Portable detection device and troubleshooting method for starting failure of an aviation auxiliary power unit

Abstract

The application relates to a portable detection device and a removal method for starting failure of an aviation auxiliary power device. The portable detection device comprises a data acquisition box and a pressure switching box connected with the aviation auxiliary power device respectively, the data acquisition box is connected with the pressure switching box and a mobile terminal respectively, a pressure signal processing module, a rotating speed signal processing module and a temperature signal processing module which are mutually signal-isolated are detachably arranged on the data acquisition box, the three modules are connected with an analog signal processing module, a CPU module and a power module respectively. The removal method comprises the following steps: setting multiple standard parameters of the aviation auxiliary power device; and according to the standard parameters, diagnosing and removing different types of starting failure respectively; the application can quickly and conveniently detect and remove the starting failure of the aviation auxiliary power device, meanwhile, multiple signal parameters can be referred to, and self-diagnosis of the failure is realized.

Description

Technical Field

[0001] This application relates to the field of aero-engine measurement and control technology, and in particular to a portable detection device and troubleshooting method for starting faults in aero-auxiliary power units. Background Technology

[0002] The auxiliary power unit (APU) is primarily used for ground starting of aircraft engines and for supplying power to the aircraft. During the start-up process, the APU often experiences surge and overheating faults, which can ground the entire aircraft. Due to the limited monitoring parameters on the aircraft, when surge or overheating faults occur, the limited field maintenance conditions often necessitate returning the entire aircraft to the factory for repairs. This significantly increases the fault diagnosis and troubleshooting time, severely impacting the aircraft's operational efficiency.

[0003] Currently, there is no equipment or method that can accurately and quickly diagnose starting faults in auxiliary power units, nor can it simultaneously measure multiple signal parameters.

[0004] Therefore, it is necessary to propose a solution to improve one or more problems existing in the above-mentioned related technical solutions.

[0005] It should be noted that the information disclosed in the background section above is only used to enhance the understanding of the background of this application, and therefore may include information that does not constitute prior art known to those skilled in the art. Summary of the Invention

[0006] A first aspect of this application provides a portable detection device for starting failure of an aircraft auxiliary power unit, the portable detection device comprising:

[0007] The data acquisition box has a detachable pressure signal processing module, a speed signal processing module, and a temperature signal processing module that are mutually isolated on its inner bottom plate; the pressure signal processing module, the speed signal processing module, and the temperature signal processing module are respectively connected to an analog signal processing module, a CPU module, and a power supply module;

[0008] The speed signal processing module is connected to the aircraft auxiliary power unit via a speed test cable, and the temperature signal processing module is connected to the aircraft auxiliary power unit via a temperature test cable.

[0009] A pressure adapter box, one end of which is connected to the aircraft auxiliary power unit via a pressure testing hose, and the other end of which is connected to the pressure signal processing module via a pressure testing cable;

[0010] Mobile terminal: The CPU module is communicatively connected to the mobile terminal;

[0011] The power supply module is connected to both the CPU module and the analog signal processing module, and the analog signal processing module is connected to the CPU module. The mobile terminal is used to display the starting fault of the aviation auxiliary power unit in real time.

[0012] In an exemplary embodiment of this application, a rail is provided on the inner bottom plate of the data acquisition box, and both the rotation speed signal processing module and the temperature signal processing module are disposed on the rail and can slide along the rail.

[0013] The data acquisition box has a guide rail on its inner bottom plate. The power module, the CPU module, the pressure signal processing module and the analog signal processing module can all be detached and mounted on the guide rail, and can all slide along the guide rail.

[0014] The guide rail and the clamping rail are arranged parallel to each other.

[0015] In an exemplary embodiment of this application, the data acquisition box is respectively provided with a speed signal interface, a temperature signal interface, a pressure signal interface and a network signal interface;

[0016] The outer end of the speed signal interface is connected to the speed test cable, and the inner end of the speed signal interface is connected to the speed signal processing module.

[0017] The outer end of the temperature signal interface is connected to the temperature test cable, and the inner end of the temperature signal interface is connected to the temperature signal processing module.

[0018] The outer end of the pressure signal interface is connected to the pressure test cable, and the inner end of the pressure signal interface is connected to the pressure signal processing module.

[0019] The external end of the network signal interface is connected to the mobile terminal via a network cable, and the internal end of the network signal interface is connected to the CPU module.

[0020] In an exemplary embodiment of this application, the power module includes a power module body, a power interface, and a power switch connected to each other in pairs. The power interface and the power switch are both disposed on the data acquisition box. The power module body is disposed on the guide rail. The outer end of the power interface is used to connect to an external power source.

[0021] Signal indicator lights are provided below the speed signal interface, the temperature signal interface, the pressure signal interface, the network signal interface, the power interface, and the power switch, and all of the signal indicator lights are located on the data acquisition box.

[0022] In an exemplary embodiment of this application, the pressure signal interface is provided on one side wall of the pressure adapter box, and a plurality of pressure receiving units are evenly distributed on the opposite side wall of the pressure adapter box.

[0023] Each of the pressure receiving units includes: a pressure adapter and a pressure sensor connected to each other;

[0024] The pressure adapter is disposed on the outer side wall of the pressure adapter box. The receiving end of the pressure adapter is connected to the aircraft auxiliary power unit through the pressure measuring hose, and the transmitting end of the pressure adapter is connected to the pressure sensor.

[0025] The pressure sensor is mounted on the inner wall of the pressure adapter box. The receiving end of the pressure sensor is connected to the pressure adapter, and the transmitting end of the pressure sensor is connected to the pressure signal interface.

[0026] The aircraft auxiliary power unit is equipped with a dedicated adapter pipe, which includes a pressure testing adapter and connecting hoses respectively disposed at both ends of the pressure testing adapter; one end of the pressure testing hose is connected to the pressure testing adapter, and the other end of the pressure testing hose is connected to the pressure adapter.

[0027] In an exemplary embodiment of this application, a first shock absorber is provided at the bottom of the data acquisition box; a second shock absorber is provided on the inner bottom plate of the pressure transfer box.

[0028] A second aspect of this application provides a method for troubleshooting starting faults in aircraft auxiliary power units. This method is used to troubleshoot starting faults detected by the portable testing equipment described above. The troubleshooting method includes the following steps:

[0029] Setting standard parameters for aircraft auxiliary power units;

[0030] Based on the aforementioned standard parameters, different types of starting faults are diagnosed and eliminated respectively;

[0031] The standard parameters include:

[0032] n represents rotational speed, in percentage (%).

[0033] t4 represents the exhaust temperature after the turbocharger, in °C;

[0034] P m This indicates the pressure of the lubricating oil, expressed in MPa.

[0035] t0 represents the ambient temperature, in °C;

[0036] P 起压 This indicates the air pressure after the air pump is started, in MPa.

[0037] P 进 This indicates the pressure of the imported fuel, expressed in MPa.

[0038] P2 represents the pressure after the compressor, in MPa;

[0039] P 21 This indicates the compressor exhaust air pressure measured during the previous start-up process, in MPa.

[0040] P 22 This indicates the current measured air pressure after the compressor during startup, expressed in MPa.

[0041] P I This indicates the fuel pressure in oil circuit I, in MPa.

[0042] P Ⅱ This indicates the fuel pressure in oil circuit II, in MPa.

[0043] P 主 This indicates the main fuel line pressure, in MPa.

[0044] P 上上 This indicates the air pressure in the upper chamber of the piston on the vent valve of the gas collecting chamber, in MPa.

[0045] P 上下 This indicates the air pressure in the lower chamber of the upper piston of the vent valve in the gas collecting chamber, in MPa.

[0046] P 下上 This indicates the air pressure in the upper chamber of the piston below the vent valve in the gas collecting chamber, expressed in MPa.

[0047] P 下下 This indicates the air pressure in the lower chamber of the piston below the vent valve in the gas collecting chamber, expressed in MPa.

[0048] △P 下 This indicates the pressure difference between the upper and lower chambers of the piston under the vent valve in the gas collecting chamber, expressed in MPa.

[0049] △P 上 This indicates the pressure difference between the upper and lower chambers of the piston on the vent valve of the gas collecting chamber, expressed in MPa.

[0050] The types of starting faults include: sham start-up faults, surge faults during starting, and over-temperature faults during starting.

[0051] In an exemplary embodiment of this application, diagnosing and eliminating faults in the sham driving process includes:

[0052] If the first preset time after startup is reached and the result does not meet the requirement of n = 20 ± 2%, then n is diagnosed as unqualified and the process is eliminated.

[0053] If n = 20 ± 2%, and P m If the pressure is <0.05 MPa, the diagnosis is P. m Those that fail to meet the standards will be excluded.

[0054] If n = 20 ± 2%, and P I =(P 进 If the value is +0.04*t0+0.49)±0.02MPa, then the diagnosis is P. I Those that fail to meet the standards will be excluded.

[0055] If n = 20 ± 2%, and P II -(P 进 If the pressure is +0.5) ± 0.2 MPa, then the diagnosis is P. Ⅱ Those that fail to meet the standards will be excluded.

[0056] When the second preset time after startup is reached, if P 起压 If the pressure is less than or equal to 0.02 MPa, the diagnosis is P. 起压 Those that fail to meet the standards will be excluded.

[0057] In this context, * indicates multiplication, and ≮ indicates not less than.

[0058] In an exemplary embodiment of this application, diagnosing and eliminating the surge fault includes:

[0059] When (P) 21 -P 22 ) / P 21 When ×100%≥1%, it is determined that the surge fault occurred at that moment during the startup process;

[0060] The surge fault was diagnosed and eliminated as follows:

[0061] If P 下下 If the pressure is ≥0.019MPa and P2 <0.098MPa, the fault is diagnosed as a shunt valve and should be eliminated.

[0062] If t0≤18℃, and before surge, ΔP 下 =(P 上下 -P 下下 If the pressure is greater than 0.02 MPa, the diagnosis is a faulty opening of the temperature valve, and the problem should be resolved.

[0063] If t0 > 18℃, and n ≤ 30%, and before surge, ΔP 下 =(P 上下 -P 下下If the pressure is greater than 0.02 MPa, the fault is diagnosed as a large opening of the temperature valve, and the problem should be eliminated.

[0064] Before surge, if ΔP 上 =(P 上上 -P 上下 If the pressure is ≥0.014MPa, the diagnosis is an early closing fault of the upper piston, and the problem should be eliminated.

[0065] In an exemplary embodiment of this application, diagnosing and eliminating the over-temperature fault includes:

[0066] If n≤30% and t4≥540℃, then it is judged as a 30% over-temperature fault;

[0067] If n>30% and t4≥0.85*t0+610℃, then it is judged as a starting overheating fault;

[0068] Based on the identified over-temperature fault, the following diagnosis and troubleshooting steps were performed:

[0069] If P is within the third preset time after startup I If the pressure is not within the range of 0.4–0.8 MPa, the diagnosis is P. I Those that fail to meet the standards will be excluded.

[0070] If n is in the range of 35% to 40%, if P Ⅱ If the pressure is not within the range of 0.45–0.55 MPa, the diagnosis is P. Ⅱ Those that fail to meet the standards will be excluded.

[0071] If t4 = 0.85 * t0 + 610℃, the corresponding n is in the range of 30% to 50%, and when t0 > 18℃, if ΔP 下 =(P 上下 -P 下下 If the pressure is less than 0.02 MPa, the fault is diagnosed as a small opening of the temperature valve, and the problem should be eliminated.

[0072] In this context, * indicates multiplication.

[0073] Beneficial effects:

[0074] This application proposes a portable detection device and troubleshooting method for starting faults in aircraft auxiliary power units, which has at least the following beneficial effects:

[0075] (1) By connecting the data acquisition box and the pressure transfer box, and setting up a detachable and mutually isolated pressure signal processing module, speed signal processing module and temperature signal processing module, as well as an analog signal processing module, CPU module and power supply module on the inner bottom plate of the data acquisition box, the problem of the current data acquisition system being too large and unable to quickly and conveniently detect multiple signal parameters is solved.

[0076] (2) By connecting the CPU module inside the data acquisition box to the mobile terminal, real-time acquisition and display of various signal parameters are achieved, enabling the portable testing device to have the effect of fault self-diagnosis. Furthermore, the collected signal parameter data can be stored on the mobile terminal, facilitating the study of relevant signal parameter data, understanding the logical relationships between various signal parameters, and enabling staff to quickly and accurately determine the fault type and location and promptly troubleshoot when dealing with similar problems in the future.

[0077] (3) By setting various signal processing modules in the data acquisition box and the pressure transfer box, and setting the first shock absorber at the bottom of the data acquisition box and the second shock absorber in the pressure transfer box, the detection equipment can be portable, shockproof, compact in structure, and adaptable to complex field environments. Attached Figure Description

[0078] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application. It is obvious that the drawings described below are merely some embodiments of this application, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort.

[0079] Figure 1 A schematic diagram illustrating the principle of a portable detection device for starting failure of an aircraft auxiliary power unit in an exemplary embodiment of this application;

[0080] Figure 2 This illustration shows a perspective view of the data acquisition box in an exemplary embodiment of this application;

[0081] Figure 3 This shows a top view of the data acquisition box in an exemplary embodiment of this application;

[0082] Figure 4 A top view of the pressure transfer box in an exemplary embodiment of this application is shown;

[0083] Figure 5 A perspective view of the pressure transfer box in an exemplary embodiment of this application is shown;

[0084] Figure 6 This diagram illustrates the structure of the pressure measuring hose in an exemplary embodiment of this application.

[0085] Figure 7 This diagram illustrates the steps of a method for troubleshooting a startup failure of an aircraft auxiliary power unit in an exemplary embodiment of this application.

[0086] In the diagram, 100 is the data acquisition box; 110 is the speed signal processing module; 111 is the speed test cable; 112 is the speed signal interface; 120 is the temperature signal processing module; 121 is the temperature test cable; 122 is the temperature signal interface; 130 is the pressure signal processing module; 131 is the pressure testing hose; 132 is the pressure test cable; 133 is the pressure signal interface; 140 is the analog signal processing module; 150 is the CPU module; 160 is the power module body; 161 is the power interface; 162 is the power switch; 170 is the rail; 180 is the guide rail; 190 is the network signal interface; 200 is the pressure adapter box; 210 is the pressure adapter; 220 is the pressure sensor; 300 is the dedicated adapter pipe; 310 is the pressure testing adapter; 320 is the docking hose; 400 is the signal indicator light; 500 is the first shock absorber; 600 is the second shock absorber; and 700 is the mobile terminal. Detailed Implementation

[0087] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the examples set forth herein; rather, they are provided to make this application more comprehensive and complete, and to fully convey the concept of the exemplary embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

[0088] Furthermore, the accompanying drawings are merely illustrative of this application and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and therefore repeated descriptions of them will be omitted. Some block diagrams shown in the drawings are functional entities and do not necessarily correspond to physically or logically independent entities. These functional entities can be implemented in software, in one or more hardware modules or integrated circuits, or in different network and / or processor devices and / or microcontroller devices.

[0089] This example embodiment provides a portable detection device for starting failure of an aircraft auxiliary power unit, such as... Figure 1 As shown, Figure 1 The working principle of the portable testing device proposed in this application is illustrated. Figure 1 As can be seen, the portable testing device includes:

[0090] The data acquisition box 100 has a pressure signal processing module 130, a speed signal processing module 110, and a temperature signal processing module 120 that are mutually isolated on its inner bottom plate; the pressure signal processing module 130, the speed signal processing module 110, and the temperature signal processing module 120 are respectively connected to the analog signal processing module 140, the CPU module 150, and the power supply module body 160.

[0091] Among them, the speed signal processing module 110 is connected to the aircraft auxiliary power unit through the speed test cable 111, and the temperature signal processing module 120 is connected to the aircraft auxiliary power unit through the temperature test cable 121.

[0092] Pressure adapter box 200, one end of which is connected to the aircraft auxiliary power unit via pressure testing hose 131, and the other end of which is connected to the pressure signal processing module 130 via pressure testing cable 132;

[0093] Mobile terminal 700: CPU module 150 is connected to mobile terminal 700 for communication;

[0094] The power module body 160 is connected to the CPU module 150 and the analog signal processing module 140 respectively, and the analog signal processing module 140 is connected to the CPU module 150; the mobile terminal 700 is used to display the starting fault of the aviation auxiliary power unit in real time.

[0095] The first aspect of this application provides a portable detection device for starting failure of an aircraft auxiliary power unit, which has at least the following beneficial effects:

[0096] (1) By connecting the data acquisition box 100 and the pressure transfer box 200, and by setting up a detachable and mutually isolated pressure signal processing module 130, speed signal processing module 110 and temperature signal processing module 120, as well as an analog signal processing module 140, a CPU module 150 and a power supply module body 160 on the inner bottom plate of the data acquisition box 100, the problem of the current data acquisition system being too large and unable to quickly and conveniently detect multiple signal parameters is solved.

[0097] (2) By connecting the CPU module 150 inside the data acquisition box 100 to the mobile terminal 700, real-time acquisition and display of various signal parameters are achieved, enabling the portable detection device to have the effect of fault self-diagnosis. Furthermore, it can store previously collected signal parameter data on the mobile terminal 700, facilitating staff to study the relevant signal parameter data, understand the logical relationships between various signal parameters, and enable staff to quickly and accurately determine the fault type and location and promptly troubleshoot when dealing with similar problems in the future.

[0098] (3) By setting various signal processing modules in the data acquisition box 100 and the pressure transfer box 200, and setting the first shock absorber 500 at the bottom of the data acquisition box 100 and the second shock absorber 600 in the pressure transfer box 200, the detection equipment can be portable, shock-resistant, compact in structure, and adaptable to complex outdoor environments.

[0099] The following will provide a more detailed description of a portable detection device and troubleshooting method for starting faults of aircraft auxiliary power units proposed in this example embodiment.

[0100] The first aspect of this embodiment proposes a portable detection device for starting faults in aircraft auxiliary power units.

[0101] In one embodiment, the structure of the data acquisition box 100 is specifically designed. The data acquisition box 100 is mainly used to complete the signal conversion of the aircraft engine speed and exhaust temperature, as well as the calculation and processing of all types of signal parameters.

[0102] Figure 2 A perspective view of the data acquisition box 100 is shown. Figure 3 A top view of the data acquisition box 100 is shown. Figure 2 and Figure 3 As can be seen, the inner bottom plate of the data acquisition box 100 is equipped with a mounting rail 170 and a guide rail 180. The speed signal processing module 110 and the temperature signal processing module 120 are both mounted on the mounting rail 170 and can slide along it. During installation, the speed signal processing module 110 and the temperature signal processing module 120 are slidably connected to the mounting rail 170; during disassembly, the speed signal processing module 110 and the temperature signal processing module 120 are simply slid out of the mounting rail 170.

[0103] Similarly, the power module body 160, CPU module 150, pressure signal processing module 130, and analog signal processing module 140 can all be detachably mounted on the guide rail 180 and can all slide along the guide rail 180. During installation, the power module body 160, CPU module 150, pressure signal processing module 130, and analog signal processing module 140 are slidably connected to the guide rail 180; during disassembly, the power module body 160, CPU module 150, pressure signal processing module 130, and analog signal processing module 140 are simply slid out of the guide rail 180.

[0104] This design facilitates the installation and disassembly of the portable acquisition device, reducing its size and making it more convenient and faster. On the other hand, it also enables the simultaneous detection of multiple signal parameters, solving the problem of limited signal types due to complex outdoor environments.

[0105] Furthermore, the guide rail 180 and the clamp rail 170 are arranged parallel to each other, which is beneficial for the wiring connection between the modules.

[0106] Furthermore, handles can be installed on the outermost modules to make it easier for staff to install and remove the modules.

[0107] In one embodiment, by Figure 2 It can be clearly seen that the data acquisition box 100 is equipped with a speed signal interface 112, a temperature signal interface 122, a pressure signal interface 133, and a network signal interface 190.

[0108] Furthermore, the outer end of the speed signal interface 112 is connected to the speed test cable 111, and the inner end of the speed signal interface 112 is connected to the speed signal processing module 110. Here, the speed signal of the auxiliary power unit is transmitted to the data acquisition box 100 through the speed test cable 111, and then transmitted to the speed signal processing module 110 through the speed signal interface 112. The speed signal is shaped, filtered, and transformed into a standard voltage signal, and then converted into a digital signal by the analog signal processing module 140 and displayed on the mobile terminal 700.

[0109] Furthermore, the outer end of the temperature signal interface 122 is connected to the temperature test cable 121, and the inner end of the temperature signal interface 122 is connected to the temperature signal processing module 120. Here, the temperature signal of the auxiliary power device is transmitted to the data acquisition box 100 through the temperature test cable 121, and then transmitted to the temperature signal processing module 120 through the temperature signal interface 122. The temperature signal is shaped, filtered, and transformed into a standard voltage signal, and then converted into a digital signal by the analog signal processing module 140 and displayed on the mobile terminal 700.

[0110] Furthermore, the outer end of the pressure signal interface 133 is connected to the pressure test cable 132, and the inner end of the pressure signal interface 133 is connected to the pressure signal processing module 130. After receiving the pressure signal, the data acquisition box 100 transmits it to the analog signal processing module 140, converts it into a digital signal, and displays it on the mobile terminal 700 through the network signal interface 190.

[0111] Furthermore, the external end of the network signal interface 190 is connected to the mobile terminal 700 via a network cable, and the internal end of the network signal interface 190 is connected to the CPU module 150.

[0112] The data acquisition box 100 is connected to various types of test cables and mobile terminals 700 through various signal interfaces, thereby realizing the basic functions of the data acquisition box 100.

[0113] In one embodiment, by Figure 2 As can be seen, the power module includes a power module body 160, a power interface 161, and a power switch 162, all connected in pairs. Both the power interface 161 and the power switch 162 are mounted on the data acquisition box 100, while the power module body 160 is mounted on the guide rail 180. The power module body 160 supplies current to the entire portable testing device. The outer end of the power interface 161 connects to an external power source, while the inner end connects to the pressure signal processing module 130, the speed signal processing module 110, the temperature signal processing module 120, the analog signal processing module 140, and the CPU module 150, respectively. Since the pressure adapter box 200 is connected to the data acquisition box 100, the power module body 160 also supplies power to the pressure adapter box 200.

[0114] Here, the power supply is converted to 24V DC after passing through the power interface 161 and the power switch 162, and then supplies power to other modules, while illuminating the corresponding signal indicator 400.

[0115] Furthermore, indicator lights 400 are installed below all types of signal interfaces, power interface 161, and power switch 162. This allows staff to quickly understand the working status of each interface, promptly identify problematic interfaces, and improve work efficiency.

[0116] In one embodiment, such as Figure 4 and Figure 5 As shown, the pressure adapter box 200 is specifically designed. A pressure signal interface 133 is provided on one side wall of the pressure adapter box 200, and multiple pressure receiving units are evenly distributed on the opposite side wall of the pressure adapter box 200.

[0117] Each pressure receiving unit includes: a pressure adapter 210 and a pressure sensor 220 connected to each other;

[0118] The pressure adapter 210 is installed on the outer wall of the pressure adapter box 200. The receiving end of the pressure adapter 210 is connected to the aircraft auxiliary power unit through the pressure measuring hose 131, and the transmitting end of the pressure adapter 210 is connected to the pressure sensor 220.

[0119] The pressure sensor 220 is installed on the inner wall of the pressure adapter box 200. The receiving end of the pressure sensor 220 is connected to the pressure adapter 210, and the transmitting end of the pressure sensor 220 is connected to the pressure signal interface 133.

[0120] Here, to address the inconvenience of installing the auxiliary power unit (APU) within the confined space of an aircraft and the inability to directly measure the required pressure, a dedicated adapter pipe 300 was designed. This dedicated adapter pipe 300 includes a pressure testing adapter 310 for connecting to the pressure testing hose 131. Both ends of the pressure testing adapter 310 utilize flexible docking hoses 320 consistent with the APU interface, achieving compatibility with the APU structure. Figure 6 As shown, when using this portable testing device, it is necessary to first disconnect the pipelines at the following locations on the aircraft auxiliary power unit: air pressure after the auxiliary power unit starts the compressor, air pressure after starting the air pump, outlet pressure of the gas chamber vent valve, air pressure in the upper chamber of the gas chamber vent valve, air pressure in the lower chamber of the upper piston of the gas chamber vent valve, air pressure in the upper chamber of the lower piston of the gas chamber vent valve, air pressure in the lower chamber of the lower piston of the gas chamber vent valve, lubricating oil pressure at the auxiliary power unit inlet, fuel pressure at the auxiliary power unit inlet, starting I oil circuit pressure, starting I oil circuit pressure, and main fuel pressure. Then, replace the pipelines at the corresponding disconnection locations with a dedicated adapter pipe 300. This dedicated adapter pipe 300 consists of a pressure testing adapter 310 and connecting hoses 320 respectively installed at both ends of the pressure testing adapter 310. At this time, one end of the pressure testing hose 131 is connected to the pressure testing adapter 310, and the other end of the pressure testing hose 131 is connected to the pressure adapter 210.

[0121] In one embodiment, by Figure 2 As can be seen, first shock absorbers 500, preferably four shock-absorbing support pads, are installed at the four corners of the bottom of the data acquisition box 100. Second shock absorbers 600, preferably shock-absorbing pads, are also installed on the bottom plate of the pressure transfer box 200. This design gives the portable testing device a certain degree of shock resistance, making it more suitable for operation in complex outdoor environments.

[0122] Furthermore, the data acquisition box 100 in this application is also connected to the mobile terminal 700, thereby enabling the storage, display, and analysis of various acquired signal parameters. This facilitates staff in quickly and accurately determining the type and location of the fault and promptly troubleshooting it. The mobile terminal 700 is preferably a computer or laptop computer, and it is equipped with testing software.

[0123] It should be noted that in this embodiment, the data acquisition box 100 and the pressure transfer box 200 are designed as independent separate units, thus ensuring that the operator maintains a certain distance from the engine and effectively isolates the engine noise. The dimensions of the data acquisition box 100 do not exceed 250×200×150 mm, and its weight does not exceed 4 kg. The dimensions of the pressure transfer box 200 do not exceed 250×150×150 mm, and its weight does not exceed 3 kg. To prevent damage to the data acquisition box 100 and the pressure transfer box 200 from the external environment during use, both boxes are made of high-strength aluminum alloy, and shock-absorbing components are added to the base plate, making the entire testing equipment compact, lightweight, corrosion-resistant, and shock-resistant, better adaptable to the complex electromagnetic environment of the external field, and meeting the requirements for portability and mobility.

[0124] In this embodiment, the aircraft engine speed is taken from the 2500A speed sensor. Due to the special nature of the aircraft speed sensor, it cannot be directly read using conventional methods. Therefore, the output signal must first undergo preprocessing such as shaping and amplification before subsequent acquisition and processing of the speed signal can be performed. The temperature signal is taken from the K-82 connector. Simultaneously, to avoid affecting the original aircraft wiring, a dedicated connector was designed to redistribute the speed and temperature signals, thereby achieving synchronous display of aircraft flight parameters and the portable testing device, achieving the goal of simultaneous measurement and facilitating rapid recovery after use.

[0125] The second aspect of this embodiment proposes a method for troubleshooting starting faults in aircraft auxiliary power units. This method is used to troubleshoot starting faults detected by the aforementioned portable testing equipment, such as... Figure 7 As shown, the following steps may be included:

[0126] Step S101: Set the standard parameters for the aircraft auxiliary power unit.

[0127] Step S102: According to standard parameters, diagnose and troubleshoot different types of starting faults respectively.

[0128] The standard parameters include:

[0129] n represents rotational speed, in percentage (%).

[0130] t4 represents the exhaust temperature after the turbocharger, in °C;

[0131] P m This indicates the pressure of the lubricating oil, expressed in MPa.

[0132] t0 represents the ambient temperature, in °C;

[0133] P 起压 This indicates the air pressure after the air pump is started, in MPa.

[0134] P进 This indicates the pressure of the imported fuel, expressed in MPa.

[0135] P2 represents the pressure after the compressor, in MPa;

[0136] P 21 This indicates the compressor exhaust air pressure measured during the previous start-up process, in MPa.

[0137] P 22 This indicates the current measured air pressure after the compressor during startup, expressed in MPa.

[0138] P I This indicates the fuel pressure in oil circuit I, in MPa.

[0139] P Ⅱ This indicates the fuel pressure in oil circuit II, in MPa.

[0140] P 主 This indicates the main fuel line pressure, in MPa.

[0141] P 上上 This indicates the air pressure in the upper chamber of the piston on the vent valve of the gas collecting chamber, in MPa.

[0142] P 上下 This indicates the air pressure in the lower chamber of the upper piston of the vent valve in the gas collecting chamber, in MPa.

[0143] P 下上 This indicates the air pressure in the upper chamber of the piston below the vent valve in the gas collecting chamber, expressed in MPa.

[0144] P 下下 This indicates the air pressure in the lower chamber of the piston below the vent valve in the gas collecting chamber, expressed in MPa.

[0145] △P 下 This indicates the pressure difference between the upper and lower chambers of the piston under the vent valve in the gas collecting chamber, expressed in MPa.

[0146] △P 上 This indicates the pressure difference between the upper and lower chambers of the piston on the vent valve of the gas collecting chamber, expressed in MPa.

[0147] Types of starting faults include: sham start-up faults, surge faults during starting, and over-temperature faults during starting.

[0148] In one embodiment, diagnosing and troubleshooting faults during a dummy driving process includes:

[0149] If the first preset time after startup is reached and the result does not meet the requirement of n = 20 ± 2%, then n is diagnosed as unqualified and is excluded. In this embodiment, the first preset time is 32 seconds after the start button is pressed.

[0150] If n = 20 ± 2%, and P m If the pressure is <0.05 MPa, the diagnosis is P. m Those that fail to meet the standards will be excluded.

[0151] If n = 20 ± 2%, and P I =(P 进 If the value is +0.04*t0+0.49)±0.02MPa, then the diagnosis is P. I Those that fail to meet the standards will be excluded.

[0152] If n = 20 ± 2%, and P II -(P 进 If the pressure is +0.5) ± 0.2 MPa, then the diagnosis is P. Ⅱ Those that fail to meet the standards will be excluded.

[0153] When the second preset time after startup is reached, if P 起压 If the pressure is less than or equal to 0.02 MPa, the diagnosis is P. 起压 If it fails to meet the requirements, it will be excluded. In this embodiment, the second preset time is 4 seconds after startup.

[0154] Here, * indicates multiplication, and ≮ indicates not less than.

[0155] In one embodiment, diagnosing and eliminating surge faults includes:

[0156] When (P) 21 -P 22 ) / P 21 When ×100%≥1%, it is determined that a surge fault occurred at that moment during the startup process;

[0157] The surge fault is diagnosed and eliminated as follows:

[0158] If P 下下 If the pressure is ≥0.019MPa and P2 <0.098MPa, the fault is diagnosed as a shunt valve and should be eliminated.

[0159] If t0≤18℃, and before surge, ΔP 下 =(P 上下 -P 下下 If the pressure is greater than 0.02 MPa, the diagnosis is a faulty opening of the temperature valve, and the problem should be resolved.

[0160] If t0 > 18℃, and n ≤ 30%, and before surge, ΔP 下 =(P 上下 -P 下下 If the pressure is greater than 0.02 MPa, the fault is diagnosed as a large opening of the temperature valve, and the problem should be eliminated.

[0161] Before surge, if ΔP 上 =(P 上上 -P 上下 If the pressure is ≥0.014MPa, the diagnosis is an early closing fault of the upper piston, and the problem should be eliminated.

[0162] In one embodiment, diagnosing and troubleshooting over-temperature faults includes:

[0163] If n≤30% and t4≥540℃, then it is judged as a 30% over-temperature fault;

[0164] If n>30% and t4≥0.85*t0+610℃, then it is judged as a starting overheating fault;

[0165] Based on the identified over-temperature fault, the following diagnosis and troubleshooting steps were performed:

[0166] If P is within the third preset time after startup I If the pressure is not within the range of 0.4–0.8 MPa, the diagnosis is P. I Those that fail to meet the standards will be excluded.

[0167] If n is in the range of 35% to 40%, if P Ⅱ If the pressure is not within the range of 0.45–0.55 MPa, the diagnosis is P. Ⅱ Those that fail to meet the standards will be excluded.

[0168] If t4 = 0.85 * t0 + 610℃, the corresponding n is in the range of 30% to 50%, and when t0 > 18℃, if ΔP 下 =(P 上下 -P 下下 If the pressure is less than 0.02 MPa, the fault is diagnosed as a small opening of the temperature valve, and the problem should be eliminated.

[0169] In this context, * indicates multiplication.

[0170] It should be noted that in this embodiment, for the mobile device, in the default online monitoring state upon startup, clicking the "Stop Recording" button in the testing software will turn the button red, indicating that the collected signal parameter data is not being recorded. When recording is needed, clicking the "Start Recording" button will turn the button green, initiating recording. When it is necessary to determine the cause of a fault, clicking the "Diagnose" button will automatically analyze the fault and generate a diagnosis report, achieving a self-diagnostic effect. For ease of observation, the squareness of small-range signal parameter data is increased by 50 times, the exhaust temperature is reduced by 5 times, and the speed signal remains unchanged; the oscilloscope curve displays real-time data. Different colors are used to indicate the measurement parameter oscilloscope curves, making analysis and identification faster and more intuitive.

[0171] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the embodiments of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0172] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. In addition, those skilled in the art can combine and integrate the different embodiments or examples described in this specification.

[0173] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the scope of the technology disclosed in this application, and these modifications or substitutions should all be covered within the scope of protection of this application.

[0174] Other embodiments of this application will readily occur to those skilled in the art upon consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of this application that follow the general principles of this application and include common knowledge or customary techniques in the art not disclosed herein.

Claims

1. A portable detection device for starting faults in aircraft auxiliary power units, characterized in that, The portable testing device includes: The data acquisition box has a detachable pressure signal processing module, a speed signal processing module, and a temperature signal processing module that are mutually isolated on its inner bottom plate; the pressure signal processing module, the speed signal processing module, and the temperature signal processing module are respectively connected to an analog signal processing module, a CPU module, and a power supply module; The speed signal processing module is connected to the aircraft auxiliary power unit via a speed test cable, and the temperature signal processing module is connected to the aircraft auxiliary power unit via a temperature test cable. A pressure adapter box, one end of which is connected to the aircraft auxiliary power unit via a pressure testing hose, and the other end of which is connected to the pressure signal processing module via a pressure testing cable; Mobile terminal: The CPU module is communicatively connected to the mobile terminal; The power supply module is connected to both the CPU module and the analog signal processing module, and the analog signal processing module is connected to the CPU module; the mobile terminal is used to display the starting fault of the aircraft auxiliary power unit in real time. The data acquisition box is equipped with a speed signal interface, a temperature signal interface, a pressure signal interface and a network signal interface, respectively; The outer end of the speed signal interface is connected to the speed test cable, and the inner end of the speed signal interface is connected to the speed signal processing module. The outer end of the temperature signal interface is connected to the temperature test cable, and the inner end of the temperature signal interface is connected to the temperature signal processing module. The outer end of the pressure signal interface is connected to the pressure test cable, and the inner end of the pressure signal interface is connected to the pressure signal processing module. The external end of the network signal interface is connected to the mobile terminal via a network cable, and the internal end of the network signal interface is connected to the CPU module. The pressure signal interface is provided on one side wall of the pressure adapter box, and multiple pressure receiving units are evenly distributed on the opposite side wall of the pressure adapter box. Each of the pressure receiving units includes: a pressure adapter and a pressure sensor connected to each other; The pressure adapter is disposed on the outer side wall of the pressure adapter box. The receiving end of the pressure adapter is connected to the aircraft auxiliary power unit through the pressure measuring hose, and the transmitting end of the pressure adapter is connected to the pressure sensor. The pressure sensor is mounted on the inner wall of the pressure adapter box. The receiving end of the pressure sensor is connected to the pressure adapter, and the transmitting end of the pressure sensor is connected to the pressure signal interface. The aircraft auxiliary power unit is equipped with a dedicated adapter pipe, which includes a pressure testing adapter and connecting hoses respectively disposed at both ends of the pressure testing adapter; one end of the pressure testing hose is connected to the pressure testing adapter, and the other end of the pressure testing hose is connected to the pressure adapter.

2. The portable detection device for starting faults of aircraft auxiliary power units according to claim 1, characterized in that, The data acquisition box has a mounting rail on its inner bottom plate. The speed signal processing module and the temperature signal processing module are both mounted on the mounting rail and can slide along the mounting rail. The data acquisition box has a guide rail on its inner bottom plate. The power module, the CPU module, the pressure signal processing module and the analog signal processing module can all be detached and mounted on the guide rail, and can all slide along the guide rail. The guide rail and the clamping rail are arranged parallel to each other.

3. The portable detection device for starting faults of aircraft auxiliary power units according to claim 2, characterized in that, The power module includes a power module body, a power interface, and a power switch that are connected to each other in pairs. The power interface and the power switch are both located on the data acquisition box. The power module body is located on the guide rail. The outer end of the power interface is used to connect to an external power source. Signal indicator lights are provided below the speed signal interface, the temperature signal interface, the pressure signal interface, the network signal interface, the power interface, and the power switch, and all of the signal indicator lights are located on the data acquisition box.

4. The portable detection device for starting faults of aircraft auxiliary power units according to claim 3, characterized in that, The bottom of the data acquisition box is provided with a first shock absorber; the inner bottom plate of the pressure transfer box is provided with a second shock absorber.

5. A method for troubleshooting starting faults in aircraft auxiliary power units, characterized in that, This troubleshooting method is used to troubleshoot starting faults detected by the portable testing device according to any one of claims 1-4, and the troubleshooting method includes the following steps: Setting standard parameters for aircraft auxiliary power units; Based on the aforementioned standard parameters, different types of starting faults are diagnosed and eliminated respectively; The standard parameters include: n represents the rotational speed, expressed as % . t4 represents the exhaust temperature after the turbocharger, in °C; P m This indicates the pressure of the lubricating oil, expressed in MPa. t0 represents the ambient temperature, in °C; P 起压 This indicates the air pressure after the air pump is started, in MPa. P 进 This indicates the pressure of the imported fuel, in MPa. P2 represents the pressure after the compressor, in MPa; P 21 This indicates the compressor exhaust air pressure measured during the previous start-up process, in MPa. P 22 This indicates the current measured air pressure after the compressor during startup, expressed in MPa. P I This indicates the fuel pressure in oil circuit I, in MPa. P Ⅱ This indicates the fuel pressure in oil circuit II, in MPa. P 上上 This indicates the air pressure in the upper chamber of the piston on the vent valve of the gas collecting chamber, in MPa. P 上下 This indicates the air pressure in the lower chamber of the upper piston of the vent valve in the gas collecting chamber, expressed in MPa. P 下上 This indicates the air pressure in the upper chamber of the piston below the vent valve in the gas collecting chamber, expressed in MPa. P 下下 This indicates the air pressure in the lower chamber of the piston below the vent valve in the gas collecting chamber, expressed in MPa. △P 下 This indicates the pressure difference between the upper and lower chambers of the piston under the vent valve in the gas collecting chamber, expressed in MPa. △P 上 This indicates the pressure difference between the upper and lower chambers of the piston on the vent valve of the gas collecting chamber, expressed in MPa. The types of starting faults include: sham start-up process faults, surge faults during the starting process, and over-temperature faults during the starting process; Diagnosing and troubleshooting the aforementioned sham driving process faults includes: If the first preset time after startup is reached and the result does not meet n=20±2%, then n is diagnosed as unqualified and the process is eliminated. If n=20±2%, and P m If the pressure is <0.05 MPa, the diagnosis is P. m Those that fail to meet the standards will be excluded. If it meets the condition n=20±2%, and The diagnosis is Those that fail to meet the standards will be excluded. If n=20±2%, and P Ⅱ =(P 进 If the pressure is +0.5) ± 0.2 MPa, then the diagnosis is P. Ⅱ Those that fail to meet the standards will be excluded. When the second preset time after startup is reached, if P 起压 If the pressure is less than or equal to 0.02 MPa, the diagnosis is P. 起压 Those that fail to meet the standards will be excluded. in, ≮ indicates multiplication, and ≮ indicates not less than; Diagnosing and eliminating the surge fault includes: When (P) 21 -P 22 ) / P 21 When ×100%≥1%, it is determined that the surge fault occurred at that moment during the startup process; The surge fault was diagnosed and eliminated as follows: If P 下下 If the pressure is ≥0.019 MPa and P2 < 0.098 MPa, the fault is diagnosed as a shunt valve and should be eliminated. If t0≤18℃, and before surge, ΔP 下 =(P 下上 -P 下下 If the pressure is greater than 0.02 MPa, the diagnosis is a faulty opening of the temperature valve, and the problem should be resolved. If t0 > 18℃, and n ≤ 30%, and before surge, ΔP 下 =(P 下上 -P 下下 If the pressure is greater than 0.02 MPa, the fault is diagnosed as a large opening of the temperature valve, and the problem should be eliminated. Before surge, if ΔP 上 = (P 上上 -P 上下 If the pressure is ≥0.014MPa, the diagnosis is premature closing of the upper piston, and the problem should be resolved. Diagnosing and troubleshooting the over-temperature fault includes: If n≤30% and t4≥540℃, then it is judged as a 30% over-temperature fault; If n>30%, and If so, it is determined to be a starting overheating fault; Based on the identified over-temperature fault, the following diagnosis and troubleshooting steps were performed: If P I If the pressure is not within the range of 0.4~0.8 MPa, the diagnosis is P. I Those that fail to meet the standards will be excluded. If n is in the range of 35% to 40%, if P Ⅱ If the pressure is not within the range of 0.45~0.55 MPa, the diagnosis is P. Ⅱ Those that fail to meet the standards will be excluded. like When n is in the range of 30% to 50%, and when t0 > 18℃, if ΔP 下 =(P 下上 -P 下下 If the pressure is less than 0.02 MPa, the fault is diagnosed as a small opening of the temperature valve, and the problem should be eliminated. in, Indicates multiplication.

Images