CN212337513U - Ignition controller of small-sized aviation piston engine - Google Patents
Ignition controller of small-sized aviation piston engine Download PDFInfo
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- CN212337513U CN212337513U CN202020878737.4U CN202020878737U CN212337513U CN 212337513 U CN212337513 U CN 212337513U CN 202020878737 U CN202020878737 U CN 202020878737U CN 212337513 U CN212337513 U CN 212337513U
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Abstract
The invention relates to an ignition controller of a small aviation piston engine, belonging to the field of small aviation piston engines; the charging coil and the trigger coil are respectively wound on the charging iron core and the trigger iron core and are arranged in the shell; the control circuit comprises a charging circuit, a triggering circuit, a discharging circuit and a parking circuit; the shell is provided with an output port, a direct-current power supply positive electrode interface and a grounding port, the output port is connected with a spark plug of an engine cylinder through a high-voltage ignition coil, and the direct-current power supply positive electrode interface and the grounding port are respectively connected with a positive electrode and a negative electrode of a direct-current power supply. The ignition controller is provided with the charging iron core and the trigger iron core, the induced potential generated in the charging coil can be enhanced by 50%, the electric quantity stored by the capacitor in the control circuit can be increased by 30%, the induced potential in the trigger coil can be increased by 30%, and the ignition energy of the spark plug can be increased by 20%.
Description
Technical Field
The invention belongs to the field of small aviation piston engines, and particularly relates to an ignition controller of a small aviation piston engine.
Background
At present, the vast majority of small and medium-sized unmanned aerial vehicles use aviation piston engines, the ignition system of the unmanned aerial vehicles generally adopts a magneto ignition system, the system adopts a flywheel type rotating magnet structure, a flywheel is directly connected with a crankshaft to be installed, and an ignition coil component is installed on an engine crankcase.
Chinese patent publication No. CN 208595007U discloses a small two-stroke four-cylinder horizontally opposed aero-engine, which comprises a magneto, an exhaust pipe, a coupling, a check valve, a crankshaft, a crankcase, a split connecting rod, a piston and four cylinder bodies.
Chinese patent publication No. CN203403950U discloses "a small two-stroke four-cylinder aircraft engine, which comprises a crankcase, four cylinder bodies, four carburetors, an ignition mechanism, and an accelerator operating mechanism, wherein the four cylinder bodies are horizontally arranged on two sides of the crankcase in a pairwise manner, the crankcase is provided with a crankshaft, and the crankshaft is connected with pistons in the four cylinder bodies through connecting rods; the ignition mechanism synchronously ignites two opposite cylinder bodies and ignites the other two opposite cylinder bodies by 180-degree deviation.
Chinese patent publication No. CN206158856U discloses a four-cylinder unmanned aerial vehicle engine, which comprises a gas combustion device, a driving device, a transmission device and an exhaust device, wherein the driving device comprises: the device comprises a cylinder, a high-pressure cap, a spark plug, a cylinder gasket, a piston and a piston pin, wherein one end of the cylinder is connected with the spark plug through the high-pressure cap.
Chinese patent publication No. CN108869029A discloses a small two-stroke double-cylinder aviation gasoline engine, which comprises two cylinder bodies, an exhaust pipe, a magneto, a crankcase, a spark plug, an ignition cable, a magneto rotor, a check valve, a carburetor, an air filter, a coupling, a rear case, a crankshaft, a connecting rod and a piston.
Chinese patent publication No. CN203430682U discloses an ignition mechanism for a small two-stroke four-cylinder aircraft engine, which comprises an ignition rotor fixed to a crankshaft of the engine, two ignition coils, and four spark plugs mounted on four cylinder bodies.
The engines disclosed in the first four Chinese patents are all aviation two-stroke piston engines, ignition mechanisms of the engines all adopt magneto ignition systems, but detailed descriptions of related technologies and products are omitted; although the fifth chinese patent discloses an ignition mechanism, only the structure of the ignition rotor is described in detail, and the ignition coil is only described schematically, and the technology has the following defects: firstly, the energy generated on the primary coil of the ignition coil is weak and unstable, so that the ignition energy generated on the secondary coil cannot meet the ignition requirement, and the spark plug cannot normally and reliably ignite; secondly, the ignition time is changed in a mode of changing the circumferential position of the flywheel, once the flywheel is installed and fixed, the ignition time of the engine is fixed and cannot be dynamically changed when the engine works, and the ignition time of the engine at different rotating speeds is different, so that the performance of the engine at different rotating speeds is influenced; and thirdly, the engine cannot be flamed out and stopped due to the lack of a stopping control circuit.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides the ignition controller of the small aviation piston engine, which has simple structure and high reliability, and forms a complete magneto ignition system with an ignition rotor, so that the ignition system of the small aviation piston engine can work normally and reliably.
The technical scheme of the invention is as follows: an ignition controller of a small-sized aviation piston engine, characterized in that: the charging coil and the trigger coil are respectively wound on the charging iron core and the trigger iron core and are arranged in the shell; the control circuit is arranged in the shell and comprises a charging loop, a triggering loop, a discharging loop and a parking loop;
the shell is provided with an output port, a direct-current power supply positive electrode interface and a grounding port, the output port is connected with a spark plug of an engine cylinder through a high-voltage ignition coil, the direct-current power supply positive electrode interface is connected with a direct-current power supply positive electrode, and the grounding port is connected with a direct-current power supply negative electrode.
The further technical scheme of the invention is as follows: a charging coil L1, rectifier diodes D1 and D2 and capacitors C1 and C2 in the control circuit are sequentially connected to form a charging circuit, the diodes D1 and D2 are connected in series, one end of the charging coil L1 is connected with the anode of the diode D1, the cathode of the diode D2 is connected with one ends of the capacitors C1 and C2, the other end of the charging coil L1 is connected with the other ends of the capacitors C1 and C2, and the capacitors C1 and C2 are connected in parallel; the trigger circuit is formed by sequentially connecting a control electrode and a negative electrode of a trigger coil L2, a resistor R1 and a controlled silicon BG2, wherein the control electrode of the controlled silicon BG2 is connected with the resistor R1, the negative electrode of the BG2 is connected with a trigger coil L2, a rectifier diode D3 and a resistor R2 are connected with a trigger coil L2 in parallel, and a diode D4 is connected with the trigger circuit in parallel; the capacitors C1 and C2, the positive electrode and the negative electrode of the silicon controlled BG2, the output port and the high-voltage ignition coil are connected in sequence to form a discharge loop; direct current power supply positive pole interface, diode D5, resistance R3, the control pole of silicon controlled rectifier BG1, the ground connection port, diode D6, charging coil L1 links to each other and constitutes the parking return circuit, direct current power supply positive pole interface links to each other with diode D5's positive pole, silicon controlled rectifier BG 1's control pole links to each other with R3, BG 1's positive pole links to each other with charging coil L1 one end, the negative pole links to each other with the ground connection port, diode D6's positive pole, diode D6's negative pole links to each other with charging coil L1's the other end.
The further technical scheme of the invention is as follows: the output port, the direct-current power supply positive interface and the grounding port are all assembled by adopting embedded nuts, and the joint of the output port, the direct-current power supply positive interface and the grounding port and the shell is sealed and filled by adopting epoxy resin and is used for resisting vibration and preventing moisture.
The further technical scheme of the invention is as follows: the ignition controllers are mounted on the outer peripheral surface of the engine crankcase, and the number and the layout of the ignition controllers are determined according to the number, the layout and the ignition sequence of the engine cylinders.
Advantageous effects
The invention has the beneficial effects that:
1. the ignition controller is provided with the charging iron core and the trigger iron core, the induced potential generated in the charging coil can be enhanced by 50%, the electric quantity stored by a capacitor in the control circuit can be increased by 30%, the induced potential in the trigger coil can be increased by 30%, and the ignition energy of the spark plug can be increased by 20%;
2. the ignition controller is internally provided with the control circuit, alternating current can be converted into direct current, and the output current is smoother by adopting a parallel capacitor mode in the circuit, so that the charging and discharging voltage on the capacitor is more stable, the average value of the output direct current voltage is improved, the stability and sufficiency of the ignition energy of a spark plug are ensured, and the ignition reliability is improved;
3. the ignition controller can lead the ignition time to change along with the change of the rotating speed, because the rotating speed is lower, the induced current generated in the trigger coil changes slowly, the voltage value of the conduction silicon controlled rectifier generates later, therefore, the ignition time is triggered later, the voltage of the conduction silicon controlled rectifier generates earlier when the rotating speed is higher, therefore, the ignition time is triggered earlier, the ignition time under different rotating speeds can be adjusted without adjusting the position of the ignition controller, and the working performance of the engine under various rotating speeds is better;
4. the parking circuit is designed, so that the normal parking of the engine can be ensured, the electromagnetic interference of other electrical equipment on the unmanned aerial vehicle can be effectively prevented, the parking circuit can be used as one mode of the engine parking, and the normal parking of the engine can be ensured under the condition that other parking modes are abnormal;
5. the ignition controller has strong universality and can be used on a single-cylinder or multi-cylinder engine through different installation layouts.
Drawings
FIG. 1 is a schematic diagram of the structure and interface of the ignition controller of the present invention;
FIG. 2 is a control circuit diagram of the ignition controller of the present invention;
fig. 3 is a schematic view of two installations of the ignition controller of the present invention.
Description of reference numerals: the ignition device comprises a shell 1, a charging coil 2, a triggering coil 3, a charging iron core 4, a triggering iron core 5, an output port 6, a direct-current power supply positive electrode interface 7, a grounding port 8, an ignition controller 9 and an ignition rotor 10.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
As shown in fig. 1, an ignition controller for a small-sized aviation piston engine is provided, the structure of the ignition controller is composed of a shell 1, a charging coil 2, a trigger coil 3, a charging iron core 4, a trigger iron core 5 and a control circuit, the charging iron core 4 and the trigger iron core 5 after magnetization are respectively inserted into the charging coil 2 and the trigger coil 3, the iron core after magnetization also becomes a magnet, thus, the magnetic fields of the charging iron core 4 and the charging coil 2 after electrification are mutually superposed, the magnetic fields of the trigger iron core 5 and the trigger coil 3 are mutually superposed, the magnetic induction intensity of the charging coil 2 can be enhanced, the induction potential in the charging coil 2 can be increased, and the electric charge stored in a capacitor in the control circuit can be increased. The magnetic induction intensity of the trigger coil 3 is also enhanced, the induced potential in the trigger coil 3 can be increased, and the capacitor discharge can be controlled more reliably.
The ignition controller 9 is provided with an output port 6, a direct-current power supply positive electrode interface 7 and a grounding port 8 on the shell 1. The output port 6 of the ignition controller 9 is connected with a high-voltage ignition coil, the high-voltage ignition coil is connected with a spark plug of the cylinder, the positive electrode of the direct-current power supply is connected with the positive electrode interface 7 of the direct-current power supply, and the grounding port 8 of the direct-current power supply is connected with the negative electrode of the power supply.
As shown in fig. 2, a charging coil L1, a rectifying diode D1, D2 and capacitors C1, C2 in a control circuit of the ignition controller 9 are connected in sequence to form a charging circuit, diodes D1, D2 are connected in series, one end of the charging coil L1 is connected to the anode of the diode D1, the cathode of the diode D2 is connected to one ends of the capacitors C1, C2, the other end of the charging coil L1 is connected to the other ends of the capacitors C1, C2, and the capacitors C1, C2 are connected in parallel; the trigger circuit is formed by sequentially connecting a control electrode and a negative electrode of a trigger coil L2, a resistor R1 and a controlled silicon BG2, wherein the control electrode of the controlled silicon BG2 is connected with the resistor R1, the negative electrode of the BG2 is connected with a trigger coil L2, a rectifier diode D3 and a resistor R2 are connected with a trigger coil L2 in parallel, and a diode D4 is connected with the trigger circuit in parallel; the capacitors C1 and C2, the positive electrode and the negative electrode of the silicon controlled BG2, the output port and the high-voltage ignition coil are connected in sequence to form a discharge loop; direct current power supply positive pole interface, diode D5, resistance R3, the control pole of silicon controlled rectifier BG1, the ground connection port, diode D6, charging coil L1 links to each other and constitutes the parking return circuit, direct current power supply positive pole interface links to each other with diode D5's positive pole, silicon controlled rectifier BG 1's control pole links to each other with R3, BG 1's positive pole links to each other with charging coil L1 one end, the negative pole links to each other with the ground connection port, diode D6's positive pole, diode D6's negative pole links to each other with charging coil L1's the other end.
The operating principle of the ignition controller of the present invention is as follows:
when the permanent magnet of the ignition rotor 10 rotating synchronously with the crankshaft sweeps across the charging coil L1 of the ignition controller, in the charging circuit, due to the effect of the charging iron core 4 on the magnetic induction intensity enhancement, an alternating current with high amplitude is induced in the charging coil L1, the alternating current is rectified into a pulse direct current by the rectifier diodes D1 and D2, and the charges are stored in the capacitors C1 and C2.
When the ignition rotor 10 continues to rotate and the permanent magnet sweeps across the trigger coil L2 of the ignition controller on the trigger loop, alternating current is induced in the trigger coil L2, the voltage is divided and limited through R1, the generated induced voltage acts on the control electrode of the controllable silicon BG2, and when the voltage reaches a preset value, the controllable silicon BG2 is conducted.
After the silicon controlled BG2 is conducted, capacitors C1 and C2 on a discharge circuit input a pulse voltage to the high-voltage ignition coil through the conducted silicon controlled BG2, under the action of boosting of a secondary coil of the high-voltage ignition coil, high-energy electric sparks are generated between electrodes of a spark plug connected with the high-voltage ignition coil, and meanwhile, due to the unidirectional conduction action of diodes D1 and D2, the capacitors C1 and C2 are prevented from discharging to a charging coil L1. When the voltage applied to the control electrode of the controllable silicon BG2 is reduced to be less than a preset value, the controllable silicon BG2 is closed, the discharge circuit is disconnected, the capacitor stops discharging, and the spark plug also stops igniting.
When the engine needs to be parked, a direct-current power supply on a parking loop is switched on, the direct-current power supply acts on a control electrode of the controllable silicon BG1, the controllable silicon BG1 is switched on, a charging coil L1 is in short circuit, a spark plug stops igniting, the engine is parked, and the controllable silicon BG1 is switched off after the direct-current power supply is switched off.
The parallel capacitors C1 and C2 have the functions of increasing the capacitance and filtering besides charging and discharging, so that the output current is smoother, the charging and discharging voltage on the capacitors is more stable, the average value of the output direct-current voltage is improved, the stability and sufficiency of the ignition energy of the spark plug are ensured, and the ignition reliability is improved. The diode D3 is used for rectifying to generate voltage for conducting the thyristor BG2, and the resistors R1 and R2 are used for reducing reverse voltage borne by the thyristor BG2 and protecting thyristor elements.
As shown in fig. 3, the ignition controller 9 is mounted on the outer peripheral surface of the crankcase, and the peripheral surface thereof is coaxial with the ignition rotor 10, and the number and layout of the ignition controllers 9 are arranged at a certain angle according to the number, layout and firing order of the engine cylinders, and a set gap is reserved in the radial direction of the rotation circumference with the ignition rotor 10, so as to prevent the engine from malfunctioning due to collision with the charging core 4 and the trigger core 5 when the ignition rotor 10 rotates at a high speed. As shown in the left drawing of figure 3, only one ignition controller is needed to be installed to control the ignition of the cylinder in the small aviation two-stroke piston engine with a single cylinder or two cylinders arranged in a horizontally opposite mode, and the ignition controller 9 repeats the ignition working process once when the ignition rotor 10 rotates for 360 degrees, as shown in the right drawing of figure 3, two ignition controllers can be vertically installed at 180-degree intervals to respectively control the ignition of the front row of cylinders and the rear row of exhaust cylinders because the ignition moments of the front row of cylinders and the rear row of cylinders are 180-degree different, and the front row of cylinders and the rear row of exhaust cylinders respectively perform ignition once when the ignition rotor 10 rotates for 360 degrees, so that the working cycle of the ignition system is realized.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (4)
1. An ignition controller of a small-sized aviation piston engine, characterized in that: the charging coil and the trigger coil are respectively wound on the charging iron core and the trigger iron core and are arranged in the shell; the control circuit is arranged in the shell and comprises a charging loop, a triggering loop, a discharging loop and a parking loop;
the shell is provided with an output port, a direct-current power supply positive electrode interface and a grounding port, the output port is connected with a spark plug of an engine cylinder through a high-voltage ignition coil, the direct-current power supply positive electrode interface is connected with a direct-current power supply positive electrode, and the grounding port is connected with a direct-current power supply negative electrode.
2. An ignition controller for a small aviation piston engine as defined in claim 1, wherein: a charging coil L1, rectifier diodes D1 and D2 and capacitors C1 and C2 in the control circuit are sequentially connected to form a charging circuit, the diodes D1 and D2 are connected in series, one end of a charging coil L1 is connected with the anode of the diode D1, the cathode of a diode D2 is connected with one ends of the capacitors C1 and C2, the other end of the charging coil L1 is connected with the other ends of the capacitors C1 and C2, and the capacitors C1 and C2 are connected in parallel; the trigger circuit is formed by sequentially connecting a control electrode and a negative electrode of a trigger coil L2, a resistor R1 and a controlled silicon BG2, wherein the control electrode of the controlled silicon BG2 is connected with the resistor R1, the negative electrode of the BG2 is connected with a trigger coil L2, a rectifier diode D3 and a resistor R2 are connected with a trigger coil L2 in parallel, and a diode D4 is connected with the trigger circuit in parallel; the capacitors C1 and C2, the positive electrode and the negative electrode of the silicon controlled BG2, the output port and the high-voltage ignition coil are connected in sequence to form a discharge loop; direct current power supply positive pole interface, diode D5, resistance R3, the control pole of silicon controlled rectifier BG1, the ground connection port, diode D6, charging coil L1 links to each other and constitutes the parking return circuit, direct current power supply positive pole interface links to each other with diode D5's positive pole, silicon controlled rectifier BG 1's control pole links to each other with R3, BG 1's positive pole links to each other with charging coil L1 one end, the negative pole links to each other with the ground connection port, diode D6's positive pole, diode D6's negative pole links to each other with charging coil L1's the other end.
3. An ignition controller for a small aviation piston engine as defined in claim 1, wherein: the output port, the direct-current power supply positive interface and the grounding port are all assembled by adopting embedded nuts, and the joint of the output port, the direct-current power supply positive interface and the grounding port and the shell is sealed and filled by adopting epoxy resin and is used for resisting vibration and preventing moisture.
4. An ignition controller for a small aviation piston engine as defined in claim 1, wherein: the ignition controllers are mounted on the outer peripheral surface of the engine crankcase, and the number and the layout of the ignition controllers are determined according to the number, the layout and the ignition sequence of the engine cylinders.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020878737.4U CN212337513U (en) | 2020-05-22 | 2020-05-22 | Ignition controller of small-sized aviation piston engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202020878737.4U CN212337513U (en) | 2020-05-22 | 2020-05-22 | Ignition controller of small-sized aviation piston engine |
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| CN212337513U true CN212337513U (en) | 2021-01-12 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111456879A (en) * | 2020-05-22 | 2020-07-28 | 西北工业大学 | Ignition controller of small-sized aviation piston engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111456879A (en) * | 2020-05-22 | 2020-07-28 | 西北工业大学 | Ignition controller of small-sized aviation piston engine |
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