Integrated data acquisition compression ignition aeroengine, control method and storage medium

Abstract

The application relates to the technical field of engines, in particular to an integrated data acquisition type compression ignition aero-engine, a control method and a storage medium. Strain gauges are used to measure the strain of a piston surface, a first thermocouple is used to measure the temperature of the piston surface, and a second thermocouple is used to measure the surface temperature of an oil pan. When the surface temperature of the oil pan is monitored to be relatively high, high-temperature oil vapor and / or air mixture above the oil pan is transported to a cooler through an electric pump, and then is returned to the oil pan after being cooled, so that the temperature around the piston skirt is prevented from being too high to cause damage to the built-in data acquisition device of the engine, and the problem of how to accurately and stably acquire relevant data of the compression ignition aero-engine is solved.

Description

Technical Field

[0001] This invention relates to the field of engine technology, and in particular to an integrated data acquisition compression ignition aero-engine, control method, and storage medium. Background Technology

[0002] In recent years, with the rapid development of my country's general aviation industry, compression ignition aircraft engines have been widely used in my country's general aviation field due to their advantages such as low fuel consumption, good altitude characteristics, low cost, high reliability, and long endurance.

[0003] Because the operating environment of engines in the aviation field is relatively complex, when operating under harsh conditions at high altitudes, the low atmospheric pressure and temperature result in less air intake and lower air intake temperature, which reduces the effective combustion in the cylinder. This leads to the transfer of heat to engine components, causing the piston surface of core engine components to become too hot, resulting in phenomena such as head erosion, pin seat cracking, ring groove charring, and skirt deformation and cracking.

[0004] In order to study pistons and avoid the above-mentioned phenomena, an integrated data acquisition compression ignition aero-engine that can accurately and stably acquire relevant internal data is needed.

[0005] The above content is only used to help understand the technical solution of the present invention and does not represent an admission that the above content is prior art. Summary of the Invention

[0006] The main objective of this invention is to provide an integrated data acquisition compression ignition aero-engine, which aims to solve the problem of how to accurately acquire relevant data of compression ignition aero-engines.

[0007] To achieve the above objectives, the present invention provides an integrated data acquisition compression ignition aero-engine, which includes: an engine casing (1), a piston (2), a first thermocouple (3), a cylinder wall (4), a first wireless charging receiver module (5), a first wireless charging transmitter module (6), a microprocessor circuit (7), a first thermal insulation enclosure (8), a battery (9), an electronic control unit (10), a cooler (11), a signal receiving module (12), a second wireless charging transmitter module (13), a second radio receiver module (14), a second thermocouple (15), an oil pan (16), an electric pump (17), a crankshaft (18), a connecting rod (19), a patch temperature control switch (20), a second thermal insulation enclosure (21), a high-temperature resistant battery (22), and a strain gauge (23).

[0008] The cylinder wall (4) is located inside the engine housing (1), the piston (2) and the first thermocouple (3) are located inside the cylinder wall (4), and the first thermocouple (3) is located on the surface of the piston (2) and connected to the microprocessor circuit (7) through a circuit. The microprocessor circuit (7) is located inside the first heat insulation encapsulation box (8), and the microprocessor circuit (7) is also connected to the patch temperature control switch (20) through another circuit. The patch temperature control switch (20) is close to the bottom of the second heat insulation encapsulation box (21). The second heat insulation encapsulation box (21) is equipped with a high-temperature resistant battery (22). The circuit of the high-temperature resistant battery (22) passes through the connecting rod (19) and is connected to the second radio receiver module (14) located at the bottom of the connecting rod (19) inside the connecting rod (19).

[0009] The strain gauge (23) is symmetrically arranged with the first thermocouple (3) and connected to the microprocessor circuit (7) through the circuit;

[0010] The crankshaft (18) is mounted on the lower outer side of the connecting rod (19) via a mounting base;

[0011] The first wireless charging receiver module (5) and the first wireless charging transmitter module (6) are installed at intervals on the outer side of the connecting rod (19);

[0012] The signal receiving module (12), the second wireless charging transmitting module (13), and the second thermocouple (15) are disposed inside the oil pan (16). The second wireless charging transmitting module (13) and the second radio receiving module (14) are disposed at intervals. The signal receiving module (12), the second wireless charging transmitting module (13), and the second thermocouple (15) are all connected to the battery (9) and the electronic control unit (10) disposed outside the oil pan (16) through circuits. The circuits of the signal receiving module (12) and the second wireless charging transmitting module (13) are connected to the same side of the battery (9) and the electronic control unit (10), and the circuit of the second thermocouple (15) is connected to the other side of the battery (9) and the electronic control unit (10).

[0013] The circuit of the electric pump (17) is connected to one side of the battery (9) and the electronic control unit (10). The pipe on one side of the electric pump (17) is inserted into one vertical side of the oil pan (16), and the pipe on the other side of the electric pump (17) passes through the cooler (11) and is inserted into the other vertical side of the oil pan (16) to form a cooling circuit.

[0014] Optionally, the microprocessor circuit (7) includes a data input interface (71), a processing chip (72), a circuit board (73), a surface mount TF card (74), a power interface (75), and a WIFI module (76).

[0015] After the processing chip (72) processes the temperature signal data collected by the thermocouple (3) and the strain signal data collected by the strain gauge (23), it transmits the signal data and stores it in the patch TF card (74), and transmits it to the electronic control unit (10) through the WIFI module (76).

[0016] The microprocessor circuit (7) is connected to the first thermocouple (3) and strain gauge (23) through the data input interface (71), and the microprocessor circuit (7) is connected to the power interface (75) and the high-temperature battery (22) through the first power line (84).

[0017] Optionally, the first heat-insulating encapsulation box (8) includes: a first outer shell (81), a first sealing cover (82), a first signal line (83), and a first power line (84).

[0018] The microprocessor circuit (7) is placed in the center of the first housing (81). The microprocessor circuit (7) is wrapped with a first two-component epoxy potting compound layer (231). The space between the first two-component epoxy potting compound layer (231) and the first housing (81) is filled with nano-silica aerogel (24).

[0019] A second two-component epoxy potting compound layer (232) is filled between the contact side of the nano silica aerogel (24) and the first sealing cap (82).

[0020] The first signal line (83) consists of multiple wires, and the first signal line (83) and the first power line (84) pass through the first sealing cover (82) and are connected to the outside.

[0021] Optionally, the second heat-insulating encapsulation box (21) is adhesively connected to the bottom of the piston (2). The second heat-insulating encapsulation box (21) includes a second outer shell (211), a second sealing cap (212), a second power cord (213), and a first power cord (84).

[0022] The high-temperature resistant battery (22) is placed in the center of the second shell (211). The high-temperature resistant battery (22) is wrapped with a third two-component epoxy potting compound layer (251). The third two-component epoxy potting compound layer (251) and the second shell (211) are then filled with a second nano-silica aerogel (26).

[0023] The second nano-silica aerogel (26) and the second sealing cap (212) are filled with a fourth two-component epoxy potting compound layer (252).

[0024] The second power line (213) and the first power line (84) pass through the second sealing cover (212) and are connected to the outside.

[0025] Optionally, the cooler (11) includes a heat dissipation copper pipe (111) and a housing (112); the heat dissipation copper pipe (111) includes an air inlet (28) and an air outlet (30); the housing (112) has a water inlet (27) and a water outlet (29) on both sides.

[0026] The heat dissipation copper pipe (111) is used to transfer the heat of the high-temperature oil vapor and / or air mixture to the water in the cooler (11) to cool the high-temperature oil vapor and / or the air mixture.

[0027] Furthermore, to achieve the above objectives, the present invention also provides a control method for an integrated data acquisition compression ignition aero-engine, applied to the integrated data acquisition compression ignition aero-engine described above, the method comprising:

[0028] The monitoring patch temperature control switch monitors the first temperature value, the second temperature value of the second thermocouple, and the engine running time;

[0029] When the first temperature value is greater than or equal to a preset first temperature threshold, the first strategy is executed;

[0030] When the second temperature value is greater than or equal to the preset second temperature threshold, the second strategy is executed;

[0031] When the engine running time exceeds a preset running time threshold, the third strategy is executed.

[0032] Optionally, when the first temperature value is greater than or equal to the preset first temperature threshold, the patch temperature control switch contacts close, so that the microprocessor circuit is connected to and powered on by the high-temperature resistant battery. After being powered on, the microprocessor circuit begins to collect data from the first thermocouple and strain gauge, and transmits and stores the collected data to the patch TF card. The steps of executing the first strategy specifically include:

[0033] Set the engine to idle to trigger the data acquisition device.

[0034] Optionally, the step of executing the second strategy specifically includes:

[0035] The electric pump is controlled to run at a preset speed to draw the high-temperature oil vapor and / or air mixture from the upper part of the oil pan to the cooler for cooling and then return to the upper part of the oil pan;

[0036] When the second temperature value is detected to be less than or equal to the preset second temperature threshold, the electric pump is controlled to shut down.

[0037] Optionally, the step of executing the third strategy specifically includes:

[0038] The wireless charging module is turned on so that it charges the high-temperature resistant battery.

[0039] Get charging time;

[0040] When the charging time is greater than or equal to the preset charging time, the wireless charging module is controlled to turn off.

[0041] Furthermore, to achieve the above objectives, the present invention also provides a computer-readable storage medium storing a control program for an integrated data acquisition compression ignition (ICCI) aero-engine, wherein when the ICCI control program is executed by a processor, it implements the steps of the control method for the ICCI aero-engine as described above.

[0042] This invention provides an integrated data acquisition compression-ignition aero-engine, a control method, and a storage medium. The integrated data acquisition compression-ignition aero-engine incorporates a microprocessor circuit integrating storage and wireless data transmission technology. This microprocessor circuit processes and transmits data acquired by a first thermocouple and strain gauge. Since no leads are required, the problem of lead breakage that can occur with traditional lead-wire methods is eliminated. Furthermore, the small size of the microprocessor circuit results in a small overall data acquisition device, making it suitable for the relatively small and compact structure of compression-ignition aero-engines, thus achieving the goal of integrated acquisition of piston temperature and strain data from compression-ignition aero-engines. Attached Figure Description

[0043] Figure 1 This is a schematic diagram of the integrated data acquisition compression ignition aero-engine structure according to an embodiment of the present invention;

[0044] Figure 2 This is a schematic diagram of the microprocessor circuit involved in an embodiment of the present invention;

[0045] Figure 3 This is a schematic diagram of the structure of the first heat-insulating packaging box according to an embodiment of the present invention;

[0046] Figure 4 This is a schematic diagram of the structure of the second heat-insulating packaging box according to an embodiment of the present invention;

[0047] Figure 5 This is a schematic diagram of the structure of the cooler according to an embodiment of the present invention;

[0048] Figure 6 This is a schematic diagram of the hardware operating environment of the integrated data acquisition compression ignition aero-engine involved in the embodiments of the present invention;

[0049] Figure 7This is a schematic flowchart illustrating an embodiment of the control method for an integrated data acquisition compression ignition aero-engine of the present invention.

[0050] In the diagram, 1. Engine housing; 2. Piston; 3. First thermocouple; 4. Cylinder wall; 5. First wireless charging receiver module; 6. First wireless charging transmitter module; 7. Microprocessor circuit; 8. First thermal insulation enclosure; 9. Battery; 10. Electronic control unit; 11. Cooler; 12. Signal receiving module; 13. Second wireless charging transmitter module; 14. Second radio receiver module; 15. Second thermocouple; 16. Oil pan; 17. Electric pump; 18. Crankshaft; 19. Connecting rod; 20. Patch thermostat switch; 21. Second thermal insulation enclosure; 22. High-temperature resistant battery; 23. Strain gauge.

[0051] 71. Data input interface; 72. Processing chip; 73. Circuit board; 74. Surface mount TF card; 75. Power interface; 76. WIFI module;

[0052] 81. First outer casing; 82. First sealing cover; 83. First signal line; 84. First power line;

[0053] 211. Second outer shell; 212. Second sealing cap; 213. Second power cord; 231. First two-component epoxy potting compound layer; 232. Second two-component epoxy potting compound layer; 24. Nano-silica aerogel; 26. Second nano-silica aerogel; 251. Third two-component epoxy potting compound layer; 252. Fourth two-component epoxy potting compound layer;

[0054] 111. Copper heat dissipation pipe; 112. Outer casing; 28. Air inlet; 30. Air outlet; 27. Water inlet; 29. ​​Water outlet.

[0055] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0056] This application designs an integrated data acquisition compression-ignition aero-engine. The integrated data acquisition compression-ignition aero-engine incorporates a microprocessor circuit integrating storage and wireless data transmission technologies. This microprocessor circuit processes and transmits data acquired by a first thermocouple and strain gauge. Since no leads are required, the problem of lead breakage that can occur with traditional lead-wire methods is eliminated. Furthermore, the small size of the microprocessor circuit results in a small overall data acquisition device, making it suitable for the relatively small and compact structure of compression-ignition aero-engines, thus achieving the goal of integrated acquisition of piston temperature and strain data for compression-ignition aero-engines.

[0057] In addition, the integrated data acquisition compression ignition aero-engine is also designed with a patch temperature control switch, which controls the on / off state of the microprocessor circuit. The microprocessor circuit is only turned on when certain conditions are met, which effectively extends the service life of the microprocessor circuit.

[0058] In addition, the integrated data acquisition compression ignition aero engine is also designed with a heat-insulating enclosure. The heat-insulating enclosure is made of a material with good heat insulation performance to isolate the internal components from the harsh environment formed by external engine oil and high-temperature engine oil vapor.

[0059] In addition, the integrated data acquisition compression ignition aero-engine is also designed with a wireless charging transceiver module, which is used to charge the high-temperature resistant battery, which in turn powers the microprocessor circuit, enabling the microprocessor circuit to operate for extended periods.

[0060] To better understand the above technical solutions, exemplary embodiments of this disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of this disclosure are shown in the drawings, it should be understood that this disclosure can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of this disclosure to those skilled in the art.

[0061] First Embodiment

[0062] Reference Figure 1 The integrated compression ignition aero-engine includes an engine casing 1, a piston 2, a first thermocouple 3, a cylinder wall 4, a first wireless charging receiver module 5, a first wireless charging transmitter module 6, a microprocessor circuit 7, a first thermal insulation enclosure 8, a battery 9, an electronic control unit 10, a cooler 11, a signal receiving module 12, a second wireless charging transmitter module 13, a second radio receiver module 14, a second thermocouple 15, an oil pan 16, an electric pump 17, a crankshaft 18, a connecting rod 19, a patch temperature control switch 20, a second thermal insulation enclosure 21, a high-temperature resistant battery 22, and a strain gauge 23.

[0063] The cylinder wall 4 is located inside the engine housing 1. The piston 2 and the first thermocouple 3 are located inside the cylinder wall 4, with the first thermocouple 3 positioned on the surface of the piston 2 and connected to the microprocessor circuit 7 via a circuit. In this embodiment, the connection can optionally be continuous; the first thermocouple 3 is used to collect the temperature of the piston 2 surface.

[0064] The strain gauge 23 is symmetrically arranged with the first thermocouple 3 and is connected to the microprocessor circuit 7 through a circuit to measure the strain of the piston;

[0065] Optionally, the thermocouple can be a TT-K-30 model thermocouple with a temperature measurement range of -20 to 800℃.

[0066] The microprocessor circuit 7 is housed within the first thermally insulated enclosure 8 to isolate it from the external environment. The microprocessor circuit 7 is also connected to a surface-mount temperature control switch 20 via another circuit. The surface-mount temperature control switch 20 is attached to the bottom of the second thermally insulated enclosure 21, which contains a high-temperature resistant battery 22. The circuit of the high-temperature resistant battery 22 passes through a connecting rod 19 and is connected to a second radio receiving module 14 located at the bottom of the connecting rod 19. In this embodiment, when the ambient temperature around the surface-mount temperature control switch 20 reaches a preset temperature threshold, the contacts of the surface-mount temperature control switch 20 close, connecting the first power line 84 from the high-temperature resistant battery 22 to the microprocessor circuit 7. This connects the microprocessor circuit 7 to the high-temperature resistant battery 22, which then supplies power to the microprocessor circuit 7, triggering it to begin operation.

[0067] Optionally, in this embodiment, the high-temperature resistant battery 22 can be made of a high-temperature resistant ternary lithium-ion battery.

[0068] In this embodiment, when the microprocessor circuit 7 starts working, it first adjusts the engine to idle speed so that the engine runs at a lower power to avoid interference with data transmission when the engine is running at high power. Then, the relevant components in the microprocessor circuit 7 start to collect data.

[0069] Alternatively, as an alternative implementation, the engine may be shut off immediately after data acquisition is completed.

[0070] The crankshaft 18 is mounted on the lower outer side of the connecting rod 19 via a mounting base. It is used to bear the force transmitted from the connecting rod 19 and convert the force into torque output to drive other accessories on the engine.

[0071] The first wireless charging receiver module 5 and the first wireless charging transmitter module 6 are installed at intervals on the outer side of the connecting rod 19. In this embodiment, the first wireless charging receiver module 5 is used to receive electrical energy transmitted from the second wireless charging transmitter module 13, and the first wireless charging transmitter module 6 is used to transmit electrical energy to the high-temperature resistant battery 22 to charge the high-temperature resistant battery 22.

[0072] The signal receiving module 12, the second wireless charging transmitting module 13, and the second thermocouple 15 are disposed inside the oil pan 16. The second wireless charging transmitting module 13 and the second radio receiving module 14 are spaced apart. The signal receiving module 12, the second wireless charging transmitting module 13, and the second thermocouple 15 are all connected to the battery 9 and the electronic control unit 10 disposed outside the oil pan 16 via circuits. The circuits of the signal receiving module 12 and the second wireless charging transmitting module 13 are connected to the same side of the battery 9 and the electronic control unit 10, and the circuit of the second thermocouple 15 is connected to the other side of the battery 9 and the electronic control unit 10. In this embodiment, the second radio receiving module 14 receives electrical energy from the battery 9, and the second wireless charging transmitting module 13 transmits electrical energy to the first wireless charging receiving module 5 to transfer the electrical energy of the battery 9 to the high-temperature resistant battery 22, thereby charging the high-temperature resistant battery 22.

[0073] Alternatively, the battery 9 can be made of lithium iron phosphate.

[0074] The circuit of the electric pump 17 is connected to one side of the battery 9 and the electronic control unit 10. A pipe on one side of the electric pump 17 is inserted into one vertical side of the oil pan 16, and a pipe on the other side of the electric pump 17 passes through the cooler 11 and is inserted into the other vertical side of the oil pan 16 to form a cooling circuit. In this embodiment, the second thermocouple 15 is used to measure the temperature of the upper part of the oil pan 16. Optionally, the second thermocouple 15 can be installed on the upper part of the oil level of the oil pan 16. Optionally, the electric pump 17 can be installed on the pipeline between the oil pan 16 and the cooler 11 to pump out the high-temperature oil vapor and / or air mixture above the oil pan 16. The high-temperature oil vapor and / or air mixture is transported to the cooler 11 through the pipeline. After being cooled by the cooler 11, the high-temperature oil vapor and / or air mixture is transported back to the engine oil pan 16.

[0075] Furthermore, refer to Figure 2 In this embodiment, the microprocessor circuit 7 also includes a data input interface 71, a processing chip 72, a circuit board 73, a surface-mount TF card 74, a power interface 75, and a WIFI module 76.

[0076] After processing the temperature signal data collected by the first thermocouple 3 and the strain signal data collected by the strain gauge 23, the processing chip 72 transmits the signal data and stores it in the surface-mount TF (Trans Flash) card 74. The surface-mount TF card 74 transmits the signal data to the electronic control unit 10 through the WIFI module 76.

[0077] Furthermore, refer to Figure 5In this embodiment, the cooler 11 includes a heat dissipation copper pipe 111 and a housing 112, wherein the heat dissipation copper pipe 111 includes an air inlet 28 and an air outlet 30; the housing 112 has a water inlet 27 and a water outlet 29 on both sides.

[0078] The heat dissipation copper pipe 111 is used to transfer the heat of high-temperature oil vapor and / or air mixture to the coolant in the cooler 11, so as to cool the high-temperature oil vapor and / or air mixture.

[0079] In this embodiment, when the electric pump 17 starts to draw high-temperature oil vapor and / or the air mixture from the upper part of the oil pan 16, the high-temperature oil vapor and / or the air mixture enter the heat dissipation copper pipe 111 from the air inlet 28 and then return to the upper part of the oil pan 16 from the air outlet 30; the coolant in the cooler 11 enters the internal space of the cooler 11 through the water inlet 27, and after reducing the temperature of the gas in the heat dissipation copper pipe 111 by heat transfer, it flows out from the water outlet 29.

[0080] Optionally, the cooler 11 may also be equipped with a cooling source. After the coolant flows out of the outlet 29 and returns to the cooling source, the cooling source cools the coolant to the target temperature.

[0081] In the technical solution provided in this embodiment, the temperature at the surface of the piston 2 is measured by the first thermocouple 3, and the surface temperature of the oil pan 16 is measured by the second thermocouple 15. When the surface temperature of the oil pan 16 is detected to be high, the high-temperature oil vapor and / or air mixture above the oil pan 16 is transported to the cooler 11 by the electric pump 17 for cooling and then returned to the surface of the oil pan 16. This accurately monitors the temperature of the oil pan 16 while avoiding excessively high temperatures around the piston skirt that could damage the engine's built-in data acquisition device.

[0082] Second Embodiment

[0083] Reference Figure 3 Based on the first embodiment, in this embodiment, the first heat-insulating encapsulation box 8 includes: a first outer shell 81, a first sealing cover 82, a first signal line 83, and a first power line 84;

[0084] The microprocessor circuit 7 is placed in the center of the first housing 81, and a two-component epoxy potting compound layer is wrapped around the outside of the microprocessor circuit 7, serving as the first two-component epoxy potting compound layer 231. In this embodiment, the two-component epoxy potting compound layer has good waterproof, oil-proof, insulating, corrosion-resistant, and vibration-resistant properties, and can effectively isolate engine oil and oil vapor and prevent short circuits in the circuit.

[0085] A layer of nano-silica aerogel 24 is then filled between the first two-component epoxy potting compound layer 231 and the first outer shell 81. The nano-silica aerogel 24 has good thermal insulation properties and can effectively isolate the microprocessor circuit 7 from the external high-temperature environment.

[0086] A second two-component epoxy potting compound layer 232 is filled between the nano-silica aerogel 24 and the first sealing cap 82 so that the nano-silica aerogel 24 is encapsulated in the nano-silica aerogel 24, further improving the protection effect of the microprocessor circuit 7.

[0087] The first signal line 83 and the first power line 84 pass through the first sealing cover 82 and are connected to the outside. In this embodiment, one end of the first signal line 83 and the first power line 84 are connected to the microprocessor circuit 7, and the other end passes through the first sealing cover 82 and is connected to the outside, so that the microprocessor circuit 7 is connected to the outside.

[0088] Furthermore, refer to Figure 4 and Figure 1 In this embodiment, the second heat-insulating encapsulation box 21 is adhesively connected to the bottom of the piston 2. The second heat-insulating encapsulation box 21 includes a second outer shell 211, a second sealing cover 212, a second power line 213, and a first power line 84.

[0089] The high-temperature resistant battery 22 is placed in the center of the second shell 211. The high-temperature resistant battery 22 is wrapped with a third two-component epoxy potting compound layer 251. The third two-component epoxy potting compound layer 251 and the second shell 211 are then filled with a second nano-silica aerogel 26.

[0090] A second layer of nano-silica aerogel 26 is filled between the third two-component epoxy potting compound layer 251 and the second outer shell 211. As the second nano-silica aerogel 26, it can effectively isolate the high-temperature resistant battery 22 from the external high-temperature environment.

[0091] The second nano-silica aerogel 26 is filled with a fourth two-component epoxy potting compound layer 252 between the contact side of the second sealing cap 212, so that the nano-silica aerogel 24 is encapsulated in the second nano-silica aerogel 26, further improving the protection effect of the high-temperature resistant battery 22.

[0092] The second power line 213 and the first power line 84 pass through the second sealing cover 212 and are connected to the outside. In this embodiment, one end of the second power line 213 and the first power line 84 are connected to the high-temperature resistant battery 22, and the other end passes through the second sealing cover 212 and is connected to the outside, so that the high-temperature resistant battery 22 is connected to the outside.

[0093] In the technical solution provided in this embodiment, the heat insulation materials of the first heat insulation encapsulation box 8 and the second heat insulation encapsulation box 21 are a two-component epoxy potting compound and nano-silica aerogel 24, which avoids damage to the high-temperature resistant battery 22 and microprocessor circuit 7 placed in the heat insulation encapsulation box during engine operation, thereby improving the protection effect on the high-temperature resistant battery 22 and microprocessor circuit 7.

[0094] As one implementation scheme, Figure 6 This is a schematic diagram of the hardware operating environment of the integrated data acquisition compression ignition aero-engine involved in the embodiments of the present invention.

[0095] like Figure 6 As shown, the integrated data acquisition compression-ignition aero-engine may include: a processor 1001, such as a CPU; a memory 1005; a user interface 1003; a network interface 1004; and a communication bus 1002. The communication bus 1002 is used to enable communication between these components. The user interface 1003 may include a display screen or an input unit such as a keyboard; optionally, the user interface 1003 may also include a standard wired interface or a wireless interface. The network interface 1004 may optionally include a standard wired interface or a wireless interface (such as a Wi-Fi interface). The memory 1005 may be a high-speed RAM or a stable, non-volatile memory, such as a disk drive. Optionally, the memory 1005 may also be a storage device independent of the aforementioned processor 1001.

[0096] Those skilled in the art will understand that Figure 6 The integrated data acquisition compression ignition aero-engine architecture shown does not constitute a limitation on the integrated data acquisition compression ignition aero-engine, and may include more or fewer components than shown, or combine certain components, or have different component arrangements.

[0097] like Figure 6 As shown, the storage device 1005, which serves as a storage medium, may include an operating system, a network communication module, a user interface module, and a control program for an integrated data acquisition compression ignition (CICI) aero-engine. The operating system is a program that manages and controls the hardware and software resources of the integrated data acquisition CICI aero-engine, the control program for the integrated data acquisition CICI aero-engine, and the operation of other software or programs.

[0098] exist Figure 6In the integrated data acquisition compression ignition aero-engine shown, the user interface 1003 is mainly used to connect to the terminal and communicate with the terminal; the network interface 1004 is mainly used to communicate with the back-end server; and the processor 1001 can be used to call the control program of the integrated data acquisition compression ignition aero-engine stored in the memory 1005.

[0099] In this embodiment, the integrated data acquisition compression ignition aero-engine includes: a storage device 1005, a processor 1001, and a control program for the integrated data acquisition compression ignition aero-engine stored in the storage device and executable on the processor, wherein:

[0100] When processor 1001 calls the control program for the integrated data acquisition compression ignition aircraft engine stored in memory 1005, it performs the following operations:

[0101] Acquire the first temperature value monitored by the built-in sensor of the patch temperature control switch, the second temperature value at the second thermocouple, and the engine running time;

[0102] When the first temperature value is greater than or equal to a preset first temperature threshold, the first strategy is executed;

[0103] When the second temperature value is greater than or equal to the preset second temperature threshold, the second strategy is executed;

[0104] When the engine running time exceeds a preset running time threshold, the third strategy is executed.

[0105] When processor 1001 calls the control program for the integrated data acquisition compression ignition aircraft engine stored in memory 1005, it performs the following operations:

[0106] Set the engine to idle to trigger the data acquisition device.

[0107] When processor 1001 calls the control program for the integrated data acquisition compression ignition aircraft engine stored in memory 1005, it performs the following operations:

[0108] The electric pump is controlled to run at a preset speed to draw the high-temperature oil vapor and / or air mixture from the upper part of the oil pan to the cooler for cooling and then return to the upper part of the oil pan;

[0109] When the second temperature value is detected to be less than or equal to the preset second temperature threshold, the electric pump is controlled to shut down.

[0110] When processor 1001 calls the control program for the integrated data acquisition compression ignition aircraft engine stored in memory 1005, it performs the following operations:

[0111] The wireless charging module is turned on so that it charges the high-temperature resistant battery.

[0112] Get charging time;

[0113] When the charging time is greater than or equal to the preset charging time, the wireless charging module is controlled to turn off.

[0114] Based on the hardware architecture of the integrated data acquisition compression ignition aero-engine based on the above engine technology, an embodiment of the control method for the integrated data acquisition compression ignition aero-engine of the present invention is proposed.

[0115] Reference Figure 7 In the third embodiment, the control method for the integrated data acquisition compression ignition aero-engine is applied to the integrated data acquisition compression ignition aero-engine described in any embodiment, and the method includes the following steps:

[0116] Step S10: Obtain the first temperature value monitored by the built-in sensor of the patch temperature control switch, the second temperature value at the second thermocouple, and the engine running time;

[0117] Step S20: When the first temperature value is greater than or equal to a preset first temperature threshold, execute the first strategy;

[0118] Step S30: When the second temperature value is greater than or equal to a preset second temperature threshold, execute the second strategy;

[0119] Step S40: When the engine running time exceeds a preset running time threshold, the third strategy is executed.

[0120] In this embodiment, the data processing module of the integrated data acquisition compression-ignition aero-engine (hereinafter referred to as the engine) acquires a first temperature value monitored by the built-in sensor of the patch temperature control switch, a second temperature value at the second thermocouple, and the engine running time at preset time intervals. The patch temperature control switch is located at the bottom of the second heat-insulating enclosure to monitor the temperature at the bottom of the enclosure, and the second thermocouple is located outside the engine's oil pan to monitor the temperature outside the oil pan. The engine running time can be recorded by setting a timer and transmitted to the engine's data processing module.

[0121] In this embodiment, when the first temperature value is greater than or equal to a preset first temperature threshold, a first strategy is executed to trigger the data acquisition device; when the second temperature value is greater than or equal to a preset second temperature threshold, a second strategy is executed to reduce the temperature at the oil pan; when the engine running time is greater than a preset running time threshold, it is determined that the remaining charge of the high-temperature resistant battery is low, and a third strategy is executed to charge the high-temperature resistant battery.

[0122] Optionally, the preset first temperature threshold can be 50℃, the preset second temperature threshold can be 75℃, and the preset running time threshold can be 20 hours.

[0123] Furthermore, in this embodiment, step S20 includes:

[0124] Step S21: Set the engine to idle speed and trigger the data acquisition device.

[0125] Optionally, in this embodiment, the first strategy includes: after the engine starts, the temperature of the engine piston skirt rises after the engine warms up. When the temperature of the engine piston skirt reaches a preset temperature value, the electronic control unit sets the engine to idle speed, the contact of the patch temperature control switch closes automatically, and the power line is connected. At this time, the microprocessor circuit is connected to the high-temperature resistant battery, the microprocessor circuit is triggered to start working, the microprocessor circuit begins to collect data from the first thermocouple and strain gauge, and stores the data in the built-in patch TF card. The electronic control unit and the microprocessor circuit are connected and transmit data through a WIFI module.

[0126] It should be noted that setting the engine to idle and storing the data in the built-in patch TF card can effectively avoid problems such as unstable signal transmission and transmission interruption caused by the engine at high speeds. At the same time, it solves the problem of high power consumption of the data acquisition device in the mode of acquiring and transmitting data simultaneously.

[0127] Further and optionally, after the data transmission is completed, the engine is turned off, allowing the overall temperature of the engine to begin to drop, meaning the temperature of the piston skirt will also drop over time. When the temperature of the piston skirt is lower than a preset first temperature threshold, the surface-mount temperature control switch contacts automatically disconnect, thereby disconnecting the microprocessor circuit from the high-temperature resistant battery and causing the microprocessor circuit to stop working.

[0128] Furthermore, in this embodiment, step S30 includes:

[0129] Step S31: Control the electric pump to run at a preset speed to draw the high-temperature oil vapor and / or air mixture from the upper part of the oil pan to the cooler for cooling.

[0130] Step S32: When the second temperature value is detected to be less than or equal to the preset second temperature threshold, the electric pump is controlled to shut down, stopping the extraction of high-temperature oil vapor and / or air mixture from the upper part of the oil pan to the cooler for cooling.

[0131] Optionally, in this embodiment, the second strategy includes: when the oil pan temperature reaches a preset second temperature threshold, the electronic control unit controls the electric pump to turn on and adjust it to a preset speed. At this time, the high-temperature oil vapor / air mixture in the upper part of the oil pan is extracted, cooled by the cooler, and then returned to the oil pan, thereby reducing the ambient temperature near the microprocessor circuit and preventing the microprocessor circuit from being damaged due to overheating at high ambient temperatures. When the oil pan temperature is less than or equal to the preset second temperature threshold, the electronic control unit controls the electric pump to turn off, stopping the cooling of the high-temperature oil vapor / air mixture in the engine oil pan.

[0132] Furthermore, in this embodiment, step S40 includes:

[0133] Step S41: Control the wireless charging module to turn on so that the wireless charging module can charge the high-temperature resistant battery.

[0134] Step S42, obtain the charging time;

[0135] Step S43: When the charging time is greater than or equal to the preset charging time, control the wireless charging module to turn off.

[0136] Optionally, in this embodiment, the third strategy includes: after the engine has run for a preset time threshold, the remaining power of the high-temperature resistant battery is low. At this time, the wireless charging device is turned on to charge the high-temperature resistant battery and the charging time is obtained. When the charging time is greater than or equal to the preset charging time, the wireless charging module is controlled to turn off.

[0137] Optionally, the preset charging time can be 5 hours.

[0138] In the technical solution provided in this embodiment, three different control methods are used to control the integrated data acquisition compression ignition aero-engine, thereby achieving over-temperature control of the data acquisition device in the integrated data acquisition compression ignition aero-engine, avoiding damage to the data acquisition device inside the engine due to high temperature, and controlling the charging of the high-temperature resistant battery to improve the working endurance of the microprocessor circuit.

[0139] Furthermore, those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The computer program includes program instructions and can be stored in a storage medium, which is a computer-readable storage medium. The program instructions are executed by at least one processor in an integrated data acquisition compression ignition aero-engine to implement the process steps of the embodiments of the above methods.

[0140] Therefore, the present invention also provides a computer-readable storage medium storing a control program for an integrated data acquisition compression ignition aero-engine, wherein the control program for the integrated data acquisition compression ignition aero-engine, when executed by a processor, implements the various steps of the control method for the integrated data acquisition compression ignition aero-engine as described in the above embodiments.

[0141] The computer-readable storage medium can be any computer-readable storage medium capable of storing program code, such as a USB flash drive, portable hard drive, read-only memory (ROM), magnetic disk, or optical disk.

[0142] It should be noted that, since the storage medium provided in the embodiments of this application is the storage medium used to implement the methods of the embodiments of this application, those skilled in the art can understand the specific structure and variations of the storage medium based on the methods described in the embodiments of this application, and therefore will not be repeated here. All storage media used in the methods of the embodiments of this application fall within the scope of protection of this application.

[0143] Those skilled in the art will understand that embodiments of the present invention can be provided as methods, systems, or computer program products. Therefore, the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention can take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0144] This invention is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart illustrations and / or block diagrams. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0145] These computer program instructions may also be stored in a computer-readable storage device that can direct a computer or other programmable data processing device to operate in a particular manner, such that the instructions stored in the computer-readable storage device produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0146] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0147] It should be noted that any reference signs placed between parentheses in the claims should not be construed as limiting the claims. The word "comprising" does not exclude the presence of components or steps not listed in the claims. The word "a" or "an" preceding a component does not exclude the presence of a plurality of such components. The invention can be implemented by means of hardware comprising several different components and by means of a suitably programmed computer. In a unit claim enumerating several means, several of these means may be embodied by the same item of hardware. The use of the words first, second, and third, etc., does not indicate any order. These words can be interpreted as names.

[0148] Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the invention.

[0149] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. An integrated data acquisition compression ignition aero-engine, characterized in that, The integrated data acquisition compression ignition aero-engine includes an engine casing (1), piston (2), first thermocouple (3), cylinder wall (4), first wireless charging receiver module (5), first wireless charging transmitter module (6), microprocessor circuit (7), first heat insulation enclosure (8), battery (9), electronic control unit (10), cooler (11), signal receiving module (12), second wireless charging transmitter module (13), second radio receiver module (14), second thermocouple (15), oil pan (16), electric pump (17), crankshaft (18), connecting rod (19), patch temperature control switch (20), second heat insulation enclosure (21), high temperature resistant battery (22), and strain gauge (23). The cylinder wall (4) is located inside the engine housing (1), the piston (2) and the first thermocouple (3) are located inside the cylinder wall (4), and the first thermocouple (3) is located on the surface of the piston (2) and connected to the microprocessor circuit (7) through a circuit. The microprocessor circuit (7) is located inside the first heat insulation encapsulation box (8), and the microprocessor circuit (7) is also connected to the patch temperature control switch (20) through another circuit. The patch temperature control switch (20) is close to the bottom of the second heat insulation encapsulation box (21). The second heat insulation encapsulation box (21) is equipped with a high-temperature resistant battery (22). The circuit of the high-temperature resistant battery (22) passes through the connecting rod (19) and is connected to the second radio receiver module (14) located at the bottom of the connecting rod (19) inside the connecting rod (19). The strain gauge (23) is symmetrically arranged with the first thermocouple (3) and connected to the microprocessor circuit (7) through the circuit; The crankshaft (18) is mounted on the lower outer side of the connecting rod (19) via a mounting base; The first wireless charging receiver module (5) and the first wireless charging transmitter module (6) are installed at intervals on the outer side of the connecting rod (19); The signal receiving module (12), the second wireless charging transmitting module (13), and the second thermocouple (15) are disposed inside the oil pan (16). The second wireless charging transmitting module (13) and the second radio receiving module (14) are disposed at intervals. The signal receiving module (12), the second wireless charging transmitting module (13), and the second thermocouple (15) are all connected to the battery (9) and the electronic control unit (10) disposed outside the oil pan (16) through circuits. The circuits of the signal receiving module (12) and the second wireless charging transmitting module (13) are connected to the same side of the battery (9) and the electronic control unit (10), and the circuit of the second thermocouple (15) is connected to the other side of the battery (9) and the electronic control unit (10). The circuit of the electric pump (17) is connected to one side of the battery (9) and the electronic control unit (10). The pipe on one side of the electric pump (17) is inserted into one vertical side of the oil pan (16), and the pipe on the other side of the electric pump (17) passes through the cooler (11) and is inserted into the other vertical side of the oil pan (16) to form a cooling circuit.

2. The integrated data acquisition compression ignition aero-engine as described in claim 1, characterized in that, The microprocessor circuit (7) includes a data input interface (71), a processing chip (72), a circuit board (73), a surface-mount TF card (74), a power interface (75), and a WIFI module (76). After the processing chip (72) processes the temperature signal data collected by the first thermocouple (3) and the strain signal data collected by the strain gauge (23), it transmits the signal data and stores it in the patch TF card (74). The patch TF card (74) transmits the signal data to the electronic control unit (10) through the WIFI module (76). The microprocessor circuit (7) is connected to the first thermocouple (3) and strain gauge (23) through the data input interface (71), and the microprocessor circuit (7) is connected to the power interface (75) and the high-temperature battery (22) through the first power line (84).

3. The integrated data acquisition compression ignition aero-engine as described in claim 1, characterized in that, The first heat-insulating encapsulation box (8) includes: a first outer shell (81), a first sealing cover (82), a first signal line (83), and a first power line (84); The microprocessor circuit (7) is placed in the center of the first housing (81). The microprocessor circuit (7) is wrapped with a first two-component epoxy potting compound layer (231). The space between the first two-component epoxy potting compound layer (231) and the first housing (81) is filled with nano-silica aerogel (24). A second two-component epoxy potting compound layer (232) is filled between the contact side of the nano silica aerogel (24) and the first sealing cap (82). The first signal line (83) consists of multiple lines, and the first signal line (83) and the first power line (84) pass through the first sealing cover (82) and are connected to the outside.

4. The integrated data acquisition compression ignition aero-engine as described in claim 1, characterized in that, The second heat-insulating encapsulation box (21) is adhesively connected to the bottom of the piston (2). The second heat-insulating encapsulation box (21) includes a second outer shell (211), a second sealing cap (212), a second power line (213), and a first power line (84). The high-temperature resistant battery (22) is placed in the center of the second shell (211). The high-temperature resistant battery (22) is wrapped with a third two-component epoxy potting compound layer (251). The third two-component epoxy potting compound layer (251) and the second shell (211) are then filled with a second nano-silica aerogel (26). The second nano-silica aerogel (26) and the second sealing cap (212) are filled with a fourth two-component epoxy potting compound layer (252). The second power line (213) and the first power line (84) pass through the second sealing cover (212) and are connected to the outside.

5. The integrated data acquisition compression ignition aero-engine as described in claim 1, characterized in that, The cooler (11) includes a heat dissipation copper pipe (111) and a shell (112); the heat dissipation copper pipe (111) includes an air inlet (28) and an air outlet (30); the shell (112) has a water inlet (27) and a water outlet (29) on both sides. The heat dissipation copper pipe (111) is used to transfer the heat of the high-temperature oil vapor and / or air mixture to the water in the cooler (11) to cool the high-temperature oil vapor and / or the air mixture.

6. A control method for an integrated data acquisition compression ignition aero-engine, characterized in that, The control method for the integrated data acquisition compression ignition aero-engine as described in any one of claims 1 to 5 includes the following steps: Acquire the first temperature value monitored by the built-in sensor of the patch temperature control switch, the second temperature value of the second thermocouple, and the engine running time; When the first temperature value is greater than or equal to a preset first temperature threshold, the first strategy is executed; When the second temperature value is greater than or equal to the preset second temperature threshold, the second strategy is executed; When the engine running time exceeds a preset running time threshold, the third strategy is executed.

7. The method as described in claim 6, characterized in that, When the first temperature value is greater than or equal to the preset first temperature threshold, the patch temperature control switch contacts close, so that the microprocessor circuit is connected to the high-temperature resistant battery and powered on. After being powered on, the microprocessor circuit begins to collect data from the first thermocouple and strain gauge, and transmits and stores the collected data to the patch TF card. The steps of executing the first strategy specifically include: Set the engine to idle to trigger the data acquisition device.

8. The method as described in claim 6, characterized in that, The steps for implementing the second strategy specifically include: The electric pump is controlled to run at a preset speed to draw the high-temperature oil vapor and / or air mixture from the upper part of the oil pan to the cooler for cooling and then return to the upper part of the oil pan; When the second temperature value is detected to be less than or equal to the preset second temperature threshold, the electric pump is controlled to shut down.

9. The method as described in claim 6, characterized in that, The steps for implementing the third strategy specifically include: The wireless charging module is turned on so that it charges the high-temperature resistant battery. Get charging time; When the charging time is greater than or equal to the preset charging time, the wireless charging module is controlled to turn off.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a control program for an integrated data acquisition compression ignition aero-engine, which, when executed by a processor, implements the steps of the control method for an integrated data acquisition compression ignition aero-engine as described in any one of claims 6 to 9.

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