Grouping ignition coil of unmanned aerial vehicle engine

Abstract

An unmanned aerial vehicle engine grouping ignition coil comprises a shell, the shell is provided with a containing cavity with an upward opening, the containing cavity is covered with a top cover, the bottom of the shell protrudes towards the two sides in the transverse direction to form a first high-voltage head and a second high-voltage head, a low-voltage head is installed on one side of the shell, and the low-voltage head is installed on the other side of the shell. A coil assembly is installed in the containing cavity and provided with a positive high-voltage output end and a negative high-voltage output end, a first high-voltage wire harness is installed on the first high-voltage head, and the other end of the first high-voltage wire harness is used for being provided with a first spark plug connected to the positive high-voltage output end. A second high-voltage wire harness is installed on the second high-voltage head, and the other end of the second high-voltage wire harness is used for configuring a second spark plug connected to the negative high-voltage output end. The structure optimization design of the ignition coil is a single-coil double-output structure, one coil can be a two-cylinder ignition coil, and the ignition energy is improved. For the unmanned aerial vehicle, the number of spark plugs used for single-coil dual output is reduced by half, and the total weight is reduced.

Description

Technical Field

[0001] This invention relates to an ignition coil for a drone engine. Background Technology

[0002] In existing technologies, for passenger vehicle applications, the mainstream currently uses single-coil single-output coils with higher output energy than the coil energy in this patent. For example, CN223712551U discloses an ignition coil with a non-uniform thickness iron core structure, including a housing, a low-voltage head at the top of the housing, a high-voltage sheath assembly at the bottom of the housing, a coil assembly arranged laterally inside the housing and filled with epoxy resin, the low-voltage head located at one end of the coil assembly, and an ignition module located inside the housing adjacent to the low-voltage head. The coil assembly includes a T-shaped iron core, a primary frame sleeved outside the T-shaped iron core, a secondary frame sleeved outside the primary frame, and a first C-shaped iron core and a second C-shaped iron core surrounding the secondary frame. The first C-shaped iron core and the second C-shaped iron core are combined together to form an O-shape and connected to the end of the T-shaped iron core. The thickness of the first C-shaped iron core and the second C-shaped iron core is greater than the thickness of the T-shaped iron core. However, in the application of piston engines for drones, aircraft safety must be considered in the design. Simply dividing a single coil into two outputs would result in lower effective ignition energy compared to a single coil with a single output. To address this issue, the ignition coil structure needs to be redesigned. Summary of the Invention

[0003] To address the problems in the prior art, the purpose of this invention is to provide an ignition coil for a drone engine with high output energy.

[0004] To achieve the above objectives, the technical solution adopted by the present invention is: a drone engine grouped ignition coil, including a housing, the housing having an upward-opening receiving cavity, the receiving cavity being covered by a top cover, the bottom of the housing protruding laterally to both sides to form a first high-voltage head and a second high-voltage head, a low-voltage head being installed on one side of the housing, a coil assembly being installed inside the receiving cavity, the coil assembly having a positive high-voltage output terminal and a negative high-voltage output terminal, a first high-voltage wire harness being installed on the first high-voltage head, the other end of the first high-voltage wire harness being used to configure a first spark plug connected to the positive high-voltage output terminal, a second high-voltage wire harness being installed on the second high-voltage head, the other end of the second high-voltage wire harness being used to configure a second spark plug connected to the negative high-voltage output terminal.

[0005] Preferably, the first spark plug and the second spark plug are respectively connected to adjacent cylinders.

[0006] Preferably, the first high-voltage wire harness and the second high-voltage wire harness are internally provided with suppression resistors.

[0007] Preferably, the coil assembly includes a T-shaped iron core, a primary frame sleeved on the outside of the T-shaped iron core, a secondary frame sleeved on the primary frame, and a first C-shaped iron core and a second C-shaped iron core surrounding the outside of the secondary frame. The primary frame is wound with primary windings, and the secondary frame is wound with secondary windings. The first C-shaped iron core and the second C-shaped iron core are wrapped with thermoplastic elastic buffer covers. The first C-shaped iron core and the second C-shaped iron core are combined together at both ends of the secondary frame.

[0008] Preferably, the top surface of the T-shaped iron core is attracted to the first C-shaped iron core and the second C-shaped iron core by a magnetic sheet.

[0009] Preferably, the receiving cavity is filled with epoxy resin and the coil assembly is completely encapsulated therein.

[0010] Preferably, a first high-pressure pin is installed inside the first high-pressure head, and a second high-pressure pin is installed inside the second high-pressure head.

[0011] Preferably, positioning ribs are provided at intervals on the side walls of the mounting holes of the first high-pressure pin and the second high-pressure pin.

[0012] Preferably, the first high-voltage harness plug is connected to the first high-voltage pin, and the second high-voltage harness plug is connected to the second high-voltage pin.

[0013] Preferably, the low-pressure head is connected to the outer casing via a slot.

[0014] Thanks to the above technical solutions, the optimized design of this ignition coil features a single-coil dual-output configuration, allowing one coil to ignite two cylinders, thus increasing ignition energy. For drones, the single-coil dual-output design halves the number of spark plugs needed, reducing the overall weight. Attached Figure Description

[0015] Appendix Figure 1 A perspective view of the grouped ignition coils of the UAV engine according to the present invention; Appendix Figure 2 A three-dimensional exploded view of the grouped ignition coils of the UAV engine according to the present invention; Appendix Figure 3 A three-dimensional exploded view of the coil assembly of the grouped ignition coil of the UAV engine according to the present invention; Appendix Figure 4 A partial cross-sectional view of the coil assembly of the integrated single-cylinder independent ignition coil according to the present invention; Appendix Figure 5 A cross-sectional view of the first high-voltage wiring harness of the unmanned aerial vehicle engine group ignition coil according to the present invention; Appendix Figure 6 The circuit diagram of the grouped ignition coil of the UAV engine according to the present invention. Detailed Implementation

[0016] In the following description, the terminology used in the specification will be briefly described, and embodiments will be described in detail. All terms used herein, including descriptive or technical terms, should be interpreted as having the meaning understood by one of ordinary skill in the art. However, these terms may have different meanings depending on the intent of one of ordinary skill in the art, precedent, or the emergence of new technologies.

[0017] Furthermore, some terms may be chosen by the applicant, and in such cases, the meaning of the chosen terms will be described in detail in the detailed description of the embodiments. Therefore, the terms used herein must be defined based on their meanings in conjunction with the description throughout the specification. Additionally, when a component “comprises” or “contains” an element, the component may also include other elements without excluding them, unless there is a specific description to the contrary. In the following description, terms such as “component” and “module” indicate a unit for performing at least one function or operation, wherein units and modules may be implemented as hardware or software or by combining hardware and software.

[0018] Embodiments will now be described more fully with reference to the accompanying drawings. However, embodiments may be implemented in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of the embodiments to those skilled in the art. In the following description, well-known functions or structures are not described in detail, as they would obscure the embodiments with unnecessary detail, and throughout the specification, the same reference numerals in the drawings denote the same or similar elements.

[0019] Appendix Figure 1 A perspective view of the grouped ignition coils of the UAV engine according to the present invention; attached. Figure 2 This is a three-dimensional exploded view of a drone engine grouped ignition coil according to the present invention. This embodiment is a drone engine grouped ignition coil, including a housing 1 with an upward-opening receiving cavity. A top cover 2 covers the receiving cavity. A first high-voltage head 3 and a second high-voltage head 4 are formed by laterally protruding from the bottom of the housing 1 on both sides. A low-voltage head 5 is installed on one side of the housing 1 and is connected to the housing 1 via a slot. A coil assembly 6 is installed inside the receiving cavity. The coil assembly 6 has a positive high-voltage output terminal and a negative high-voltage output terminal. A first high-voltage wiring harness 7 is installed on the first high-voltage head 2, and the other end of the first high-voltage wiring harness 7 is used to configure a first spark plug connected to the positive high-voltage output terminal. A second high-voltage wiring harness 8 is installed on the second high-voltage head 4, and the other end of the second high-voltage wiring harness 8 is used to configure a second spark plug connected to the negative high-voltage output terminal.

[0020] Appendix Figure 3 A three-dimensional exploded view of the coil assembly of the unmanned aerial vehicle engine grouped ignition coil according to the present invention; attached. Figure 4 This is a partial cross-sectional view of the coil assembly of the integrated single-cylinder independent ignition coil according to the present invention. The coil assembly 6 includes a T-shaped iron core 61, a primary frame 62 sleeved on the outside of the T-shaped iron core 61, a secondary frame 63 sleeved on the primary frame 62, and a first C-shaped iron core 64 and a second C-shaped iron core 65 surrounding the outside of the secondary frame 63. The first C-shaped iron core 64 and the second C-shaped iron core 65 are combined at both ends of the secondary frame 63. The top surface of the T-shaped iron core 61 is attracted to the first C-shaped iron core 64 and the second C-shaped iron core 65 by a magnetic sheet 66. The iron core structure adopts a closed design consisting of two (double) C-shaped sections and a (single) T-shaped section in the middle. Due to the low magnetic resistance and concentrated magnetic flux, the energy conversion efficiency of the closed magnetic circuit structure is significantly improved. The magnetic sheet uses permanent magnet material, which can increase the energy storage of the primary coil, resulting in a higher output voltage and energy of the ignition coil.

[0021] The housing cavity is filled with epoxy resin, which completely encapsulates the coil assembly 6. The first C-shaped iron core 64 and the second C-shaped iron core 65 are externally wrapped with thermoplastic elastic buffer covers. Due to the difference in the linear expansion coefficients of the internal materials, the thermoplastic elastic buffer covers use elastic polymer materials. This significantly reduces the risk of cracking of the filling material (epoxy resin) under temperature changes in the ignition coil, improving the stability and service life of the ignition coil. The top of each of the thermoplastic elastic buffer covers for the first C-shaped iron core 64 and the second C-shaped iron core 65 has multiple spaced grooves, thereby reducing the amount of epoxy resin used and dispersing the internal stress of the epoxy resin.

[0022] Primary windings are wound on the primary frame 62. A first fixing groove and a second fixing groove are provided above the primary frame 62. The beginning and end ends of the primary windings are respectively wound and fixed in the first and second fixing grooves. The first and second fixing grooves are square grooves with their openings facing upwards. When the primary wire is wound around the fixing grooves on the primary frame, and the low-voltage insert is inserted into the fixing groove, the retaining clip on the low-voltage insert pierces the enamel coating of the primary wire, connecting the primary wire to the insert.

[0023] Secondary windings are wound on the secondary frame 63. A first fixing seat and a second fixing seat are respectively provided at both ends of the secondary frame 63. A first high-voltage insert is installed in the first fixing seat, and a second high-voltage insert is installed in the second fixing seat. The beginning and end ends of the secondary windings are respectively wound and fixed onto the first and second high-voltage inserts. The first and second fixing seats are circular holes with openings facing both sides. The first and second high-voltage inserts are hollow annular structures. The first and second high-voltage inserts have openings for the wire ends, and their ends have positioning handles.

[0024] A first high-voltage pin 31 is installed inside the first high-voltage head 3, and the first high-voltage pin 31 makes pin-type contact with the first high-voltage plug. A second high-voltage pin 41 is installed inside the second high-voltage head 4, and the second high-voltage pin 41 makes pin-type contact with the second high-voltage plug. Positioning ribs are spaced apart on the side walls of the mounting holes of the first high-voltage pin 31 and the second high-voltage pin 41. These positioning ribs increase the stability of the connection and reduce contact resistance. The first high-voltage wire harness 7 is pin-connected to the first high-voltage pin 31, and the second high-voltage wire harness 8 is pin-connected to the second high-voltage pin 41.

[0025] Appendix Figure 5 This is a cross-sectional view of the first high-voltage wiring harness of the drone engine group ignition coil according to the present invention; the first high-voltage wiring harness 7 and the second high-voltage wiring harness 8 are internally provided with suppression resistors 9, which can provide EMC noise filtering.

[0026] Appendix Figure 6 This is a circuit diagram of the grouped ignition coil for a drone engine according to the present invention. This ignition coil is used in a drone engine, a horizontally opposed 4-cylinder four-stroke engine, with 2 spark plugs per cylinder (8 in total), using 4 ignition coils connected to the spark plugs in a cross-connection manner via a high-voltage wiring harness. The ignition coil is designed as a single-coil dual-output coil, meaning one coil can ignite two cylinders. Specifically, it ignites cylinders #1 and #2. When cylinder #1 is ignited (effective ignition), cylinder #2 is in exhaust mode (ineffective ignition); when cylinder #2 is ignited (effective ignition), cylinder #1 is in exhaust mode (ineffective ignition). C1-, C2-, C3-, C4-: These are the negative terminals of the ignition control signals for the four cylinders. The ECU controls the ignition of the corresponding cylinder by controlling the on / off state of these four pins to ground. B+: Positive power supply, controlled by the ignition switch or main relay. Each coil (C1- to C4-) is individually controlled by the ECU and does not interfere with each other. This means that if the internal circuitry of one coil (such as the transformer corresponding to C1) fails, only one cylinder will misfire, while the other three cylinders will continue to operate normally. However, the high-voltage output of ignition coil 2 also ignites cylinders #1 and #2, replenishing the misfired cylinder and ensuring the safety of the drone. The ECU's control signal is achieved by controlling the grounding circuit of the primary coil. Internally, the ECU acts like a switch; when it connects C1- to ground, the primary coil is energized and stores energy; when it disconnects, the primary coil current disappears, inducing a high-voltage current in the secondary coil, thus achieving ignition.

[0027] It should be understood that the embodiments described herein should be considered in a descriptive sense only and not for limiting purposes. The description of features or aspects within each embodiment should generally be considered applicable to other similar features or aspects in other embodiments. Although one or more embodiments have been described with reference to the accompanying drawings, those skilled in the art will understand that various changes in form and detail may be made therein without departing from the spirit and scope defined by the appended claims.

Claims

1. A grouped ignition coil for a drone engine, characterized in that: The device includes a housing (1) having an upward-opening receiving cavity covered by a top cover (2). The bottom of the housing (1) protrudes laterally to both sides to form a first high-voltage head (3) and a second high-voltage head (4). A low-voltage head (5) is installed on one side of the housing (1). A coil assembly (6) is installed inside the receiving cavity. The coil assembly (6) has a positive high-voltage output terminal and a negative high-voltage output terminal. A first high-voltage wire harness (7) is installed on the first high-voltage head (2). The other end of the first high-voltage wire harness (7) is used to configure a first spark plug connected to the positive high-voltage output terminal. A second high-voltage wire harness (8) is installed on the second high-voltage head (4). The other end of the second high-voltage wire harness (8) is used to configure a second spark plug connected to the negative high-voltage output terminal.

2. The UAV engine grouped ignition coil according to claim 1, characterized in that: The first spark plug and the second spark plug are respectively connected to adjacent cylinders.

3. The UAV engine grouped ignition coil according to claim 1, characterized in that: The first high-voltage wire harness (7) and the second high-voltage wire harness (8) are equipped with suppression resistors (9).

4. The UAV engine grouped ignition coil according to claim 1, characterized in that: The coil assembly (6) includes a T-shaped iron core (61), a primary frame (62) sleeved on the outside of the T-shaped iron core (61), a secondary frame (63) sleeved on the primary frame (62), and a first C-shaped iron core (64) and a second C-shaped iron core (65) surrounding the outside of the secondary frame (63). The primary frame (62) is wound with primary windings, and the secondary frame (63) is wound with secondary windings. The first C-shaped iron core (64) and the second C-shaped iron core (65) are wrapped with thermoplastic elastic buffer covers. The first C-shaped iron core (64) and the second C-shaped iron core (65) are combined together at both ends of the secondary frame (63).

5. The dual-ended output coil assembly according to claim 4, characterized in that: The top surface of the T-shaped iron core (61) is attracted to the first C-shaped iron core (64) and the second C-shaped iron core (65) by a magnetic sheet (66).

6. The UAV engine grouped ignition coil according to claim 1, characterized in that: The cavity is filled with epoxy resin and the coil assembly (6) is completely encapsulated therein.

7. The UAV engine grouped ignition coil according to claim 1, characterized in that: The first high-pressure head (3) is equipped with a first high-pressure pin (31), and the second high-pressure head (4) is equipped with a second high-pressure pin (41).

8. The UAV engine grouped ignition coil according to claim 7, characterized in that: Positioning ribs are provided at intervals on the side walls of the mounting holes of the first high-pressure pin (31) and the second high-pressure pin (41).

9. The UAV engine grouped ignition coil according to claim 7, characterized in that: The first high-voltage harness (7) is connected to the first high-voltage pin (31) by a pin, and the second high-voltage harness (8) is connected to the second high-voltage pin (41) by a pin.

10. The UAV engine grouped ignition coil according to claim 1, characterized in that: The low-pressure head (5) is connected to the outer casing (1) via a slot.

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