An electronic history system for aircraft engine ignition actuator capable of self-detection and recording

Abstract

The present invention relates to the technical field of aircraft engine ignition starting, and in particular to an electronic resume system of an aircraft engine ignition exciter capable of self-detection and recording. The system accurately obtains the unsealing time, installation time, disassembly time, working times and working hours of the ignition exciter by setting a collection module, and calculates the remaining total life of the ignition exciter by setting a control module, thereby saving the labor cost and time cost of assembling the ignition exciter for the use and maintenance of the aircraft engine, and effectively improving the work efficiency of the maintenance and use of the aircraft engine ignition exciter.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine starting and ignition, in particular to an electronic resume system of an aircraft engine ignition exciter capable of self-detection and recording. Background Art

[0002] The aircraft engine ignition actuator logbook is a configuration-type user document that records the ignition actuator's manufacturing quality certification, technical status, and usage and maintenance information. The logbook is different from other technical data, and its usage and maintenance information needs to be recorded and updated in a timely manner according to the usage of the ignition actuator. Errors and omissions in the usage record of the ignition actuator may cause the product to be used beyond its service life, posing safety hazards or mission delays; errors and omissions in the usage record of the ignition actuator may also cause the product to be used at a reduced service life, resulting in waste of resources and increased costs. Therefore, updating the usage record in the ignition actuator logbook is a very important and necessary task, and the records need to be accurate without any errors or omissions.

[0003] The use records of traditional aircraft engine ignition exciters are recorded in paper logbooks. After leaving the factory, the engine is assembled and used. When each ignition exciter is installed and used, its paper logbook needs to be kept separately from the product. The use, loading and unloading, working hours and other records of the ignition exciter must be recorded manually in a paper logbook after each engine assembly and unloading. The use record work is complicated and consumes a lot of manpower and time costs. In addition, the work efficiency of the logbook is low, and there are often problems such as omissions and loss of the logbook, which may cause safety risks and waste of resources, and is also inconvenient to use. Summary of the invention

[0004] The present invention aims at the problems that the current paper resume books of aircraft engine ignition exciters are inconvenient for recording the use of assembled engines, have high labor and time costs, low recording efficiency, and are prone to errors and omissions. An electronic resume system for aircraft engine ignition exciters capable of self-detection and recording is proposed. An acquisition module is set to accurately obtain the unsealing time of the ignition exciter, the installation time of the ignition exciter, the disassembly time of the ignition exciter, the working times of the ignition exciter, and the working hours of the ignition exciter. A control module is set to calculate the remaining total life of the ignition exciter, thereby saving the labor cost and time cost of the ignition exciter assembly and maintenance of the aircraft engine, and effectively improving the work efficiency of the maintenance and use of the aircraft engine ignition exciter.

[0005] The specific implementation contents of the present invention are as follows:

[0006] An electronic history system for an aircraft engine ignition exciter capable of self-detection and recording is provided on the aircraft engine ignition exciter and comprises a collection module and a control module;

[0007] The input end of the acquisition module is connected to the engine ignition exciter, and the output end is connected to the control module;

[0008] The acquisition module is used to obtain the unsealing time of the ignition exciter, the installation time of the ignition exciter, the disassembly time of the ignition exciter, the working times of the ignition exciter, and the working hours of the ignition exciter;

[0009] The control module is used to calculate the remaining total life of the ignition exciter based on the ignition exciter unsealing time, ignition exciter installation time, ignition exciter disassembly time, ignition exciter working times, and ignition exciter working hours obtained from the acquisition module.

[0010] In order to better implement the present invention, further, the control module includes a single chip microcomputer;

[0011] The control logic in the single chip microcomputer includes:

[0012] Remaining total life = remaining working hours life / working times life / calendar life record;

[0013] Remaining working hours life = working hours life - used working hours;

[0014] Remaining working times life = working times life - used working times;

[0015] Remaining calendar life = calendar life - (current time - unsealing time).

[0016] In order to better implement the present invention, further, the acquisition module includes an unsealing time acquisition circuit;

[0017] The unsealing time acquisition circuit includes a photosensitive unit, a relay switch, and a clock unit;

[0018] The input end of the photosensitive unit inputs the ambient light signal, and the output end is connected to the input end of the control module;

[0019] The input end of the relay switch is connected to the output end of the photosensitive unit, and the output end of the relay switch is connected to the input end of the clock unit;

[0020] The output end of the clock unit outputs the unsealing time to the control module.

[0021] In order to better realize the present invention, further, the said self-detecting and recording aero-engine ignition exciter electronic resume system also includes a loading and unloading trigger installation structure;

[0022] The acquisition module includes a loading and unloading trigger acquisition circuit;

[0023] The loading and unloading trigger mounting structure includes a mounting screw, and the mounting screw is connected to the aircraft engine mounting base;

[0024] The input end of the loading and unloading triggering and collecting circuit is connected to the mounting screw, and the output end of the loading and unloading triggering and collecting circuit outputs the disassembly time to the control module.

[0025] In order to better implement the present invention, further, the loading and unloading trigger installation structure also includes an insulating coating, a metal coating, and a mounting hole;

[0026] The insulating coating is arranged on the surface of the aviation ignition exciter;

[0027] The metal coating is arranged on the surface of the insulating coating and is connected to the loading and unloading triggering and collecting circuit;

[0028] The mounting hole screw is mounted to the mounting hole of the ignition actuator and contacts the metal coating around the mounting hole, and the mounting screw is connected to the engine mounting base.

[0029] In order to better implement the present invention, further, the acquisition module also includes a working number acquisition circuit;

[0030] The working times acquisition circuit is used to rectify the high-voltage pulse electrical signal obtained from the aviation ignition exciter into a DC low-voltage signal, convert the DC low-voltage signal into a high-level signal when the aviation ignition exciter is working, and convert the DC low-voltage signal into a low-level signal when the aviation ignition exciter stops working; finally, the working times are generated according to the high-level signal.

[0031] In order to better implement the present invention, further, the acquisition module also includes a working hour acquisition circuit;

[0032] The working hour acquisition circuit is used to rectify the continuous pulse voltage signal obtained from the vibration sensor inside the aviation ignition exciter into DC switch information, generate working hours according to the DC switch information and output it to the control module.

[0033] In order to better implement the present invention, further, the electronic resume system of the aircraft engine ignition exciter capable of self-detection and recording also includes a display module;

[0034] The display module is arranged on the outer surface of the aviation ignition exciter and is connected to the output end of the control module.

[0035] The present invention has the following beneficial effects:

[0036] (1) The present invention sets a data acquisition circuit triggered by operation, illumination, installation, and vibration on the ignition exciter to realize automatic acquisition and recording of data such as the unsealing time, installation and disassembly time, number of operations, and working hours of the aviation ignition exciter. After being processed by the single-chip microcomputer central processing unit CPU, the data can be recorded and transmitted to a display screen to record and display the unsealing time, installation and disassembly time, number of operations, working hours, remaining life, and other usage history of the ignition exciter.

[0037] (2) The present invention arranges a display screen to be assembled on the outer surface of the ignition exciter, thereby detecting and automatically recording the loading and unloading time, working hours, calendar life and other usage records of the ignition exciter, thereby avoiding the problems of complicated manual recording work in traditional paper resumes, manual recording errors and omissions, and loss of paper resumes. The present invention has the characteristics of convenient recording operation, automatic recording, and accurate recording, which can save the labor cost and time cost of assembling the upper unit of the ignition exciter for use and maintenance, and effectively improve the work efficiency of the maintenance and use of the upper unit ignition exciter. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 This is a schematic diagram of the overall circuit structure provided by the present invention.

[0039] Figure 2 It is a schematic diagram of the structure of the unsealing time acquisition circuit provided by the present invention.

[0040] Figure 3 It is a schematic diagram of the structure of the loading and unloading time collection circuit provided by the present invention.

[0041] Figure 4 It is a schematic diagram of the first part of the structure of the working number acquisition circuit provided by the present invention.

[0042] Figure 5 It is a schematic diagram of the second part of the structure of the working number acquisition circuit provided by the present invention.

[0043] Figure 6 It is a schematic diagram of the structure of the working hour collection circuit provided by the present invention.

[0044] Figure 7 It is a schematic diagram of the appearance installation structure provided by the present invention.

[0045] Figure 8 It is a schematic diagram of the loading and unloading trigger structure provided by the present invention.

[0046] Fig. 9 It is a schematic diagram of the battery charging circuit structure provided by the present invention.

[0047] Among them, 1. Metal coating, 2. Mounting hole, 3. Insulation coating, 4. Display screen, 5. Photovoltaic panel. DETAILED DESCRIPTION

[0048] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. It should be understood that the described embodiments are only part of the embodiments of the present invention, not all of the embodiments, and therefore should not be regarded as limiting the scope of protection. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technical personnel in this field without making creative work are within the scope of protection of the present invention.

[0049] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "disposed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0050] Embodiment 1:

[0051] This embodiment provides an electronic history system for an aircraft engine ignition actuator that can self-detect and record. Figure 4 As shown, taking a high-voltage and high-energy ignition exciter, i.e., an energy storage igniter, and a certain type of low-voltage AC input energy storage ignition system as an example, the main parameters of the energy storage ignition system are as follows:

[0052] Power input: 110~115V / 380~420Hz;

[0053] Output voltage: voltage peak value is not less than 15kV;

[0054] Peak current: not less than 2000A;

[0055] Spark frequency: 2±0.5Hz;

[0056] Total lifespan: 500 engine operating hours / 1000 times / 10 years.

[0057] like Figure 4 , Figure 5 , Figure 6 As shown, the circuit structure of the ignition exciter is mainly composed of three parts: an AC boost module, a rectifier voltage doubler energy storage module, and a discharge module.

[0058] The circuit components mainly include:

[0059] Suppressor: including filter inductors L01, L02 and through-hole capacitors C01, C02, which play the role of current regulation, control the input power and spark efficiency of the ignition exciter; and can prevent the low-frequency signal and high-frequency signal of the ignition exciter from pouring into the aircraft power system and interfering with other equipment;

[0060] Transformer T1: includes primary winding and secondary winding, which increases the 110-115V AC to about 2120V;

[0061] High temperature diodes D1 and D2: used to rectify and multiply the voltage of AC signals;

[0062] Energy storage capacitor C5: used for energy storage;

[0063] Voltage doubling capacitors C4 and C3: used to charge the energy storage capacitor C5;

[0064] Discharge resistor R2: used to gradually discharge the remaining charge in the energy storage capacitor C5 when the ignition exciter is powered off. It has a large resistance value, but plays a small role in the normal operation of the igniter.

[0065] Current limiting resistor R1: used to limit the charging current of capacitor C4;

[0066] Current limiting resistor R3: used to limit the charging current of high-frequency oscillation capacitor C6;

[0067] High frequency transformer T2;

[0068] High-frequency oscillation capacitor C6: used for energy storage, breaking down the discharge tube G1 and the ignition nozzle through the high-frequency transformer T2 to form an ignition circuit path.

[0069] Discharge tube G1: It is used to separate the ignition nozzle circuit from the energy storage capacitor C5, so that when the working conditions of the nozzle change, the energy storage capacitor C6 can be charged to the specified breakdown voltage without being affected by the working conditions of the ignition nozzle;

[0070] Safety resistor R2: The resistance is very large, so that the discharge tube G1 can directly sense the voltage of the energy storage capacitor C5. When the high-frequency transformer T2 and the voltage-doubling capacitor C3 fall off, it can provide a discharge channel for the energy storage capacitor C5 to prevent C5 from being charged to a voltage value that endangers safety and breaks down the energy storage capacitor C5.

[0071] Its specific working process is: when the ignition exciter power supply is input, when the induced voltage on the secondary winding is positive at the upper end and negative at the lower end, before the voltage peak arrives, the high-temperature diode D2 is turned on, the high-temperature diode D1 is turned off, and the branch formed by the voltage-doubling capacitor C3, the energy storage capacitor C5 and the voltage-doubling capacitor C4 in series is charged; at a certain moment after the voltage crosses the peak, the voltage on the voltage-doubling capacitor C3 is greater than the output voltage of the secondary winding, the high-temperature diode D1 is turned on, the high-temperature diode D2 is turned off, the voltage-doubling capacitor C3 is discharged through the energy storage capacitor C3 through the secondary winding, and the voltage-doubling capacitor C4 continues to charge the energy storage capacitor C5; when the induced voltage on the secondary winding is negative at the upper end and positive at the lower end When the voltage peak arrives, the high temperature diode D1 is turned on and the high temperature diode D2 is turned off, charging the branch formed by the voltage doubling capacitor C4, the energy storage capacitor C5 and the voltage doubling capacitor C3 in series; at a certain moment after the voltage passes the peak, the voltage on the voltage doubling capacitor C4 is greater than the output voltage of the secondary winding, the high temperature diode D2 is turned on, the high temperature diode D1 is turned off, the voltage doubling capacitor C4 is discharged through the energy storage capacitor C5 through the secondary winding, and the voltage doubling capacitor C3 continues to charge the energy storage capacitor C5; the secondary winding induced voltage alternates between positive and negative half cycles, and no matter how the induced voltage changes, the energy storage capacitor C5 is always in a charging state, and its voltage shows an intermittent upward trend. At the same time, the high frequency oscillation capacitor C6 is also charged through the primary of the high frequency transformer T2 and the current limiting resistor R2. As the number of charging times increases, the voltage on the energy storage capacitor C5 and the high frequency oscillation capacitor C6 gradually rises. When the high-frequency oscillation capacitor C6 rises to the threshold voltage of the discharge tube G1, it will break through the discharge tube G1 and enter the discharge link. The voltage on the high-frequency oscillation capacitor C6 is applied to the primary of T2, and a high voltage of (15~20)kV is generated on its secondary, breaking through the ignition nozzle, so that the electric energy stored in the energy storage capacitor C5 is discharged through the discharge path formed by the discharge tube G1, the secondary of the high-frequency transformer T2, the ignition cable, and the ignition nozzle. At the same time, a discharge spark is formed at the ignition end of the ignition nozzle to complete the ignition.

[0072] The electronic resume system of the aircraft engine ignition actuator capable of self-detection and recording proposed in this embodiment is arranged on the aircraft engine ignition actuator, and includes a collection module, a control module, and a display module;

[0073] The input end of the acquisition module is connected to the engine ignition exciter, and the output end is connected to the control module;

[0074] The acquisition module is used to obtain the unsealing time of the ignition exciter, the installation time of the ignition exciter, the disassembly time of the ignition exciter, the working times of the ignition exciter, and the working hours of the ignition exciter;

[0075] The control module is used to calculate the remaining total life of the ignition exciter based on the ignition exciter unsealing time, ignition exciter installation time, ignition exciter disassembly time, ignition exciter working times, and ignition exciter working hours obtained from the acquisition module.

[0076] The control module includes a single chip microcomputer;

[0077] The control logic in the single chip microcomputer includes:

[0078] Remaining total life = remaining working hours life / working times life / calendar life record;

[0079] Remaining working hours life = working hours life - used working hours;

[0080] Remaining working times life = working times life - used working times;

[0081] Remaining calendar life = calendar life - (current time - unsealing time).

[0082] Working principle: Figure 1 As shown, the electronic resume of the aircraft engine ignition exciter for automatic detection and recording includes an unsealing trigger collection circuit, a loading and unloading trigger collection circuit, a working number trigger collection circuit, and a working hour trigger collection circuit. Figure 1 As shown, these circuits are triggered when the ignition exciter is used, and the data is automatically collected and transmitted to the single-chip microcomputer. After the single-chip microcomputer calculates and processes, the recorded results are displayed on the display screen 4 on the surface of the ignition exciter.

[0083] This embodiment sets a data acquisition circuit triggered by work, lighting, installation, and vibration on the ignition exciter to realize automatic acquisition and recording of data such as the unsealing time, installation and disassembly time, working times, working hours, etc. of the aviation ignition exciter. After being processed by the single-chip microcomputer central processing unit CPU, the data can be recorded and transmitted to the display screen 4 to record and display the usage history of the ignition exciter such as the unsealing time, installation and disassembly time, working times, working hours, and remaining life.

[0084] Embodiment 2:

[0085] This embodiment is based on the above embodiment 1. Figure 2 As shown, the acquisition module includes an unsealing time acquisition circuit.

[0086] The unsealing time acquisition circuit includes a photosensitive unit, a relay switch, and a clock unit;

[0087] The input end of the photosensitive unit inputs the ambient light signal, and the output end is connected to the input end of the control module;

[0088] The input end of the relay switch is connected to the output end of the photosensitive unit, and the output end of the relay switch is connected to the input end of the clock unit;

[0089] The output end of the clock unit outputs the unsealing time to the control module.

[0090] like Figure 2 As shown, the photoresistor LRD is installed on the surface of the ignition actuator. The ignition actuator is in a dark light state in the packaging box, and is in a light state after being removed from the packaging box and unsealed. The photoresistor LRD is in a high resistance state in the dark light, and in a low resistance state when illuminated.

[0091] When unsealing, the photoresistor R1 on the surface of the product becomes smaller, and the voltage on R2 becomes larger, triggering the relay switch to turn on, triggering the clock to record the unsealing time. The microcontroller is set to record the unsealing time only once. After triggering and recording the unsealing time once, the unsealing time record will not be triggered repeatedly. After returning to the factory and before repackaging, the microcontroller setting can be reset and retriggered.

[0092] The other parts of this embodiment are the same as those of the above-mentioned embodiment 1, and thus will not be described in detail.

[0093] Embodiment 3:

[0094] This embodiment is based on any one of the above embodiments 1 to 2. Figure 4 As shown, the acquisition module also includes a loading and unloading trigger acquisition circuit, and the self-detecting and recording aircraft engine ignition exciter electronic history system also includes a loading and unloading trigger installation structure.

[0095] The loading and unloading trigger mounting structure includes a mounting screw, and the mounting screw is connected to the aircraft engine mounting base;

[0096] The input end of the loading and unloading triggering and collecting circuit is connected to the mounting screw, and the output end of the loading and unloading triggering and collecting circuit outputs the disassembly time to the control module.

[0097] like Figure 3 As shown in the figure, when the ignition exciter is installed on the engine, the installation of the mounting hole screw triggers S1 to turn on, the resistor R3 is at a high level, the relay switch is turned on, and the clock is triggered to record the installation time of the ignition exciter. When the ignition exciter is removed from the engine, the mounting screw is unscrewed to trigger S1 to disconnect, the resistor R3 is at a low level, the relay switch is disconnected, and the clock is triggered to record the removal time of the ignition exciter. The loading and unloading time can be repeatedly triggered to record multiple installation and disassembly times.

[0098] The ignition exciter loading and unloading trigger installation structure is as follows Figure 7 , Figure 8 As shown, a layer of insulating coating 3 is first sprayed on the surface of the ignition exciter, and then a metal coating 1 is sprayed on the surface of the insulating coating 3 as shown in the figure. The metal coating 1 is a conductive path, and the other end is connected to the Figure 3 The resistor R3 in the circuit is connected. When not installed on the engine, the metal coating 1 is not grounded, that is, Figure 4S1 in the circuit is in the disconnected state. When the ignition exciter is installed on the engine, the mounting hole screw is installed to the ignition exciter mounting hole 2 and contacts the metal coating 1 around the mounting hole 2. At the same time, the mounting screw is connected to the engine mounting base, and the engine mounting base is the reference voltage, that is, grounded. The mounting screw contacts the metal coating 1 and the ground at the same time, that is, Figure 4 The S1 switch in the circuit is turned on. Figure 8 Ignition actuator mounting structure, the ignition actuator is mounted on the engine through the mounting screws. Figure 4 The S1 switch in the circuit is turned on, and the screws are removed from the engine. Figure 3 The S1 switch in the circuit is open.

[0099] The other parts of this embodiment are the same as any one of the above-mentioned embodiments 1-2, so they will not be repeated here.

[0100] Embodiment 4:

[0101] This embodiment is based on any one of the above embodiments 1 to 3. Figure 4 , Figure 5 As shown, the acquisition module also includes a working times acquisition circuit.

[0102] The working times acquisition circuit is used to rectify the high-voltage pulse electrical signal obtained from the aviation ignition exciter into a DC low-voltage signal, convert the DC low-voltage signal into a high-level signal when the aviation ignition exciter is working, and convert the DC low-voltage signal into a low-level signal when the aviation ignition exciter stops working; finally, the working times are generated according to the high-level signal.

[0103] Working principle: Figure 4 , Figure 5 As shown, when the ignition exciter is working, the output is high-voltage pulse electricity. A transformer T2 or a mutual inductance coil is installed on the internal output circuit of the ignition exciter to collect the output low pulse voltage, and the DC low-voltage signal is rectified by the inductor L1 and the capacitor C7. Every time the ignition exciter works, the output is a high-level signal; when the ignition exciter stops working, there is no voltage and the output is a low-level signal. Each time a high-level signal triggers the counter to count once, that is, the ignition exciter works once and triggers the counter to count once. The number of working times is recorded and transmitted to the single-chip microcomputer for storage and processing, and the cumulative number of times is the number of working times used by the ignition exciter. The number of working times only records the cumulative number of working times.

[0104] The other parts of this embodiment are the same as any one of the above-mentioned embodiments 1 to 3, so they will not be repeated here.

[0105] Embodiment 5:

[0106] This embodiment is based on any one of the above embodiments 1 to 4. Figure 6As shown, the acquisition module also includes a working hour acquisition circuit.

[0107] The working hour acquisition circuit is used to rectify the continuous pulse voltage signal obtained from the vibration sensor inside the aviation ignition exciter into DC switch information, generate working hours according to the DC switch information and output it to the control module.

[0108] like Figure 6 As shown, when the ignition exciter works with the engine, the engine will generate continuous vibration. A vibration sensor is installed inside the ignition exciter. When vibrating, the vibration sensor outputs a continuous pulse voltage signal, which is amplified by T3. The voltage is rectified into DC switch information by inductor L2 and capacitor C8, triggering the relay switch clock to start recording the working hours. When the engine stops working, the vibration sensor cannot detect vibration, stops outputting pulse voltage signals, and triggers the clock to end the working hour record. The working hour record is transmitted to the microcontroller for storage, and the accumulated working hours of the ignition exciter are used. The working hours only record the accumulated working hours.

[0109] The remaining total life of the ignition exciter is recorded, and the remaining total life = total life - used life. The life of the ignition exciter is divided into calendar life, working hour life, and working number life. The used calendar life = current time - unsealing time. The single-chip microcomputer has collected and stored the total life, unsealing time, used working hours, and used working number of the ignition exciter, and then the single-chip microcomputer calculates and processes to output the remaining total life of the ignition exciter. The single-chip microcomputer calculation logic is as follows:

[0110] Remaining total life = Remaining working hours life / working times life / calendar life record

[0111] Remaining working hours life = 500 hours - used working hours

[0112] Remaining working times life = 1000 times - used working times

[0113] Remaining calendar life = 10 years - (current time - unsealing time)

[0114] The automatic detection and recording electronic logbook of the aviation engine ignition exciter has an automatic detection and recording function, as shown in Table 1 below.

[0115] Table 1 Implementation function correspondence table

[0116]

[0117]

[0118] The total life of the ignition exciter with an automatic electronic logbook is 500 engine operating hours / 1000 times / 10 years. For example, the ignition exciter was unpacked from the packaging box and installed on the engine on January 1, 2022. After 20 hours / 40 times of commissioning in the engine factory, it was assembled on the aircraft with the engine on February 1, 2022. After flying 100 times with the aircraft and about 200 flight hours, it was disassembled from the aircraft for maintenance inspection on February 1, 2023. At this time, the use history of this ignition exciter can be viewed through the display screen 4 on the ignition exciter as shown in Table 2 below.

[0119] Table 2 Usage history record display table

[0120]

[0121] During the installation and use of this ignition exciter, the use history of the ignition exciter can be updated in real time, and the use history of the ignition exciter can be viewed through the electronic history book of the ignition exciter, without any manual record in the middle. The traditional paper history book of the ignition exciter needs to be recorded in the paper history book after each flight. Manual recording is cumbersome, inconvenient, and prone to errors. This electronic history book of the aircraft engine ignition exciter with automatic detection and recording is installed on the ignition exciter and does not need to be kept separately. It is easy to carry, store and use. It has the characteristics of convenient recording operation, automatic recording, and accurate recording. It can save the labor cost and time cost of assembling the ignition exciter for the use and maintenance of the aircraft engine, and effectively improve the use and maintenance efficiency of the aircraft engine ignition exciter.

[0122] The other parts of this embodiment are the same as any one of the above-mentioned embodiments 1 to 4, so they are not repeated here.

[0123] Embodiment 6:

[0124] This embodiment is based on any one of the above embodiments 1 to 5, but the display screen 4 is eliminated, the ignition actuator usage record is stored in the single-chip microcomputer storage unit, and the ignition actuator usage record data is read through the serial port each time.

[0125] The other parts of this embodiment are the same as any one of the above-mentioned embodiments 1 to 5, so they will not be repeated here.

[0126] Embodiment 7:

[0127] This embodiment is based on any one of the above embodiments 1 to 6. Fig. 9 As shown, the display screen 4 is cancelled, the use history record of the ignition exciter is stored in the single-chip computer storage unit, and a Bluetooth wireless data transmission unit is added, and the use history record data of the ignition exciter can be read by scanning the QR code wireless connection.

[0128] Cancel photovoltaic panel 5 and increase Fig. 9 The battery charging circuit charges the battery every time the ignition exciter works.

[0129] The other parts of this embodiment are the same as any one of the above-mentioned embodiments 1 to 6, so they will not be repeated here.

[0130] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent change made to the above embodiment based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. An electronic history system for an aircraft engine ignition actuator capable of self-detection and recording, characterized in that: It is arranged on the aircraft engine ignition exciter and includes a collection module and a control module; The input end of the acquisition module is connected to the engine ignition exciter, and the output end is connected to the control module; The acquisition module is used to obtain the unsealing time of the ignition exciter, the installation time of the ignition exciter, the disassembly time of the ignition exciter, the working times of the ignition exciter, and the working hours of the ignition exciter; The control module is used to calculate the remaining total life of the ignition exciter based on the ignition exciter unsealing time, ignition exciter installation time, ignition exciter disassembly time, ignition exciter working times, and ignition exciter working hours obtained from the acquisition module.

2. The electronic history system of an aircraft engine ignition actuator capable of self-detection and recording according to claim 1, characterized in that: The control module includes a single chip microcomputer; The control logic in the single chip microcomputer includes: Remaining total life = remaining working hours life / working times life / calendar life record; Remaining working hours life = working hours life - used working hours; Remaining working times life = working times life - used working times; Remaining calendar life = calendar life - (current time - unsealing time).

3. The electronic history system of an aircraft engine ignition actuator capable of self-detection and recording according to claim 1, characterized in that: The acquisition module includes an unsealing time acquisition circuit; The unsealing time acquisition circuit includes a photosensitive unit, a relay switch, and a clock unit; The input end of the photosensitive unit inputs the ambient light signal, and the output end is connected to the input end of the control module; The input end of the relay switch is connected to the output end of the photosensitive unit, and the output end of the relay switch is connected to the input end of the clock unit; The output end of the clock unit outputs the unsealing time to the control module.

4. The electronic history system of an aircraft engine ignition actuator capable of self-detection and recording according to claim 1, characterized in that: The electronic resume system of the aviation engine ignition exciter capable of self-detection and recording also includes a loading and unloading trigger installation structure; The acquisition module includes a loading and unloading trigger acquisition circuit; The loading and unloading trigger mounting structure includes a mounting screw, and the mounting screw is connected to the aircraft engine mounting base; The input end of the loading and unloading triggering and collecting circuit is connected to the mounting screw, and the output end of the loading and unloading triggering and collecting circuit outputs the disassembly time to the control module.

5. The electronic history system of an aircraft engine ignition actuator capable of self-detection and recording according to claim 3, characterized in that: The loading and unloading trigger installation structure further comprises an insulating coating (3), a metal coating (1), and a mounting hole (2); The insulating coating (3) is arranged on the surface of the aviation ignition exciter; The metal coating (1) is arranged on the surface of the insulating coating (3) and is connected to the loading and unloading triggering and collecting circuit; The mounting hole screw is mounted to the ignition exciter mounting hole (2) and contacts the metal coating (1) around the mounting hole (2), while the mounting screw is connected to the engine mounting base.

6. The electronic history system of an aircraft engine ignition actuator capable of self-detection and recording according to claim 1, characterized in that: The acquisition module also includes a working times acquisition circuit; The working times acquisition circuit is used to rectify the high-voltage pulse electrical signal obtained from the aviation ignition exciter into a DC low-voltage signal, convert the DC low-voltage signal into a high-level signal when the aviation ignition exciter is working, and convert the DC low-voltage signal into a low-level signal when the aviation ignition exciter stops working; finally, the working times are generated according to the high-level signal.

7. The electronic history system of an aircraft engine ignition actuator capable of self-detection and recording according to claim 1, characterized in that: The acquisition module also includes a working hour acquisition circuit; The working hour acquisition circuit is used to rectify the continuous pulse voltage signal obtained from the vibration sensor inside the aviation ignition exciter into DC switch information, generate working hours according to the DC switch information and output it to the control module.

8. The electronic history system of an aircraft engine ignition actuator capable of self-detection and recording according to claim 1, characterized in that: The electronic resume system of the aviation engine ignition exciter capable of self-detection and recording also includes a display module; The display module is arranged on the outer surface of the aviation ignition exciter and is connected to the output end of the control module.

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