An aviation piston engine redundant ignition system with electromagnetic shielding function and an ignition method

Abstract

The application discloses an aviation piston engine redundant ignition system with an electromagnetic shielding function and an ignition method, and particularly relates to the field of engines. The system comprises a first control module and a second control module, two control modules are connected with two ignition coils through high-voltage damping lines, each ignition coil is connected with a spark plug mechanism through a high-voltage damping line, two spark plug mechanisms are arranged on a cylinder of the engine, the high-voltage damping line is coated with a shielding layer, and the spark plug mechanism is correspondingly sleeved with a shielding shell. Based on the system, redundant ignition control is adopted, two control modules are used, each control module can control two independent ignition systems at the same time, electric energy is released to two ignition coils at the same time, ignition control is performed, and electromagnetic interference can be effectively inhibited.

Description

Technical Field

[0001] This application relates to the field of engines, and in particular to a redundant ignition system and ignition method for an aircraft piston engine with electromagnetic shielding function. Background Technology

[0002] The ignition system of an aircraft piston engine generates strong high-frequency electromagnetic interference during operation. This interference can severely affect the normal operation of the aircraft's radio communications, navigation equipment, and electronic instruments, and may even lead to safety hazards such as signal distortion and communication interruptions. Traditional ignition systems radiate electromagnetic waves during high-voltage discharge, and existing technologies using single-layer shielding structures or simple anti-interference measures often fail to meet the stringent electromagnetic compatibility requirements of avionics. Currently, some aircraft ignition systems suppress interference by wrapping high-voltage damping wires with metal braided mesh, but this method suffers from incomplete shielding and poor grounding, failing to effectively suppress electromagnetic interference. Furthermore, some aircraft ignition systems in this case are controlled by only a single control system, which cannot guarantee the stability of the engine ignition system. Summary of the Invention

[0003] The main purpose of this application is to provide a redundant ignition system and ignition method for an aircraft piston engine with electromagnetic shielding function, aiming to solve the problem that existing ignition systems cannot effectively suppress electromagnetic interference.

[0004] To achieve the above objectives, this application provides a redundant ignition system for an aircraft piston engine with electromagnetic shielding, comprising a first control module and a second control module; the first control module includes a first controller connected to a first stator and a first capacitor, with a first charging coil and a first trigger coil wound on the first stator; the second control module includes a second controller connected to a second stator and a second capacitor, with a second charging coil and a second trigger coil wound on the second stator; the first and second stators are symmetrically arranged on both sides of the engine rotor and located within the rotor's cutting range; the first controller is connected to a first high-voltage damping wire via a first charging coil and a second trigger coil. A first ignition coil and a second ignition coil are provided. A second controller is connected to the first ignition coil and the second ignition coil respectively via a second high-voltage damping wire. The first ignition coil is connected to a first spark plug mechanism via a third high-voltage damping wire. The first spark plug mechanism is mounted on the cylinder of the engine and is used to generate an electric spark. The second ignition coil is connected to a second spark plug mechanism via a fourth high-voltage damping wire. The second spark plug mechanism is mounted on the cylinder of the engine and is used to generate an electric spark. The first, second, third, and fourth high-voltage damping wires are each covered with a shielding layer. Shielding shells are respectively fitted onto the first spark plug mechanism and the second spark plug mechanism.

[0005] Optionally, the shielding materials of the first high-voltage damping wire and the second high-voltage damping wire are the same, and the shielding layer includes a metal shielding mesh layer and a silicone rubber layer arranged from the inside out.

[0006] Optionally, the shielding layer material of the third and fourth high-voltage damping wires is the same, which is silicone rubber.

[0007] Optionally, the first spark plug mechanism and the second spark plug mechanism have the same structure. The first spark plug mechanism includes a spark plug and a spark plug cap. The shielding housing includes a shielding sleeve with openings at both ends. The shielding sleeve is fitted onto the spark plug. One end of the shielding sleeve is in close contact with the outer wall of the engine cylinder. The other end is covered with a cap. The cap is fitted onto the spark plug cap and is pressed against the grounding copper strip of the spark plug.

[0008] To achieve the above objectives, this application also provides an ignition method for an aircraft piston engine with electromagnetic shielding, employing a redundant ignition system. The method includes: the engine rotor rotates, and through electromagnetic induction, both a first charging coil and a second charging coil generate electrical energy; the first charging coil transmits the electrical energy to a first control module and a second control module for storage, respectively, while the second charging coil transmits the electrical energy to both the first control module and the second control module for storage; a first trigger coil emits an ignition signal and transmits it to both the first control module and the second control module; the second trigger coil emits an ignition signal and transmits it to both the first control module and the second control module. Two control modules; the first control module releases electrical energy to the first ignition coil and the second ignition coil respectively through the first high-voltage damping wire, and at the same time, the second control module releases electrical energy to the first ignition coil and the second ignition coil respectively through the second high-voltage damping wire. The shielding layers of the first high-voltage damping wire and the second high-voltage damping wire shield external electromagnetic signals during the release of electrical energy; the first ignition coil transmits voltage to the first spark plug mechanism through the third high-voltage damping wire, and the second ignition coil transmits voltage to the second spark plug mechanism through the fourth high-voltage damping wire, generating an electric spark to complete ignition; the shielding shell shields the narrowband electromagnetic interference generated during the spark plug discharge process.

[0009] Compared with the prior art, the beneficial effects of this application are as follows:

[0010] This invention relates to a redundant ignition system for aero-piston engines with electromagnetic shielding. Ignition is achieved by generating alternating current through rotor rotation cutting magnetic field lines, thus providing passive ignition and improving reliability. This ignition method is energy-independent; all electrical energy originates from the permanent magnets and coils themselves, without relying on external power. The first and second high-voltage damping wires serve as the first layer of shielding, used for trigger signal transmission during ignition. The third and fourth high-voltage damping wires serve as the second layer of shielding, and the shielding shell serves as the third layer. The second and third shielding structures are used for electrical signal transmission during ignition. The three layers of shielding are designed collaboratively to form a complete electromagnetic shielding system, which can more effectively suppress electromagnetic interference, ensure the stable operation of aviation radio signals and navigation equipment, and reduce the risk of signal distortion and communication interruption.

[0011] The redundant ignition method for aero-piston engines with electromagnetic shielding of the present invention employs redundant ignition control, using a first control module and a second control module for ignition control. Each control module can simultaneously control two independent ignition systems and release electrical energy to two ignition coils. If one control module fails, the other control module can still maintain ignition control. In addition, if a component in one ignition system fails, the other ignition system can still maintain the smooth progress of the ignition process, thereby improving the stability of the aero-piston engine ignition system and reducing the risk of ignition failure due to ignition signal interruption. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of a redundant ignition system for an aircraft piston engine with electromagnetic shielding function, as described in this application.

[0013] Figure 2 This is a schematic flowchart of a redundant ignition method for an aircraft piston engine with electromagnetic shielding. The realization of the purpose, functional characteristics, and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. Detailed Implementation

[0014] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0015] The first embodiment of the present invention provides a redundant ignition system for an aircraft piston engine with electromagnetic shielding function, including a first control module and a second control module; the first control module includes a first controller, which is connected to a first stator and a first capacitor, and a first charging coil and a first trigger coil are wound on the first stator; the second control module includes a second controller, which is connected to a second stator and a second capacitor, and a second charging coil and a second trigger coil are wound on the second stator; the first stator and the second stator are symmetrically arranged on both sides of the engine rotor and located within the rotor's cutting range; the first controller is connected to a first high-voltage damping wire respectively. The first ignition coil and the second ignition coil, and the second controller are connected to the first ignition coil and the second ignition coil respectively via a second high-voltage damping wire; the first ignition coil is connected to the first spark plug mechanism via a third high-voltage damping wire, and the first spark plug mechanism is installed on the cylinder of the engine to generate an electric spark; the second ignition coil is connected to the second spark plug mechanism via a fourth high-voltage damping wire, and the second spark plug mechanism is installed on the cylinder of the engine to generate an electric spark; the first high-voltage damping wire, the second high-voltage damping wire, the third high-voltage damping wire and the fourth high-voltage damping wire are respectively covered with a shielding layer; the first spark plug mechanism and the second spark plug mechanism are respectively fitted with shielding shells.

[0016] In this embodiment, ignition is achieved by generating alternating current through rotor rotation cutting magnetic field lines, serving as passive ignition and improving ignition reliability. This ignition method is energy-independent; all electrical energy comes from the permanent magnet and coils themselves, without relying on external power. Redundant ignition control is employed, using two ignition control modules: a first control module and a second control module. Each module can simultaneously control two independent ignition systems, releasing electrical energy to both ignition coils. If one control module fails, the other can still maintain ignition control. Furthermore, if a component in one ignition system fails, the other system can still maintain the ignition process, improving the stability of the aero-piston engine ignition system and reducing the risk of ignition failure due to ignition signal interruption. The first and second high-voltage damping wires serve as the first layer of shielding, used for transmitting trigger signals during ignition. The third and fourth high-voltage damping wires serve as the second layer of shielding, and the shielding shell serves as the third layer of shielding. The second and third shielding structures are used for transmitting electrical signals during ignition. The three shielding structures are designed in a coordinated manner to form a complete electromagnetic shielding system, which can more effectively suppress electromagnetic interference, ensure the stable operation of aviation radio signals and navigation equipment, and reduce the risk of signal distortion and communication interruption.

[0017] For example, the shielding layer materials of the first and second high-voltage damping wires are the same, and the shielding layer includes a metal shielding mesh layer and a silicone rubber layer disposed from the inside out. The shielding layer materials of the third and fourth high-voltage damping wires are the same, and the shielding layer material is silicone rubber.

[0018] In this embodiment, the first and second shielding structures are used to suppress broadband electromagnetic interference radiated by damping lines. Lightweight materials such as silicone rubber are used to ensure excellent shielding performance while meeting the strict weight requirements of aero-piston engines, and also improving the mechanical strength and durability of the components.

[0019] For example, the first spark plug mechanism and the second spark plug mechanism have the same structure. The first spark plug mechanism includes a spark plug and a spark plug cap. The shielding housing includes a shielding sleeve with openings at both ends. The shielding sleeve is fitted onto the spark plug. One end of the shielding sleeve is in close contact with the outer wall of the engine cylinder. The other end is covered with a cap. The cap is attached to the top of the spark plug cap and is pressed against the grounding copper strip of the spark plug.

[0020] In this embodiment, the shielding shell is used to shield against narrowband electromagnetic interference generated during spark plug discharge. Copper foil is used as the third layer of shielding, and good electrical conductivity is ensured through the pressing of the cap and the grounding copper strip. Simultaneously, the shielding performance is further optimized through electromagnetic coupling between the shielding sleeve and the cap, solving the problems of poor grounding and incomplete shielding in existing technologies, and significantly improving overall electromagnetic compatibility. Due to the good ductility of copper, after assembling the shielding sleeve and cap onto the spark plug and installing the spark plug above the cylinder head, the copper material of the shielding shell, with its good ductility, can be pressed tightly against the cylinder head and deformed to completely fit the cylinder head, forming a sealed shield.

[0021] A second embodiment of the present invention provides an ignition method for an aircraft piston engine with electromagnetic shielding function, employing the aforementioned redundant ignition system. The method specifically includes the following steps:

[0022] In step S1, the engine rotor rotates, and through electromagnetic induction, both the first charging coil and the second charging coil generate electrical energy.

[0023] In step S2, the first charging coil transmits electrical energy to the first control module and the second control module for storage; the second charging coil transmits electrical energy to the first control module and the second control module for storage.

[0024] Specifically, the first charging coil transmits electrical energy to the first controller and the second controller respectively, and stores it in the first capacitor and the second capacitor; the second charging coil transmits electrical energy to the first controller and the second controller respectively, and stores it in the first capacitor and the second capacitor.

[0025] Step S3: The first trigger coil sends an ignition signal and transmits it to the first control module and the second control module respectively; the second trigger coil sends an ignition signal and transmits it to the first control module and the second control module respectively.

[0026] In step S4, the first control module releases electrical energy to the first ignition coil and the second ignition coil through the first high-voltage damping wire, and at the same time, the second control module releases electrical energy to the first ignition coil and the second ignition coil through the second high-voltage damping wire. The shielding layers of the first high-voltage damping wire and the second high-voltage damping wire shield external electromagnetic signals during the release of electrical energy.

[0027] In step S5, the first ignition coil transmits voltage to the first spark plug mechanism through the third high-voltage damping wire, and the second ignition coil transmits voltage to the second spark plug mechanism through the fourth high-voltage damping wire, generating an electric spark to complete ignition; the shielding shell shields external electromagnetic signals during the voltage transmission process.

[0028] In this embodiment, a redundant ignition control method is employed, using two ignition control modules: a first control module and a second control module. Each control module can simultaneously control two independent ignition systems, releasing electrical energy to both ignition coils. If one control module fails, the other can still maintain ignition control. Furthermore, if a component in one ignition system fails, the other system can still maintain the ignition process, improving the stability of the aero-piston engine ignition system and reducing the risk of ignition failure due to ignition signal interruption. Simultaneously, the first and second control modules can autonomously switch on and off. When troubleshooting the control box's malfunction, either control module can be autonomously switched to control the ignition for investigation.

[0029] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. A redundant ignition system for an aircraft piston engine with electromagnetic shielding function, characterized in that, It includes a first control module and a second control module; The first control module includes a first controller, which is connected to a first stator and a first capacitor. A first charging coil and a first trigger coil are wound on the first stator. The second control module includes a second controller, which is connected to a second stator and a second capacitor. A second charging coil and a second trigger coil are wound on the second stator. The first stator and the second stator are symmetrically arranged on both sides of the engine rotor and are located within the cutting range of the rotor; The first controller is connected to the first ignition coil and the second ignition coil via a first high-voltage damping wire, and the second controller is connected to the first ignition coil and the second ignition coil via a second high-voltage damping wire. The first ignition coil is connected to the first spark plug mechanism via the third high-voltage damping wire. The first spark plug mechanism is installed on the cylinder of the engine and is used to generate an electric spark. The second ignition coil is connected to the second spark plug mechanism via the fourth high-voltage damping wire. The second spark plug mechanism is installed on the cylinder of the engine and is used to generate an electric spark. The first, second, third, and fourth high-voltage damping wires are each covered with a shielding layer. The first spark plug mechanism and the second spark plug mechanism are respectively fitted with shielding shells.

2. The redundant ignition system for an aircraft piston engine with electromagnetic shielding function according to claim 1, characterized in that, The shielding layer materials of the first and second high-voltage damping wires are the same, and the shielding layer includes a metal shielding mesh layer and a silicone rubber layer arranged from the inside out.

3. The redundant ignition system for an aircraft piston engine with electromagnetic shielding function according to claim 1, characterized in that, The shielding layer material of the third and fourth high-voltage damping wires is the same, which is silicone rubber.

4. The redundant ignition system for an aircraft piston engine with electromagnetic shielding function according to claim 1, characterized in that, The first spark plug mechanism and the second spark plug mechanism have the same structure. The first spark plug mechanism includes a spark plug and a spark plug cap. The shielding housing includes a shielding sleeve with openings at both ends. The shielding sleeve is fitted onto the spark plug. One end of the shielding sleeve is in close contact with the outer wall of the engine cylinder, and the other end is covered with a cap. The cap is attached to the top of the spark plug cap and is pressed against the grounding copper strip of the spark plug.

5. An ignition method for an aircraft piston engine with electromagnetic shielding function, characterized in that, The method using the redundant ignition system according to any one of claims 1-4 includes: As the engine rotor rotates, electrical energy is generated in both the first and second charging coils through electromagnetic induction. The first charging coil transmits electrical energy to the first control module and the second control module for storage, and at the same time, the second charging coil transmits electrical energy to the first control module and the second control module for storage. The first trigger coil sends an ignition signal, which is then transmitted to the first control module and the second control module respectively. The second trigger coil sends an ignition signal, which is then transmitted to the first control module and the second control module respectively. The first control module releases electrical energy to the first ignition coil and the second ignition coil through the first high-voltage damping wire, respectively. At the same time, the second control module releases electrical energy to the first ignition coil and the second ignition coil through the second high-voltage damping wire, respectively. The shielding layers of the first high-voltage damping wire and the second high-voltage damping wire shield external electromagnetic signals during the release of electrical energy. The first ignition coil delivers voltage to the first spark plug mechanism through the third high-voltage damping wire, and the second ignition coil delivers voltage to the second spark plug mechanism through the fourth high-voltage damping wire, generating an electric spark to complete ignition. The shielding housing shields against narrowband electromagnetic interference generated during spark plug discharge.

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