device 3 mounted on the circuit board 2, a first heat dissipation mechanism disposed on the silicon carbide MOSFET device 3, and a second heat dissipation mechanism disposed on the mounting shell 1 and in contact with the first heat dissipation mechanism; the circuit board 2 is mounted inside the mounting shell 1.
[0055] The first heat dissipation mechanism includes a first thermally conductive copper sheet 4 disposed at the bottom of the silicon carbide MOSFET device 3, a second thermally conductive copper sheet 5 disposed at the top of the silicon carbide MOSFET device 3, and a plurality of thermally conductive copper pipes 6 disposed on the second thermally conductive copper sheet 5 and respectively in contact with the second heat dissipation mechanism.
[0056] The heat-conducting copper tube 6 is U-shaped.
[0057] In this embodiment 6, based on the structure of the circuit board 2, when the circuit board 2 is installed inside the mounting housing 1, a certain gap is left between the silicon carbide MOSFET device 3 and the heat-conducting plate 8 inside the mounting housing 1. The heat-conducting copper pipe 6 is U-shaped and is placed horizontally between the silicon carbide MOSFET device 3 and the heat-conducting plate 8. In this way, the heat-conducting copper pipe 6 can come into contact with the silicon carbide MOSFET device 3 and the heat-conducting plate 8, which is beneficial for heat transfer between the silicon carbide MOSFET device 3 and the heat-conducting plate 8.
[0058] Example 7.
[0059] like Figure 1-5 As shown, the present invention provides a high-voltage resistant electronic control device for fuel cell drones, including a circuit board 2, a mounting shell 1, a silicon carbide MOSFET device 3 mounted on the circuit board 2, a first heat dissipation mechanism disposed on the silicon carbide MOSFET device 3, and a second heat dissipation mechanism disposed on the mounting shell 1 and in contact with the first heat dissipation mechanism; the circuit board 2 is mounted inside the mounting shell 1.
[0060] Mounting housing 1 includes housing 11 connected to an external drone, and housing cover 12 attached to housing 11; circuit board 2 is mounted between housing 11 and housing cover 12; second heat dissipation mechanism is located on housing cover 12.
[0061] Example 8.
[0062] like Figure 1-5 As shown, the present invention provides a high-voltage resistant electronic control device for fuel cell drones, including a circuit board 2, a mounting shell 1, a silicon carbide MOSFET device 3 mounted on the circuit board 2, a first heat dissipation mechanism disposed on the silicon carbide MOSFET device 3, and a second heat dissipation mechanism disposed on the mounting shell 1 and in contact with the first heat dissipation mechanism; the circuit board 2 is mounted inside the mounting shell 1.
[0063] Mounting housing 1 includes housing 11 connected to an external drone, and housing cover 12 attached to housing 11; circuit board 2 is mounted between housing 11 and housing cover 12; second heat dissipation mechanism is located on housing cover 12.
[0064] The housing 11 is provided with a first threaded connecting block 14, and the cover 12 is provided with a second threaded connecting block 15 that is adapted to the first threaded connecting block 14. The first threaded connecting block 14 and the second threaded connecting block 15 are internally threaded with bolts 16.
[0065] In this embodiment 8, the mounting shell 1 includes a shell 11 connected to an external drone, and a shell cover 12 attached to the shell 11. The shell 11 and the shell cover 12 are connected by internal threaded bolts 16 in the first threaded connecting block 14 and the second threaded connecting block 15. The connection and disassembly between the shell 11 and the shell cover 12 are convenient, thus facilitating the installation or disassembly of the circuit board between the shell 11 and the shell cover 12.
[0066] Example 9.
[0067] like Figure 1-5 As shown, the present invention provides a high-voltage resistant electronic control device for fuel cell drones, including a circuit board 2, a mounting shell 1, a silicon carbide MOSFET device 3 mounted on the circuit board 2, a first heat dissipation mechanism disposed on the silicon carbide MOSFET device 3, and a second heat dissipation mechanism disposed on the mounting shell 1 and in contact with the first heat dissipation mechanism; the circuit board 2 is mounted inside the mounting shell 1.
[0068] Mounting housing 1 includes housing 11 connected to an external drone, and housing cover 12 attached to housing 11; circuit board 2 is mounted between housing 11 and housing cover 12; second heat dissipation mechanism is located on housing cover 12.
[0069] The housing 11 is provided with a third threaded connection block 17 for connecting to an external drone.
[0070] In this embodiment 9, the external drone is provided with a fourth threaded connecting block 17 that is adapted to the third threaded connecting block 17. The entire utility model is threadedly connected to the external drone by screwing bolts into the third threaded connecting block 17 and the fourth threaded connecting block 17.
[0071] Example 10.
[0072] like Figure 1-5 As shown, the present invention provides a high-voltage resistant electronic control device for fuel cell drones, including a circuit board 2, a mounting shell 1, a silicon carbide MOSFET device 3 mounted on the circuit board 2, a first heat dissipation mechanism disposed on the silicon carbide MOSFET device 3, and a second heat dissipation mechanism disposed on the mounting shell 1 and in contact with the first heat dissipation mechanism; the circuit board 2 is mounted inside the mounting shell 1.
[0073] Mounting housing 1 includes housing 11 connected to an external drone, and housing cover 12 attached to housing 11; circuit board 2 is mounted between housing 11 and housing cover 12; second heat dissipation mechanism is located on housing cover 12.
[0074] A wiring inlet 18 and a wiring outlet 19 are formed between the housing 11 and the cover 12.
[0075] In this embodiment 10, there are two line input ports 18 and three line output ports 19. When this utility model is used to adjust the speed of the motor on an external drone, the power supply of the external drone is connected to the circuit board 2 through the line input port 18, and the motor on the external drone is connected to the circuit board 2 through the line output ports 19.
[0076] Finally, it should be noted that the above embodiments are merely preferred embodiments of this utility model used to illustrate the technical solutions of this utility model, and are not intended to limit it, nor are they intended to limit the patent scope of this utility model. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this utility model. That is to say, any changes or refinements made to the main design concept and spirit of this utility model that are not of substantial significance, but whose technical problems are still consistent with those of this utility model, should be included within the protection scope of this utility model. In addition, the direct or indirect application of the technical solutions of this utility model to other related technical fields are similarly included within the patent protection scope of this utility model.
Claims
1. A high-voltage resistant electronic speed controller for fuel cell drones, comprising a circuit board (2), characterized in that, It also includes a mounting housing (1), a silicon carbide MOSFET device (3) mounted on a circuit board (2), a first heat dissipation mechanism disposed on the silicon carbide MOSFET device (3), and a second heat dissipation mechanism disposed on the mounting housing (1) and in contact with the first heat dissipation mechanism; the circuit board (2) is mounted inside the mounting housing (1).
2. The high-voltage resistant electronic speed controller for a fuel cell drone according to claim 1, characterized in that, The first heat dissipation mechanism includes a first thermally conductive copper sheet (4) disposed at the bottom of the silicon carbide MOSFET device (3), a second thermally conductive copper sheet (5) disposed at the top of the silicon carbide MOSFET device (3), and a plurality of thermally conductive copper tubes (6) disposed on the second thermally conductive copper sheet (5) and respectively in contact with the second heat dissipation mechanism.
3. A high-voltage resistant electronic speed controller for a fuel cell drone according to claim 2, characterized in that, The second heat dissipation mechanism includes a heat-conducting plate (8) disposed inside the mounting housing (1) and in contact with the heat-conducting copper pipe (6), and a plurality of heat dissipation fins (9) respectively connected to the heat-conducting plate (8) and respectively located outside the mounting housing (1).
4. A high-voltage resistant electronic speed controller for a fuel cell drone according to claim 3, characterized in that, A heat dissipation slot (10) is formed between two adjacent heat dissipation fins (9).
5. A high-voltage resistant electronic speed controller for a fuel cell drone according to claim 3, characterized in that, A medium-filled gap (7) is formed between the heat-conducting copper tube (6) and the heat-conducting plate (8).
6. A high-voltage resistant electronic speed controller for a fuel cell drone according to claim 2, characterized in that, The heat-conducting copper tube (6) is U-shaped.
7. A high-voltage resistant electronic speed controller for a fuel cell drone according to claim 1, characterized in that, The mounting housing (1) includes a housing (11) connected to an external drone, and a cover (12) attached to the housing (11); a circuit board (2) is mounted between the housing (11) and the cover (12); and a second heat dissipation mechanism is located on the cover (12).
8. A high-voltage resistant electronic speed controller for a fuel cell drone according to claim 7, characterized in that, The housing (11) is provided with a first threaded connecting block (14), and the cover (12) is provided with a second threaded connecting block (15) that is compatible with the first threaded connecting block (14). The first threaded connecting block (14) and the second threaded connecting block (15) are internally threaded with bolts (16).
9. A high-voltage resistant electronic speed controller for a fuel cell drone according to claim 7, characterized in that, The housing (11) is provided with a third threaded connection block (17) for connecting to an external drone.
10. A high-voltage resistant electronic speed controller for a fuel cell drone according to claim 7, characterized in that, A wiring inlet (18) and a wiring outlet (19) are formed between the housing (11) and the cover (12).