Variable-energy ignition circuit for aero-engine

Abstract

The invention discloses a variable-energy ignition circuit for an aero-engine, which is characterized in that a filter circuit, a DC-AC inverter booster circuit and an energy storage discharge circuit are connected in sequence, and the input end of the filter circuit is connected to a digital controller; the peak current sampling control circuit is respectively connected with the DC-AC inverter booster circuit and the digital controller, and the energy storage discharge circuit is also connected with the digital controller; the peak current sampling control circuit is used for controlling the peak current of the DC-AC inverter booster circuit; a digital controller is used for sampling a voltage value of an energy storage capacitor in an energy storage discharging circuit so as to analyze and calculate a charging voltage signal, and when the calculated charging voltage signal reaches a preset value, the digital controller outputs a discharging control signal to the energy storage discharging circuit. And the energy storage discharge circuit is controlled to be switched on and outputs a high-voltage pulse signal. The problems that due to the design of an existing ignition circuit, loads generated when an engine works in a normal state are increased, and the service life of an ignition electric nozzle is adversely affected are solved.

Description

Technical Field

[0001] The present invention relates to, but is not limited to, the technical field of aviation power supply, and in particular to a variable energy ignition circuit for aviation engines. Background Art

[0002] In the existing aircraft engine ignition circuit design process, the capacitance of the capacitor used for energy storage is a fixed value, and the breakdown voltage of the discharge switch fluctuates within a very small range. Therefore, after the parameters of the ignition device are fixed, the energy storage is basically a fixed value, and the spark energy output during ignition fluctuates within a certain small range.

[0003] In order to make the engine achieve better working performance within the entire working envelope, when designing the ignition device, the energy storage is usually designed to meet the maximum demand of extreme normal working conditions, so that the ignition system can work according to the maximum demand throughout its life cycle, thereby increasing the load on the engine when working in normal conditions and having a certain impact on the life of the ignition nozzle. Summary of the invention

[0004] Purpose of the present invention: In order to solve the above technical problems, the embodiments of the present invention provide a variable energy ignition circuit for aircraft engines to solve the problem that the existing ignition circuit has a constant energy storage and is usually designed to meet the maximum demand of the extreme normal working state, thereby increasing the load of the engine when working in the normal state and having an adverse effect on the life of the ignition nozzle.

[0005] Technical solution of the present invention: The embodiment of the present invention provides a variable energy ignition circuit for an aircraft engine, comprising: a digital controller, a filter circuit, a DC-AC inverter boost circuit, a peak current sampling control circuit and an energy storage discharge circuit;

[0006] Wherein, the filter circuit, DC-AC inverter boost circuit and energy storage discharge circuit are connected in sequence, and the input end of the filter circuit is connected to the digital controller, which is used to provide power to the variable energy ignition circuit through the digital controller;

[0007] The peak current sampling control circuit is connected to the DC-AC inverter boost circuit and the digital controller respectively, and the energy storage discharge circuit is also connected to the digital controller;

[0008] The variable energy ignition circuit is used to provide power to the variable energy ignition circuit through a digital controller, and to send a reference voltage signal to the peak current sampling control circuit through the digital controller, so as to control the peak current of the DC-AC inverter boost circuit through the peak current sampling control circuit;

[0009] The variable energy ignition circuit is also used to sample the voltage value on the energy storage capacitor in the energy storage discharge circuit through a digital controller to perform analysis and calculation of the charging voltage signal. When the calculated charging voltage signal reaches a predetermined value, the digital controller outputs a discharge control signal to the energy storage discharge circuit to control the energy storage discharge circuit to conduct and output a high-voltage pulse signal, that is, to control the discharge frequency.

[0010] Optionally, in the variable energy ignition circuit for an aircraft engine as described above,

[0011] The filter circuit is used to bidirectionally suppress the input power supply noise and the interference signal generated by the variable energy ignition circuit, ensuring the normal operation of the variable energy ignition circuit without interfering with the power supply;

[0012] The DC-AC inverter boost circuit adopts an independently excited DC-AC inverter boost circuit, which is used to convert input low-voltage direct current power into high-voltage alternating current pulse power.

[0013] Optionally, in the variable energy ignition circuit for an aircraft engine as described above,

[0014] The peak current sampling control circuit is used to sample the peak current of the DC-AC inverter boost circuit, and convert the collected peak current signal into a voltage signal, and compare it with the reference voltage signal output by the digital controller. When the sampled voltage signal is higher than the reference voltage signal, a high level signal is output; the DC-AC inverter boost circuit is controlled by the high level signal, the DC-AC inverter boost circuit stops working when the level is high, and the DC-AC inverter boost circuit works normally when the level is low.

[0015] Optionally, in the variable energy ignition circuit for an aircraft engine as described above,

[0016] The energy storage discharge circuit is used to convert the AC pulse electric energy output by the DC-AC inverter boost circuit into high-voltage DC electric energy and store it in the energy storage capacitor. When the voltage across the energy storage capacitor reaches the set discharge voltage, the discharge switch is turned on and a high-voltage signal is output.

[0017] Optionally, in the variable energy ignition circuit for an aircraft engine as described above,

[0018] By adding sampling resistors at both ends of the energy storage capacitor in the energy storage discharge circuit, the digital controller samples the voltage value on the energy storage capacitor, that is, samples the charging voltage signal, and controls the discharge control signal by analyzing and calculating the charging voltage signal to achieve the change of energy storage energy.

[0019] Optionally, in the variable energy ignition circuit for an aircraft engine as described above,

[0020] The digital controller is connected to the filter circuit, the peak current sampling control circuit and the energy storage discharge circuit through an electrical connector, the power line includes a positive power supply and a negative power supply, and the signal line includes a reference voltage signal line, a discharge control signal line, and a charging voltage signal line;

[0021] In the variable energy ignition circuit, the digital controller is connected to the filter circuit via a power line, connected to the peak current sampling control circuit via a reference voltage signal line, and connected to the energy storage discharge circuit via a discharge control signal line and a charging voltage signal line respectively;

[0022] The DC-AC inverter boost circuit is connected to the rear-end energy storage and discharge circuit via a boost transformer T1, and the input coil of the boost transformer T1 is also connected to a peak current sampling control circuit.

[0023] Optionally, in the variable energy ignition circuit for an aircraft engine as described above,

[0024] In the energy storage and discharge circuit, one end of an output coil of the step-up transformer T1 is connected to the positive electrode of the silicon stack D4, and the negative electrode of the silicon stack D4 is respectively connected to one end of the energy storage capacitor C10, one end of the voltage dividing resistor R13 and one end of the discharge tube V1, and the other end of the discharge tube V1 is grounded through a resistor R19 and connected to the output coil of the booster T3; the other end of the energy storage capacitor C10 is connected to the other end of the output coil and grounded, and one end of the other output coil is connected to a diode D5 and a resistor R11 in sequence, and the rear end of the resistor R11 is respectively connected to one end of the capacitor C11, the negative electrode of the diode D6 and one end of the input coil of the transformer T2, and the positive electrode of the diode D6 is respectively connected to the other end of the input coil of the transformer T2 and the positive electrode of the thyristor SCR2, and the thyristor SCR2 is connected to the digital controller through a discharge control signal line, and the discharge control signal line is grounded through a resistor R12, and the thyristor SC The negative electrode of R2 and the other end of the resistor R11 are both grounded, one end of the output coil of the transformer T2 is connected to the control end of the thyristor SCR3, the positive electrode of the thyristor SCR3 is connected to the other end of the voltage-dividing resistor R13, and the other end of the voltage-dividing resistor R13 is connected in series with the voltage-dividing resistors R14 to R18 in sequence, and is grounded through the voltage-dividing resistor R18, and the end of the voltage-dividing resistor R18 connected to R17 is connected to the digital controller through the charging voltage signal line, the positive electrode of the thyristor SCR3 is also connected to the negative electrode of D7 in the series diodes D7 to D9, the negative electrode of the diode D7 is grounded through the capacitor C12, the positive electrode of the diode D7 is connected between the voltage-dividing resistors R14 and R15, the positive electrode of the diode D8 is connected between the voltage-dividing resistors R15 and R16, the positive electrode of the diode D9 is connected to one end of the input coil of the booster T3 after being combined with the other end of the output coil of the transformer T2, and the other end of the input coil is grounded.

[0025] Optionally, in the variable energy ignition circuit for an aircraft engine as described above,

[0026] In the variable energy ignition circuit, after the input of the digital controller, it is first filtered by the filter circuit, and then converted into an AC pulse voltage signal by the DC-AC inverter circuit, and then converted into high-voltage AC by the step-up transformer T1; after being rectified by the silicon stack D4, a unidirectional high-voltage signal is formed to charge the energy storage capacitor C10; the other coil of the step-up transformer T1 is rectified by D5 to charge the capacitor C11, and the energy on the capacitor C11 is used to trigger the thyristor SCR3;

[0027] Through the voltage division of the voltage-dividing resistors R13 to R18, the voltage is sampled on the resistor R18 to obtain a charging voltage signal to reflect the charging voltage on the energy storage capacitor C10. After the charging voltage signal is fed back to the digital controller, the energy storage energy is analyzed based on the charging voltage signal to control the energy storage energy of the product;

[0028] The peak current sampling control circuit samples the current peak in the primary circuit of the step-up transformer T1 and converts it into a voltage signal, and receives the reference voltage signal from the digital controller. By comparing the two voltage signals, the control signal is output to control the working state of the DC-AC inverter circuit.

[0029] When the charging voltage signal detected by the digital controller meets the design requirements, the digital controller outputs a discharge control signal to turn on the thyristor SCR2, and turn on the thyristor SCR3 through the transformer T2 to form a discharge loop, and the energy stored in the energy storage capacitor C10 is released through the discharge loop.

[0030] Beneficial effects of the present invention: In a variable energy ignition circuit for an aircraft engine provided by an embodiment of the present invention, a digital controller not only provides power to the variable energy ignition circuit, but also provides a reference voltage signal to the peak current sampling control circuit to control the peak current; in addition, the voltage value on the energy storage capacitor in the energy storage discharge circuit is sampled by the digital controller to perform analysis and calculation of the charging voltage signal, and when the calculated charging voltage signal reaches a predetermined value, the digital controller outputs a discharge control signal to the energy storage discharge circuit. The variable energy ignition circuit provided in the embodiment of the present invention, on the one hand, collects the charging voltage signal on the energy storage capacitor in the energy storage discharge circuit, and sends a discharge control signal by calculating and analyzing the charging voltage signal to control the discharge frequency, thereby realizing the change of energy storage under the controlled discharge frequency, thereby realizing the change of spark energy, and realizing the use of smaller spark energy when the engine is ignited at room temperature. In relatively harsh environments such as high altitude and low temperature, the spark energy is increased by increasing the energy storage energy, thereby being able to better ignite the fuel and air mixture in the engine; on the other hand, by controlling the charging voltage and discharge frequency on the energy storage capacitor, the variable energy ignition circuit can be controlled to work in a small spark energy state for a part of the entire life cycle, thereby improving the reliability and life of the variable energy ignition circuit as a whole. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The accompanying drawings are used to provide a further understanding of the technical solution of the present invention and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present invention and do not constitute a limitation on the technical solution of the present invention.

[0032] Figure 1 , which is a schematic diagram of an existing ignition circuit of an aircraft engine;

[0033] Figure 2 A circuit block diagram of a variable energy ignition circuit for an aircraft engine provided by an embodiment of the present invention;

[0034] Figure 3 for Figure 2 The illustrated embodiment provides a circuit schematic diagram of a variable energy ignition circuit for an aircraft engine;

[0035] Figure 4 A schematic diagram of the circuit structure of a variable energy ignition circuit for an aircraft engine provided as an implementation example of the present invention. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments and features in the embodiments of the present application can be combined with each other arbitrarily without conflict.

[0037] The above background technology has explained the function and design principle of the ignition circuit in the aircraft engine. Since the energy storage is basically a fixed value, and the energy storage is usually designed to meet the maximum demand of the extreme normal working state, the ignition system works according to the maximum demand throughout the life cycle, thereby increasing the load of the engine when working in normal state, which has a certain impact on the life of the ignition nozzle.

[0038] like Figure 1 The figure shows a schematic diagram of an existing ignition circuit of an aircraft engine. After the ignition circuit is connected to the ignition power supply, the power supply signal is filtered through a filter, and the voltage signal is transmitted to the subsequent DC-AC inverter circuit, which is stepped up by the step-up transformer T1, and then rectified by the D1 rectifier silicon stack to charge the energy storage capacitor C1. When the voltage across the energy storage capacitor C1 reaches the breakdown voltage of the discharge tube V1, the discharge tube V1 breaks down and conducts, and the electric energy stored in the energy storage capacitor C1 is stepped up by the secondary step-up transformer T2 and released at the discharge end of the ignition nozzle to form an electric spark. Figure 1 The disadvantages of the existing ignition circuit shown are as follows: the energy storage is a fixed value and is designed according to the energy storage required under the limit state of the engine operating envelope. It is impossible to realize the change of energy storage under different working conditions, which will cause power waste.

[0039] In order to solve the above problems, an embodiment of the present invention provides a variable energy ignition circuit for an aircraft engine. The circuit collects the charging voltage signal on the energy storage capacitor in the energy storage discharge circuit, and sends a discharge control signal by calculating and analyzing the charging voltage signal to control the discharge frequency, thereby achieving a change in the energy storage under the controlled discharge frequency, thereby achieving a change in the spark energy, and achieving the use of a smaller spark energy when the engine is ignited at room temperature. In relatively harsh environments such as high altitude and low temperature, the spark energy is increased by increasing the energy storage energy, thereby better igniting the fuel and air mixture in the engine.

[0040] The present invention provides the following specific embodiments which can be combined with each other. The same or similar concepts or processes may not be described in detail in some embodiments.

[0041] Figure 2 The circuit block diagram of a variable energy ignition circuit for an aircraft engine provided by an embodiment of the present invention. Figure 2 As shown, the main structure of the variable energy ignition circuit for aircraft engines provided by the embodiment of the present invention includes: a filter circuit, a DC-AC inverter boost circuit, a peak current sampling control circuit and an energy storage discharge circuit.

[0042] like Figure 2 As shown, the filter circuit, the DC-AC inverter boost circuit and the energy storage discharge circuit are connected in sequence, and the input end of the filter circuit is connected to the digital controller, which is used to provide power to the variable energy ignition circuit through the digital controller.

[0043] The peak current sampling control circuit in the embodiment of the present invention is connected to the DC-AC inverter boost circuit and the digital controller respectively, and the energy storage discharge circuit is also connected to the digital controller.

[0044] Based on the circuit form of the variable energy ignition circuit provided in the above embodiment of the present invention, the digital controller provides power to the variable energy ignition circuit while also providing a reference voltage signal to the peak current sampling control circuit to control the peak current through the peak current sampling control circuit.

[0045] In addition, in an embodiment of the present invention, the digital controller samples the voltage value on the energy storage capacitor in the energy storage discharge circuit to perform analysis and calculation of the charging voltage signal. When the calculated charging voltage signal reaches a predetermined value, the digital controller outputs a discharge control signal to the energy storage discharge circuit, so that the variable energy ignition circuit output is turned on and outputs a high-voltage pulse signal, thereby realizing control of the discharge frequency.

[0046] In the embodiment of the present invention, the filter circuit performs bidirectional suppression on the input power supply noise and the interference signal generated by the operation of the variable energy ignition circuit, thereby ensuring that the variable energy ignition circuit operates normally and does not interfere with the power supply.

[0047] In the embodiment of the present invention, the DC-AC inverter boost circuit: adopts an independently excited DC-AC inverter boost circuit, whose function is to realize the conversion of input low-voltage DC power into high-voltage AC pulse power.

[0048] In an embodiment of the present invention, a peak current sampling control circuit is used to perform peak current sampling on a DC-AC inverter boost circuit, and convert the collected peak current signal into a voltage signal, and compare it with a reference voltage signal output by a digital controller. When the sampled voltage signal is higher than the reference voltage signal, a high level signal is output; the DC-AC inverter boost circuit is controlled by the high level signal, the DC-AC inverter boost circuit stops working when the level is high, and the DC-AC inverter boost circuit works normally when the level is low.

[0049] In an embodiment of the present invention, the energy storage discharge circuit is used to convert the AC pulse power output by the DC-AC inverter boost circuit into high-voltage DC power and store it in the energy storage capacitor. When the voltage across the energy storage capacitor reaches the set discharge voltage, the discharge switch is turned on and a high-voltage signal is output.

[0050] As follows Figure 2 The signals related to the digital controller are described in:

[0051] (1) Reference voltage signal: The voltage signal output by the digital controller is used to control the peak current value of the DC-AC inverter boost circuit.

[0052] (2) Discharge control signal: The voltage signal output by the digital controller is used to control the conduction of the energy storage discharge circuit, thereby controlling the discharge frequency.

[0053] (3) Charging voltage signal: By adding sampling resistors at both ends of the energy storage capacitor in the energy storage discharge circuit, the voltage value on the energy storage capacitor is sampled so that the change of energy storage energy can be achieved by controlling the discharge control signal.

[0054] In one implementation of the embodiment of the present invention, based on Figure 2 As shown in the circuit principle block diagram, the functions of each circuit are as follows: Figure 3 As shown, Figure 2 The illustrated embodiment provides a schematic diagram of the circuit principle of the variable energy ignition circuit for an aircraft engine. The digital controller is connected to the filter circuit, the peak current sampling control circuit and the energy storage discharge circuit through an electrical connector. The power line includes a positive power supply and a negative power supply. The signal line includes a reference voltage signal line, a discharge control signal line and a charging voltage signal line. In the variable energy ignition circuit, the digital controller is connected to the filter circuit through the power line, connected to the peak current sampling control circuit through the reference voltage signal line, and connected to the energy storage discharge circuit through the discharge control signal line and the charging voltage signal line respectively; in addition, the DC-AC inverter boost circuit is connected to the rear-end energy storage discharge circuit through the boost transformer T1, and the input coil of the boost transformer T1 is also connected to the peak current sampling control circuit.

[0055] In the energy storage and discharge circuit, one end of an output coil of the step-up transformer T1 is connected to the positive electrode of the silicon stack D4, and the negative electrode of the silicon stack D4 is respectively connected to one end of the energy storage capacitor C10, one end of the voltage divider resistor R13 and one end of the discharge tube V1. The other end of the discharge tube V1 is grounded through a resistor R19 and connected to the output coil of the booster T3; the other end of the energy storage capacitor C10 is connected to the other end of the output coil and grounded, one end of the other output coil is connected to a diode D5 and a resistor R11 in sequence, the rear end of the resistor R11 is respectively connected to one end of the capacitor C11, the negative electrode of the diode D6 and one end of the input coil of the transformer T2, the positive electrode of the diode D6 is respectively connected to the other end of the input coil of the transformer T2 and the positive electrode of the thyristor SCR2, the thyristor SCR2 is connected to the digital controller through a discharge control signal line, and the discharge control signal line is grounded through a resistor R12, and the thyristor SC The negative electrode of R2 and the other end of the resistor R11 are both grounded, one end of the output coil of the transformer T2 is connected to the control end of the thyristor SCR3, the positive electrode of the thyristor SCR3 is connected to the other end of the voltage-dividing resistor R13, and the other end of the voltage-dividing resistor R13 is connected in series with the voltage-dividing resistors R14 to R18 in sequence, and is grounded through the voltage-dividing resistor R18, and the end of the voltage-dividing resistor R18 connected to R17 is connected to the digital controller through the charging voltage signal line, the positive electrode of the thyristor SCR3 is also connected to the negative electrode of D7 in the series diodes D7 to D9, the negative electrode of the diode D7 is grounded through the capacitor C12, the positive electrode of the diode D7 is connected between the voltage-dividing resistors R14 and R15, the positive electrode of the diode D8 is connected between the voltage-dividing resistors R15 and R16, the positive electrode of the diode D9 is connected to one end of the input coil of the booster T3 after being combined with the other end of the output coil of the transformer T2, and the other end of the input coil is grounded.

[0056] After the power supply is input, it is first filtered by the filter circuit, and then converted into an AC pulse voltage signal through the DC-AC inverter circuit, and then converted into high-voltage AC through the step-up transformer T1; after being rectified by the silicon stack D4, a unidirectional high-voltage signal is formed to charge the energy storage capacitor C10; at the same time, the other coil of the step-up transformer T1 is rectified by D5 to charge the capacitor C11, and the energy on the capacitor C11 is used to trigger the thyristor SCR3; through the R13~R18 resistor voltage division, the charging voltage signal line is connected to the resistor R18 to perform voltage sampling on the resistor R18. The voltage signal is a charging voltage signal, which is used to reflect the charging voltage on the energy storage capacitor C10. After the charging voltage signal is fed back to the digital controller, the energy storage energy can be calculated and analyzed through the charging voltage signal, so as to control the energy storage energy of the product; the peak current sampling control circuit samples the current peak in the primary circuit of the step-up transformer T1 and converts it into a voltage signal, and at the same time receives the reference voltage signal given by the digital controller, and outputs a control signal by comparing the two voltage signals to control the working state (working / not working) of the DC-AC inverter circuit. When the charging voltage signal detected by the digital controller meets the design requirements, the digital controller outputs a discharge control signal to turn on the thyristor SCR2, and turn on the thyristor SCR3 through the transformer T2 to form a discharge circuit, and the energy stored in the energy storage capacitor C10 is released through the discharge circuit.

[0057] In the variable energy ignition circuit for an aircraft engine provided by an embodiment of the present invention, the digital controller not only provides power to the variable energy ignition circuit, but also provides a reference voltage signal to the peak current sampling control circuit to control the peak current; in addition, the voltage value on the energy storage capacitor in the energy storage discharge circuit is sampled by the digital controller to perform analysis and calculation of the charging voltage signal, and when the calculated charging voltage signal reaches a predetermined value, the digital controller outputs a discharge control signal to the energy storage discharge circuit. The variable energy ignition circuit provided in the embodiment of the present invention, on the one hand, collects the charging voltage signal on the energy storage capacitor in the energy storage discharge circuit, and sends a discharge control signal by calculating and analyzing the charging voltage signal to control the discharge frequency, thereby realizing the change of energy storage under the controlled discharge frequency, thereby realizing the change of spark energy, and realizing the use of smaller spark energy when the engine is ignited at room temperature. In relatively harsh environments such as high altitude and low temperature, the spark energy is increased by increasing the energy storage energy, thereby being able to better ignite the fuel and air mixture in the engine; on the other hand, by controlling the charging voltage and discharge frequency on the energy storage capacitor, the variable energy ignition circuit can be controlled to work in a small spark energy state for a part of the entire life cycle, thereby improving the reliability and life of the variable energy ignition circuit as a whole.

[0058] The implementation effect of the variable energy ignition circuit for an aircraft engine provided by an embodiment of the present invention is described below through an implementation case:

[0059] Implementation Cases

[0060] like Figure 4 As shown in FIG. 1 , a circuit structure diagram of a variable energy ignition circuit for an aircraft engine provided by an embodiment of the present invention is shown. Figure 4 As shown, in this implementation case, the DC-AC inverter circuit adopts an excitation switching circuit. After the power signal passes through the filter, one path is connected to the primary coil of the step-up transformer T1, and the other path is stabilized by the 7815 three-terminal regulator to output a 15V voltage. This voltage is used as a reference power supply to power integrated circuits such as the JB555 time base circuit and the LM139 voltage comparator; a 20kHz square wave signal is generated through the JB555 time base circuit and its peripheral circuits, and the periodic on and off of the MOS field effect tube Q1 is controlled by this signal; the peak current sampling control circuit is composed of resistors R7, R8, R10, capacitor C9, LM139 voltage comparator, diode D3 and thyristor SCR1, and the resistor R10 is connected in series in the primary circuit of the step-up transformer T1. After the current signal in the primary circuit passes through R10, a voltage is formed at both ends of R10. Signal, the peak current in the primary circuit is reflected by the voltage signal, and the voltage signal is compared with the reference voltage signal output by the digital controller. When the voltage signal is higher than the reference voltage, the LM139 voltage comparator outputs a high-level signal, and the high-level signal turns on the thyristor SCR1, and the output signal of the JB555 timing circuit forms a loop through the thyristor SCR1. The input voltage between the gate and source of the MOS field effect tube Q1 is zero, Q1 is turned off, the primary circuit is turned off, and the voltage on the resistor R10 is zero. The LM139 voltage comparator outputs a low-level signal, and the thyristor SCR1 is turned off. The output voltage signal of the JB555 timing circuit is applied between the gate and source of Q1, Q1 is turned on, the primary circuit is turned on to form a current, and a voltage signal is formed on the resistor R10. Through this circuit, a controllable DC-AC inverter boost circuit is formed.

[0061] Although the embodiments disclosed in the present invention are as above, the contents are only embodiments adopted to facilitate understanding of the present invention and are not intended to limit the present invention. Any technician in the field to which the present invention belongs can make any modifications and changes in the form and details of implementation without departing from the spirit and scope disclosed in the present invention, but the patent protection scope of the present invention shall still be subject to the scope defined in the attached claims.

Claims

1. A variable energy ignition circuit for an aircraft engine, characterized in that: include: Digital controller, filter circuit, DC-AC inverter boost circuit, peak current sampling control circuit and energy storage discharge circuit; Wherein, the filter circuit, DC-AC inverter boost circuit and energy storage discharge circuit are connected in sequence, and the input end of the filter circuit is connected to the digital controller, which is used to provide power to the variable energy ignition circuit through the digital controller; The peak current sampling control circuit is connected to the DC-AC inverter boost circuit and the digital controller respectively, and the energy storage discharge circuit is also connected to the digital controller; The variable energy ignition circuit is used to provide power to the variable energy ignition circuit through a digital controller, and to send a reference voltage signal to the peak current sampling control circuit through the digital controller, so as to control the peak current of the DC-AC inverter boost circuit through the peak current sampling control circuit; The variable energy ignition circuit is also used to sample the voltage value on the energy storage capacitor in the energy storage discharge circuit through a digital controller to perform analysis and calculation of the charging voltage signal. When the calculated charging voltage signal reaches a predetermined value, the digital controller outputs a discharge control signal to the energy storage discharge circuit to control the energy storage discharge circuit to conduct and output a high-voltage pulse signal, that is, to control the discharge frequency.

2. The variable energy ignition circuit for an aircraft engine according to claim 1, characterized in that: The filter circuit is used to bidirectionally suppress the input power supply noise and the interference signal generated by the variable energy ignition circuit, ensuring the normal operation of the variable energy ignition circuit without interfering with the power supply; The DC-AC inverter boost circuit adopts an independently excited DC-AC inverter boost circuit, which is used to convert input low-voltage direct current power into high-voltage alternating current pulse power.

3. The variable energy ignition circuit for an aircraft engine according to claim 1, characterized in that: The peak current sampling control circuit is used to sample the peak current of the DC-AC inverter boost circuit, and convert the collected peak current signal into a voltage signal, and compare it with the reference voltage signal output by the digital controller. When the sampled voltage signal is higher than the reference voltage signal, a high level signal is output; the DC-AC inverter boost circuit is controlled by the high level signal, the DC-AC inverter boost circuit stops working when the level is high, and the DC-AC inverter boost circuit works normally when the level is low.

4. The variable energy ignition circuit for an aircraft engine according to claim 1, characterized in that: The energy storage discharge circuit is used to convert the AC pulse electric energy output by the DC-AC inverter boost circuit into high-voltage DC electric energy and store it in the energy storage capacitor. When the voltage across the energy storage capacitor reaches the set discharge voltage, the discharge switch is turned on and a high-voltage signal is output.

5. The variable energy ignition circuit for an aircraft engine according to claim 4, characterized in that: By adding sampling resistors at both ends of the energy storage capacitor in the energy storage discharge circuit, the digital controller samples the voltage value on the energy storage capacitor, that is, samples the charging voltage signal, and controls the discharge control signal by analyzing and calculating the charging voltage signal to achieve the change of energy storage energy.

6. The variable energy ignition circuit for an aircraft engine according to any one of claims 1 to 5, characterized in that: The digital controller is connected to the filter circuit, the peak current sampling control circuit and the energy storage discharge circuit through an electrical connector, the power line includes a positive power supply and a negative power supply, and the signal line includes a reference voltage signal line, a discharge control signal line, and a charging voltage signal line; In the variable energy ignition circuit, the digital controller is connected to the filter circuit via a power line, connected to the peak current sampling control circuit via a reference voltage signal line, and connected to the energy storage discharge circuit via a discharge control signal line and a charging voltage signal line respectively; The DC-AC inverter boost circuit is connected to the rear-end energy storage and discharge circuit via a boost transformer T1, and the input coil of the boost transformer T1 is also connected to a peak current sampling control circuit.

7. The variable energy ignition circuit for an aircraft engine according to claim 6, characterized in that: In the energy storage and discharge circuit, one end of an output coil of the step-up transformer T1 is connected to the positive electrode of the silicon stack D4, and the negative electrode of the silicon stack D4 is respectively connected to one end of the energy storage capacitor C10, one end of the voltage dividing resistor R13 and one end of the discharge tube V1, and the other end of the discharge tube V1 is grounded through a resistor R19 and connected to the output coil of the booster T3; the other end of the energy storage capacitor C10 is connected to the other end of the output coil and grounded, and one end of the other output coil is connected to a diode D5 and a resistor R11 in sequence, and the rear end of the resistor R11 is respectively connected to one end of the capacitor C11, the negative electrode of the diode D6 and one end of the input coil of the transformer T2, and the positive electrode of the diode D6 is respectively connected to the other end of the input coil of the transformer T2 and the positive electrode of the thyristor SCR2, and the thyristor SCR2 is connected to the digital controller through a discharge control signal line, and the discharge control signal line is grounded through a resistor R12, and the thyristor SC The negative electrode of R2 and the other end of the resistor R11 are both grounded, one end of the output coil of the transformer T2 is connected to the control end of the thyristor SCR3, the positive electrode of the thyristor SCR3 is connected to the other end of the voltage-dividing resistor R13, and the other end of the voltage-dividing resistor R13 is connected in series with the voltage-dividing resistors R14 to R18 in sequence, and is grounded through the voltage-dividing resistor R18, and the end of the voltage-dividing resistor R18 connected to R17 is connected to the digital controller through the charging voltage signal line, the positive electrode of the thyristor SCR3 is also connected to the negative electrode of D7 in the series diodes D7 to D9, the negative electrode of the diode D7 is grounded through the capacitor C12, the positive electrode of the diode D7 is connected between the voltage-dividing resistors R14 and R15, the positive electrode of the diode D8 is connected between the voltage-dividing resistors R15 and R16, the positive electrode of the diode D9 is connected to one end of the input coil of the booster T3 after being combined with the other end of the output coil of the transformer T2, and the other end of the input coil is grounded.

8. The variable energy ignition circuit for an aircraft engine according to claim 7, characterized in that: In the variable energy ignition circuit, after the input of the digital controller, it is first filtered by the filter circuit, and then converted into an AC pulse voltage signal by the DC-AC inverter circuit, and then converted into high-voltage AC by the step-up transformer T1; after being rectified by the silicon stack D4, a unidirectional high-voltage signal is formed to charge the energy storage capacitor C10; the other coil of the step-up transformer T1 is rectified by D5 to charge the capacitor C11, and the energy on the capacitor C11 is used to trigger the thyristor SCR3; Through the voltage division of the voltage-dividing resistors R13 to R18, the voltage is sampled on the resistor R18 to obtain a charging voltage signal to reflect the charging voltage on the energy storage capacitor C10. After the charging voltage signal is fed back to the digital controller, the energy storage energy is analyzed based on the charging voltage signal to control the energy storage energy of the product; The peak current sampling control circuit samples the current peak in the primary circuit of the step-up transformer T1 and converts it into a voltage signal, and receives the reference voltage signal from the digital controller. By comparing the two voltage signals, the control signal is output to control the working state of the DC-AC inverter circuit. When the charging voltage signal detected by the digital controller meets the design requirements, the digital controller outputs a discharge control signal to turn on the thyristor SCR2, and turn on the thyristor SCR3 through the transformer T2 to form a discharge loop, and the energy stored in the energy storage capacitor C10 is released through the discharge loop.

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