A debugging system for an aeroengine monitoring device

Abstract

The application provides a debugging system of an aero-engine monitoring device, comprising: a debugging signal integration and transmission device, comprising a debugging signal generation and transmission module, a signal conditioning module and a multi-interface adapter connector module connected with each other; a debugging control terminal connected with the debugging signal integration and transmission device; wherein the multi-interface adapter connector module is connected with corresponding interfaces of the aero-engine monitoring device through a plurality of signal transmission interfaces; the debugging signal generation and transmission module comprises a signal generation and transmission controller, an analog signal input and output module and a digital signal input and output module; the signal conditioning module comprises a plurality of signal conditioning sub-modules corresponding to a plurality of aero-engine operating state signals; the plurality of signal conditioning sub-modules are respectively connected with the analog signal input and output module and the digital signal input and output module according to signal types.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aero-engine test, in particular to a debugging system of an aero-engine monitoring device. BACKGROUND

[0002] The purpose of an aero-engine health management system is to collect, record and process data in flight and ground tests to assist engine design, management, safe use, maintenance and logistics support. The engine monitoring device (EMU) is an important component of the aero-engine health management system, which can collect and store engine vibration, gas path, oil path, operation control and monitoring system working parameters to provide analyzable data for engine fault diagnosis and processing. Effective debugging of the aero-engine monitoring device is the basis for the effective application of the aero-engine monitoring device. Therefore, it is a topic to provide an efficient and convenient debugging system of the aero-engine monitoring device. SUMMARY

[0003] The technical problem to be solved by the present application is to provide a debugging system of an aero-engine monitoring device, which realizes efficient and convenient debugging of the aero-engine monitoring device.

[0004] To solve the above technical problems, the present application provides a debugging system of an aero-engine monitoring device, comprising: a debugging signal integration and transmission device, comprising a debugging signal generation and transmission module, a signal conditioning module and a multi-interface adapter connector module connected with each other; a debugging control terminal connected with the debugging signal integration and transmission device; wherein the multi-interface adapter connector module is connected with the corresponding interface of the aero-engine monitoring device through a plurality of signal transmission interfaces; the debugging signal generation and transmission module comprises a signal generation and transmission controller, an analog signal input and output module and a digital signal input and output module; the signal conditioning module comprises a plurality of signal conditioning sub-modules corresponding to a plurality of aero-engine operating state signals; the plurality of signal conditioning sub-modules are respectively connected with the analog signal input and output module and the digital signal input and output module according to the signal type.

[0005] In an embodiment of the present application, the plurality of signal conditioning sub-modules comprise a thermal resistance signal conditioning sub-module, a thermocouple signal conditioning sub-module, a gas pressure resistance signal conditioning sub-module and a voltage signal conditioning sub-module; the thermal resistance signal conditioning sub-module, the thermocouple signal conditioning sub-module, the gas pressure resistance signal conditioning sub-module and the voltage signal conditioning sub-module are connected with the analog signal input and output module.

[0006] In an embodiment of the present application, the plurality of signal conditioning sub-modules comprises a discrete quantity conditioning sub-module; the discrete quantity conditioning sub-module is connected with the digital signal input and output module.

[0007] In an embodiment of the present application, the plurality of signal conditioning sub-modules comprises a rotational speed frequency signal conditioning sub-module and a vibration charge signal conditioning sub-module; the rotational speed frequency signal conditioning sub-module and the vibration charge signal conditioning sub-module are connected with the analog signal input and output module.

[0008] In an embodiment of the present application, the multi-interface adapter connector module comprises a rotational speed signal input interface, an aviation plug connector and a first switch switching module; the first switch switching module comprises a first input end, a second input end, a third output end and a switching connection end; the aviation plug connector is connected with the vibration charge conditioning sub-module through a first connecting line to receive a vibration charge simulation signal and transmit the vibration charge simulation signal to the aviation engine monitoring device; the aviation plug connector is further connected with the third output end of the first switch switching module through a second connecting line; the first input end and the second input end of the first switch switching module are respectively connected with the rotational speed frequency signal conditioning sub-module and the rotational speed signal input interface; the first switch switching module connects the switching connection end to the first input end or the second input end based on a first switch control signal sent by the debugging control terminal, so as to connect a rotational speed frequency test signal transmitted by the rotational speed signal input interface or a rotational speed frequency simulation signal output by the rotational speed frequency signal conditioning sub-module to the third output end and transmit the rotational speed frequency simulation signal to the aviation engine monitoring device through the aviation plug connector.

[0009] In an embodiment of the present application, the rotational speed frequency test signal is generated by an engine electronic controller test piece connected with the rotational speed signal input interface.

[0010] In an embodiment of the present application, the rotational speed signal input interface is further connected with the analog signal input and output module through a third connecting line to transmit a rotational speed frequency test signal input by the rotational speed signal input interface.

[0011] In an embodiment of the present application, a first signal conversion device is further arranged between the rotational speed signal input interface and the first input end of the first switch switching module to perform communication type conversion on a rotational speed frequency test signal input by the rotational speed signal input interface.

[0012] In an embodiment of the present application, the rotational speed signal input interface comprises a bayonet nut connector.

[0013] In an embodiment of the present application, the debugging signal integration and transmission device further comprises a network adapter module, a first connection end of the network adapter module is connected with the debugging control terminal, and a second connection end of the network adapter module is connected with the debugging signal generation and transmission module and the multi-interface adapter connector module, so as to serve as a first transmission path of the debugging instruction and data.

[0014] In an embodiment of the present application, the debugging signal integration and transmission device further comprises a universal serial bus module; the debugging signal generation and transmission module comprises a serial communication module and an aviation Ethernet communication module; a first connection end of the universal serial bus module is connected with the debugging control terminal, and a second connection end of the universal serial bus module is connected with the serial communication module and the aviation Ethernet communication module, so as to serve as a second transmission path of the debugging instruction and data.

[0015] In an embodiment of the present application, the debugging control terminal comprises a debugging control software module; the debugging control software module comprises a debugging system calibration module, a debugging system calibration module, a debugging data storage and management module, and a debugging process control module.

[0016] In an embodiment of the present application, the debugging signal integration and transmission device further comprises a power supply module; a first connection end of the power supply module is connected with a power input signal, and a second connection end of the power supply module is connected with the debugging signal integration and transmission device and the multi-interface adapter connector module.

[0017] Compared with the prior art, the present application has the following advantages: the technical scheme of the present application can realize the simultaneous injection of the rotational frequency signal simulation value and the vibration charge signal simulation value into the aero-engine monitoring device, thereby providing data support for the effective debugging of the aero-engine monitoring device; in addition, the aero-engine monitoring device of different configurations can be adapted. BRIEF DESCRIPTION OF DRAWINGS

[0018] The accompanying drawings are included to provide a further understanding of the present application, and are incorporated in and constitute a part of this application, illustrate embodiments of the present application, and together with the description serve to explain the principle of the present application.

[0019] In the drawings:

[0020] Figure 1 is a composition schematic diagram of the debugging system of the aero-engine monitoring device of an embodiment of the present application.

[0021] Figure 2 is a partial composition schematic diagram of the debugging system of the aero-engine monitoring device of an embodiment of the present application.

[0022] Figure 3is a constituent schematic diagram of a debugging control software module of an aero-engine monitoring device according to an embodiment of the present application. DETAILED DESCRIPTION

[0023] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiment description will be briefly introduced as follows. Obviously, the drawings in the following description are only some examples or embodiments of the present application, and for those skilled in the art, the present application can also be applied to other similar scenarios without creative labor on the basis of the drawings. Unless it is clear from the language context or otherwise indicated, the same reference numbers in the drawings represent the same structure or operation.

[0024] As shown in the present application and claims, unless the context clearly indicates otherwise, the words "one", "a", "an", and / or "the" do not specify a singular form, but can also include a plural form. Generally, the terms "comprise" and "include" only indicate the inclusion of the steps and elements explicitly identified, and these steps and elements do not constitute an exclusive list, and the method or device can also include other steps or elements.

[0025] Unless specifically stated otherwise, the relative arrangement of the components and steps, numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present application. At the same time, it should be understood that the sizes of the various parts shown in the drawings are not drawn in accordance with the actual proportional relationship.

[0026] In addition, it should be noted that the use of the words "first", "second", and the like to define parts is only for the convenience of distinguishing the corresponding parts, and unless otherwise stated, the above words do not have special meanings, and therefore cannot be understood as limiting the scope of protection of the present application. In addition, although the terms used in the present application are selected from well-known and commonly used terms, some terms mentioned in the specification of the present application may be selected by the applicant according to his or her judgment, and the detailed meanings thereof are described in the relevant parts of the description. In addition, the present application is not only required to be understood by the actual terms used, but also by the meaning implied by each term.

[0027] It will be understood that when a component is referred to as being "on" another component, "connected to" another component, "coupled to" another component, or "contacting" another component, it can be directly on, connected, coupled, or contacting the other component, or intervening components can be present. In contrast, when a component is referred to as being "directly on," "directly connected to," "directly coupled to," or "directly contacting" another component, there are no intervening components present. Likeaiy, when a first component is referred to as being "electrically in contact with" or "electrically coupled to" a second component, there is an electrical path between the first component and the second component that allows a flow of electrical current. The electrical path can include capacitors, coupled inductors, and / or other components that allow a flow of electrical current, even if there is no direct contact between electrically conductive components.

[0028] Embodiments of the present application describe a debugging system of an aero-engine monitoring device.

[0029] Figure 1 is a schematic diagram of a debugging system of an aero-engine monitoring device according to an embodiment of the present application. Referring to Figure 1 The debugging system of an aero-engine monitoring device 100 includes a debugging signal integration and transmission device 101 and a debugging control terminal 102.

[0030] The debugging signal integration and transmission device 101 includes a debugging signal generation and transmission module 111, a signal conditioning module 112, and a multi-interface adapter connector module 113 connected to each other. The debugging control terminal 102 is connected to the debugging signal integration and transmission device 101.

[0031] In some embodiments, the multi-interface adapter connector module 113 is connected to corresponding interfaces of the aero-engine monitoring device 181 through a plurality of signal transmission interfaces. The debugging signal generation and transmission module 111 includes a signal generation and transmission controller 121, an analog signal input and output module 122, and a digital signal input and output module 123. The signal conditioning module 112 includes a plurality of signal conditioning sub-modules corresponding to a plurality of aero-engine operating state signals. The plurality of signal conditioning sub-modules are respectively connected to the analog signal input and output module 122 and the digital signal input and output module 123 according to the signal types.

[0032] In some embodiments, the plurality of signal conditioning sub-modules includes a thermal resistance signal conditioning sub-module 132, a thermal couple signal conditioning sub-module 133, a gas pressure resistance signal conditioning sub-module 134, and a voltage signal conditioning sub-module 136. The thermal resistance signal conditioning sub-module 132, the thermal couple signal conditioning sub-module 133, the gas pressure resistance signal conditioning sub-module 134, and the voltage signal conditioning sub-module 136 are connected to the analog signal input and output module 122. The voltage signal conditioning sub-module 136, for example, attenuates a voltage signal with a high amplitude to a voltage signal with a low amplitude, so as to reach the input range of the acquisition module of the aero-engine monitoring device 181.

[0033] In some embodiments, the plurality of signal conditioning sub-modules further includes a discrete quantity conditioning sub-module 137. The discrete quantity conditioning sub-module 137 is connected to the digital signal input and output module 123. The discrete quantity conditioning sub-module 137, for example, can provide a ‘ground / disconnected’ discrete signal and a ‘power supply (e.g. 28V) / disconnected’ discrete signal, so as to provide a power supply signal and a ground signal for the operation debugging of the aero-engine monitoring device 181.

[0034] The plurality of signal conditioning sub-modules can further include a rotational speed frequency signal conditioning sub-module 131 and a vibration charge signal conditioning sub-module 135. The rotational speed frequency signal conditioning sub-module 131 and the vibration charge signal conditioning sub-module 135 are connected to the analog signal input and output module 122. The rotational speed frequency signal is directly presented as a frequency signal (in Hz), and after signal value conversion, a rotational speed signal (in r / s) can be obtained.

[0035] Figure 2 FIG. 1 is a schematic diagram of a part of a debugging system of an aero-engine monitoring device according to an embodiment of the present application.

[0036] In some embodiments, referring to Figure 1 and Figure 2 the multi-interface adapter connector module 113 includes a rotational speed signal input interface 201, an aero plug connector 202, and a first switch switching module 231. The first switch switching module 231 includes a first input end 241, a second input end 242, a third output end 243, and a switching connection end 244. The aero plug connector 202 is connected to the vibration charge signal conditioning sub-module 135 through a first connection line 211, so as to receive a vibration charge simulation signal and transmit the vibration charge simulation signal to the aero-engine monitoring device 181. The aero plug connector 202 is further connected to the third output end 243 of the first switch switching module 231 through a second connection line 212. The first input end 241 and the second input end 242 of the first switch switching module 231 are respectively connected to the rotational speed frequency signal conditioning sub-module 131 and the rotational speed signal input interface 201.

[0037] The first switch switching module 231 connects the switching connection end 244 to the first input end 241 or the second input end 242 based on the first switching control signal sg issued by the debugging control terminal 102, so as to connect the rotation speed frequency test signal sr transmitted by the rotation speed signal input interface 201 or the rotation speed frequency simulation signal output by the rotation speed frequency signal conditioning sub-module 131 to the third output end 243, and transmit the signal to the aero-engine monitoring device 181 through the aero plug connector 202. The rotation speed frequency test signal sr is generated by, for example, an engine electronic controller (EEC) test piece connected to the rotation speed signal input interface 201.

[0038] In some embodiments, the rotation speed signal input interface 201 is also connected to the analog signal input and output module 122 through a third connection line 215, so as to transmit the rotation speed frequency test signal sr input by the rotation speed signal input interface 201. A first signal conversion device 251 is further arranged between the rotation speed signal input interface 201 and the first input end 241 of the first switch switching module 231, so as to perform communication type conversion on the rotation speed frequency test signal sr input by the rotation speed signal input interface 201.

[0039] In some embodiments, the rotation speed signal input interface 201 includes a bayonet nut connector (BNC) or other types of signal transmission interfaces.

[0040] Continuing to refer to Figure 1 In some embodiments, the debugging signal integration and transmission device 101 further includes a network adapter module 141, a first connection end of the network adapter module 141 being connected to the debugging control terminal 102, and a second connection end of the network adapter module 141 being connected to the debugging signal generation and transmission module 111 and the multi-interface adapter connector module 113, so as to serve as a first transmission path for debugging instructions and data.

[0041] The debugging signal integration and transmission device 101 further includes a universal serial bus module 151. The debugging signal generation and transmission module 111 includes a serial port communication module 173 and an aero Ethernet communication module 170. A first connection end of the universal serial bus module 151 is connected to the debugging control terminal 102, and a second connection end of the universal serial bus module 151 is connected to the serial port communication module 173 and the aero Ethernet communication module 170, so as to serve as a second transmission path for debugging instructions and data. The aero Ethernet communication module 170 may, for example, further include an ARINC664 (or an aeronautical full duplex switched Ethernet, AFDX) communication module 171 and an ARINC429 communication module 172.

[0042] In some embodiments, the debugging signal integration and transmission device 101 further comprises a power supply module 161. A first connection end of the power supply module 161 is connected to a power input signal 191, and a second connection end of the power supply module 161 is connected to the debugging signal integration and transmission device 101 and the multi-interface adapter connector module 113. The debugging signal generation and transmission module 111 further comprises, for example, a serial port module 125 and a debugging oscilloscope access module 174. The serial port module 125 is connected to the power supply module 161 to access the power supply signal. The debugging oscilloscope access module 174 can be connected to an oscilloscope to observe and record various signals during system operation and debugging.

[0043] The debugging system of the aero-engine monitoring device of the present application can simultaneously inject a simulated speed frequency signal and a simulated vibration charge signal into the aero-engine monitoring device, thereby providing data support for effective debugging of the aero-engine monitoring device.

[0044] Figure 3 FIG. 1 is a schematic diagram of a debugging control software module of an aero-engine monitoring device according to an embodiment of the present application.

[0045] In some embodiments, referring to Figures 1 to 3 , the debugging control terminal 102 comprises a debugging control software module 301. The debugging control software module 301 comprises a debugging system calibration module 302, a debugging system calibration module 303, a debugging data storage and management module 304, and a debugging process control module 305. The debugging control software module 301 can further comprise basic function modules, such as a system login function module, a permission configuration and verification module, and a system user management module, etc.

[0046] The debugging system calibration module 302 uses a standard data source to control the standard source to meet a certain standard environment, compares the measurement value of the aero-engine monitoring device, and fits to calculate the calibration coefficient. During the debugging system operation, the debugging control terminal 102 displays the data acquisition value and the corresponding waveform curve in real time. After the acquisition is completed, two arrays of acquisition values and actual engineering values are generated, and the calibration coefficient is calculated by linear fitting. The fitting method can be selected from, for example, the least squares method, the least residual method, or the double plane method, etc. The debugging system calibration module 303 is used to calibrate the analog signal input and output channels and the digital signal input and output channels, and to complete the conversion between the acquisition value and the actual engineering value of the system channel.

[0047] The debugging system of the aero-engine monitoring device of the present application can adapt to aero-engine monitoring devices of different configurations; and can effectively debug aero-engine monitoring devices with different parameter monitoring functions.

[0048] Having described the basic concepts, it is obvious that the above-described application disclosure is merely an example for the person skilled in the art, and does not constitute a limitation on the present application. Although not explicitly described herein, the person skilled in the art can make various modifications, improvements and modifications to the present application. Such modifications, improvements and modifications are suggested in the present application, so such modifications, improvements and modifications still fall within the spirit and scope of the exemplary embodiments of the present application.

[0049] Meanwhile, specific words are used in the present application to describe the embodiments of the present application. As "one embodiment", "an embodiment", and / or "some embodiments" means a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that the "an embodiment" or "one embodiment" or "an alternative embodiment" mentioned in different places in the specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be properly combined.

[0050] Some aspects of the present application can be performed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The above hardware or software can be referred to as "data blocks", "modules", "engines", "units", "components" or "systems". The processor can be one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors or combinations thereof.

[0051] Similarly, it should be noted that, in order to simplify the description of the present application and to help understand one or more embodiments of the present application, sometimes multiple features are combined into one embodiment, figure or description thereof in the foregoing description of the embodiments of the present application. However, this method of disclosure does not mean that the features required by the present application are more than the features mentioned in the claims. In fact, the features of the embodiments are less than all the features of the above-mentioned single embodiment.

[0052] Although the present application has been described with reference to the current specific embodiments, those skilled in the art should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or replacements can be made without departing from the spirit of the present application. Therefore, any changes, modifications and variations to the above-described embodiments within the spirit and scope of the present application will fall within the scope of the claims of the present application.

Claims

1. A debugging system for an aircraft engine monitoring device, comprising: A debugging signal integration and transmission device, comprising an interconnected debugging signal generation and transmission module, a signal conditioning module, and a multi-interface adapter connector module; A debugging control terminal is integrated with and connected to the debugging signal transmission device. The multi-interface adapter connector module is connected to the corresponding interface of the aero-engine monitoring device through multiple signal transmission interfaces; the debugging signal generation and transmission module includes a signal generation and transmission controller, an analog signal input and output module, and a digital signal input and output module; the signal conditioning module includes multiple signal conditioning sub-modules corresponding to various aero-engine operating status signals. The plurality of signal conditioning submodules are respectively connected to the analog signal input and output module and the digital signal input and output module according to the signal type; The plurality of signal conditioning submodules include a rotational speed and frequency signal conditioning submodule and a vibration charge signal conditioning submodule; the rotational speed and frequency signal conditioning submodule and the vibration charge signal conditioning submodule are connected to the analog signal input and output module; The multi-interface adapter connector module includes a speed signal input interface, an aviation plug connector, and a first switch switching module. The first switch switching module includes a first input terminal, a second input terminal, a third output terminal, and a switching connection terminal. The aviation plug connector is connected to the vibration charge conditioning submodule via a first connecting line to receive vibration charge simulation signals and transmit them to the aero-engine monitoring device. The aviation plug connector is also connected to the third output terminal of the first switch switching module via a second connecting line. The first input terminal and the second input terminal of the first switch switching module are respectively connected to the speed signal input interface and the speed frequency signal conditioning submodule. Based on a first switching control signal issued by the debugging control terminal, the first switch switching module connects the switching connection terminal to the first input terminal or the second input terminal to connect the speed frequency test signal transmitted by the speed signal input interface or the speed frequency simulation signal output by the speed frequency signal conditioning submodule to the third output terminal, and transmits it to the aero-engine monitoring device through the aviation plug connector.

2. The debugging system for the aircraft engine monitoring device according to claim 1, characterized in that, The plurality of signal conditioning submodules include a resistance temperature detector (RTD) signal conditioning submodule, a thermocouple signal conditioning submodule, a gas pressure resistance signal conditioning submodule, and a voltage signal conditioning submodule; the RTD signal conditioning submodule, the thermocouple signal conditioning submodule, the gas pressure resistance signal conditioning submodule, and the voltage signal conditioning submodule are connected to the analog signal input and output module.

3. The debugging system for the aircraft engine monitoring device according to claim 1, characterized in that, The plurality of signal conditioning submodules include a discrete quantity conditioning submodule; the discrete quantity conditioning submodule is connected to the digital signal input and output module.

4. The debugging system for the aircraft engine monitoring device according to claim 1, characterized in that, The speed frequency test signal is generated by an engine electronic controller test piece connected to the speed signal input interface.

5. The debugging system for the aircraft engine monitoring device according to claim 1, characterized in that, The speed signal input interface is also connected to the analog signal input and output module via a third connection line to transmit the speed frequency test signal input by the speed signal input interface.

6. The debugging system for the aircraft engine monitoring device according to claim 1, characterized in that, A first signal conversion device is also provided between the speed signal input interface and the first input terminal of the first switch switching module to convert the communication type of the speed frequency test signal input through the speed signal input interface.

7. The debugging system for the aircraft engine monitoring device according to claim 1, characterized in that, The rotational speed signal input interface includes a bayonet nut connector.

8. The debugging system for the aircraft engine monitoring device according to claim 1, characterized in that, The debugging signal integration and transmission device further includes a network adapter module. The first connection end of the network adapter module is connected to the debugging control terminal, and the second connection end of the network adapter module is connected to the debugging signal generation and transmission module and the multi-interface adapter connector module, so as to serve as the first transmission path for debugging commands and data.

9. The debugging system for the aircraft engine monitoring device according to claim 1, characterized in that, The debugging signal integration and transmission device further includes a universal serial bus module; the debugging signal generation and transmission module includes a serial communication module and an avionics Ethernet communication module; the first connection end of the universal serial bus module is connected to the debugging control terminal, and the second connection end of the universal serial bus module is connected to the serial communication module and the avionics Ethernet communication module, so as to serve as a second transmission path for debugging commands and data.

10. The debugging system for the aircraft engine monitoring device according to claim 1, characterized in that, The debugging control terminal includes a debugging control software module; The debugging control software module includes a debugging system calibration module, a debugging system standardization module, a debugging data storage and management module, and a debugging process control module.

11. The debugging system for the aircraft engine monitoring device according to claim 1, characterized in that, The debugging signal integration and transmission device also includes a power supply module; the first connection terminal of the power supply module is connected to the power input signal, and the second connection terminal of the power supply module is connected to the debugging signal integration and transmission device and the multi-interface adapter connector module.

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