Debugging system of aero-engine monitoring device

Abstract

The invention provides a debugging system for an aero-engine monitoring device, and the system comprises a debugging signal integration and transmission device which comprises a debugging signal generation and transmission module, a signal conditioning module and a multi-interface adapter connector module which are connected with one another; the debugging control terminal is connected with the debugging signal integration and transmission device; wherein the multi-interface adaptive 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 various aero-engine operation state signals; and 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 invention mainly relates to the field of aircraft engine testing, and in particular to a debugging system for an aircraft engine monitoring device. Background Art

[0002] The purpose of an aircraft engine health management system is to collect, record and process data from flight and ground tests to assist in engine design, management, safe use, maintenance and logistics support. The Engine Monitor Unit (EMU) is an important component of an aircraft engine health management system. It can collect and store the operating parameters of the engine vibration, gas circuit, oil circuit, operation control and monitoring system, and provide analyzable data for engine fault diagnosis and processing. The effective debugging of the aircraft engine monitoring unit is the basis for the effective application of the aircraft engine monitoring unit. Therefore, providing an efficient and convenient debugging system for aircraft engine monitoring units is a topic that needs to be addressed. Summary of the invention

[0003] The technical problem to be solved by the present invention is to provide a debugging system for an aircraft engine monitoring device, so as to realize efficient and convenient debugging of the aircraft engine monitoring device.

[0004] In order to solve the above technical problems, the present invention provides a debugging system for an aircraft 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 that are interconnected; a debugging control terminal, connected to the debugging signal integration and transmission device; wherein the multi-interface adapter connector module is connected to the corresponding interface of the aircraft engine monitoring device through multiple 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 multiple signal conditioning sub-modules corresponding to multiple aircraft engine operating status signals; the multiple signal conditioning sub-modules are respectively connected to the analog signal input and output module and the digital signal input and output module according to the signal type.

[0005] In one embodiment of the present invention, the multiple signal conditioning submodules include a thermistor signal conditioning submodule, a thermocouple signal conditioning submodule, a gas pressure resistance signal conditioning submodule and a voltage signal conditioning submodule; the thermistor 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.

[0006] In one embodiment of the present invention, 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.

[0007] In one embodiment of the present invention, the multiple signal conditioning submodules include a rotation speed frequency signal conditioning submodule and a vibration charge signal conditioning submodule; the rotation speed frequency signal conditioning submodule and the vibration charge signal conditioning submodule are connected to the analog signal input and output module.

[0008] In one embodiment of the present invention, 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 end, a second input end, a third output end and a switching connection end; the aviation plug connector is connected to the vibration charge conditioning submodule through a first connecting line to receive a vibration charge simulation signal and transmit it to the aircraft engine monitoring device; the aviation plug connector is also connected to 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 to the speed frequency signal conditioning submodule and the 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 the first switching control signal sent by the debugging control terminal, so as 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 end, and transmit it to the aircraft engine monitoring device through the aviation plug connector.

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

[0010] In one embodiment of the present invention, the rotation speed signal input interface is further connected to the analog signal input and output module via a third connecting line to transmit the rotation speed frequency test signal input by the rotation speed signal input interface.

[0011] In one embodiment of the present invention, a first signal conversion device is further provided between the speed signal input interface and the first input end of the first switch switching module to perform communication type conversion on the speed frequency test signal input through the speed signal input interface.

[0012] In one embodiment of the present invention, the rotation speed signal input interface includes a bayonet nut connector.

[0013] In one embodiment of the present invention, the debug signal integration and transmission device also includes a network adapter module, a first connection end of the network adapter module is connected to the debug control terminal, and a second connection end of the network adapter module is connected to the debug signal generation and transmission module and the multi-interface adapter connector module to serve as a first transmission path for debug instructions and data.

[0014] In one embodiment of the present invention, the debugging signal integration and transmission device also includes a universal serial bus module; the debugging signal generation and transmission module includes a serial port communication module and an aviation 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 port communication module and the aviation Ethernet communication module to serve as a second transmission path for debugging instructions and data.

[0015] In one embodiment of the present invention, the debugging control terminal includes a debugging control software module; the debugging control software module includes 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 one embodiment of the present invention, the debug signal integration and transmission device also includes a power supply module; the first connection end of the power supply module is connected to the power input signal, and the second connection end of the power supply module is connected to the debug signal integration and transmission device and the multi-interface adapter connector module.

[0017] Compared with the prior art, the present invention has the following advantages: the technical solution of the present application can realize the simultaneous injection of the rotational speed frequency signal simulation value and the vibration charge signal simulation value into the aircraft engine monitoring device, providing data support for the effective debugging of the aircraft engine monitoring device; in addition, it can also adapt to aircraft engine monitoring devices of different configurations. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0019] In the attached figure:

[0020] Figure 1 It is a schematic diagram of the composition of a debugging system of an aircraft engine monitoring device according to an embodiment of the present application.

[0021] Figure 2 It is a schematic diagram of the partial composition of a debugging system of an aircraft engine monitoring device according to an embodiment of the present application.

[0022] Figure 3It is a schematic diagram of the composition of the debugging control software module of the aircraft engine monitoring device according to one 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 following is a brief introduction to the drawings required for the description of the embodiments. Obviously, the drawings described below are only some examples or embodiments of the present application. For ordinary technicians in this field, the present application can also be applied to other similar scenarios based on these drawings without creative work. Unless it is obvious from the language environment or otherwise explained, the same reference numerals in the figures represent the same structure or operation.

[0024] As shown in this application and claims, unless the context clearly indicates an exception, the words "a", "an", "an" and / or "the" do not refer to the singular and may also include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0025] Unless otherwise specifically stated, the relative arrangement of the components and steps described in these embodiments, numerical expressions and numerical values ​​do not limit the scope of the present application. Meanwhile, it should be understood that for ease of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship.

[0026] In addition, it should be noted that the use of words such as "first" and "second" to define components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above words have no special meaning and cannot be understood as limiting the scope of protection of this application. In addition, although the terms used in this application are selected from well-known and commonly used terms, some terms mentioned in the specification of this application may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this article. In addition, it is required to understand this application not only by the actual terms used, but also by the meaning implied by each term.

[0027] It should 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 may be directly on, connected to, coupled to, or contacting the other component, or there may be intervening components. In contrast, when a component is referred to as being "directly on another component," "directly connected to," "directly coupled to," or "directly contacting" another component, there are no intervening components. Similarly, 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 current to flow. The electrical path may include capacitors, coupled inductors, and / or other components that allow current to flow, even without direct contact between conductive components.

[0028] The embodiment of the present application describes a debugging system for an aircraft engine monitoring device.

[0029] Figure 1 Schematic diagram of the composition of the debugging system of the aircraft engine monitoring device according to one embodiment of the present application. Figure 1 The debugging system 100 of the aircraft engine monitoring device includes a debugging signal integration and transmission device 101 and a debugging control terminal 102 .

[0030] The debugging signal integration and transmission device 101 comprises a debugging signal generation and transmission module 111, a signal conditioning module 112 and a multi-interface adapter connector module 113 which are 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 the corresponding interface of the aircraft engine monitoring device 181 through multiple 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 multiple signal conditioning submodules corresponding to multiple aircraft engine operating status signals. The multiple signal conditioning submodules 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 type.

[0032] In some embodiments, the plurality of signal conditioning submodules include a thermal resistor signal conditioning submodule 132, a thermocouple signal conditioning submodule 133, a gas pressure resistance signal conditioning submodule 134, and a voltage signal conditioning submodule 136. The thermal resistor signal conditioning submodule 132, the thermocouple signal conditioning submodule 133, the gas pressure resistance signal conditioning submodule 134, and the voltage signal conditioning submodule 136 are connected to the analog signal input and output module 122. The voltage signal conditioning submodule 136, for example, attenuates a voltage signal with a higher amplitude into a voltage signal with a lower amplitude so that it reaches the input range of the acquisition module of the aircraft engine monitoring device 181.

[0033] In some embodiments, the plurality of signal conditioning submodules further include a discrete quantity conditioning submodule 137. The discrete quantity conditioning submodule 137 is connected to the digital signal input and output module 123. The discrete quantity conditioning submodule 137 can, for example, provide a 'ground / disconnect' discrete signal and a 'power supply (e.g., 28V) / disconnect' discrete signal to provide a power supply signal and a ground signal for the operation debugging of the aircraft engine monitoring device 181.

[0034] The plurality of signal conditioning submodules may further include a rotation speed frequency signal conditioning submodule 131 and a vibration charge signal conditioning submodule 135. The rotation speed frequency signal conditioning submodule 131 and the vibration charge signal conditioning submodule 135 are connected to the analog signal input and output module 122. The rotation speed frequency signal is directly presented as a frequency signal (in Hertz, Hz), and after the signal value is converted, a rotation speed signal (in revolutions per second, r / s) can be obtained.

[0035] Figure 2 It is a schematic diagram of the partial composition of a debugging system of an aircraft engine monitoring device according to an embodiment of the present application.

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

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

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

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

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

[0041] The debugging signal integration and transmission device 101 also includes a universal serial bus module 151. The debugging signal generation and transmission module 111 includes a serial communication module 173 and an aviation Ethernet communication module 170. The first connection end of the universal serial bus module 151 is connected to the debugging control terminal 102, and the second connection end of the universal serial bus module 151 is connected to the serial communication module 173 and the aviation Ethernet communication module 170 to serve as a second transmission path for debugging instructions and data. The aviation Ethernet communication module 170 may also include, for example, an ARINC664 (or avionics 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 includes a power supply module 161. The first connection end of the power supply module 161 is connected to the power input signal 191, and the 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 also includes, 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 aircraft engine monitoring device of the present application can realize the simultaneous injection of the rotational speed frequency signal simulation value and the vibration charge signal simulation value into the aircraft engine monitoring device, thereby providing data support for the effective debugging of the aircraft engine monitoring device.

[0044] Figure 3 It is a schematic diagram of the composition of the debugging control software module of the aircraft engine monitoring device according to one embodiment of the present application.

[0045] In some embodiments, reference Figures 1 to 3 , the debugging control terminal 102 includes a debugging control software module 301. The debugging control software module 301 includes 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 may also include basic function modules, such as a system login function module, a permission configuration and verification module, and a system user management module.

[0046] The debugging system calibration module 302 uses a standard data source, controls the standard source to meet a certain standard environment, compares it with the measured value of the aircraft engine monitoring device, and fits and calculates the calibration coefficient. During the operation of the debugging system, 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 straight line fitting. The fitting method can be, for example, the least squares method, the minimum residual method, or the double square method. The debugging system calibration module 303 is used to perform channel calibration on the analog signal input and output channels and the digital signal input and output channels, and complete the conversion between the acquisition value and the actual engineering value of the system channel.

[0047] The debugging system of the aircraft engine monitoring device of the present application can adapt to aircraft engine monitoring devices of different configurations; and can realize effective debugging of aircraft engine monitoring devices with different parameter monitoring functions.

[0048] The basic concepts have been described above. Obviously, for those skilled in the art, the above invention disclosure is only used as an example and does not constitute a limitation of the present application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements and amendments to the present application. Such modifications, improvements and amendments are suggested in the present application, so such modifications, improvements and amendments still belong to the spirit and scope of the exemplary embodiments of the present application.

[0049] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this 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 appropriately combined.

[0050] Some aspects of the present application may 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 may be referred to as "data blocks", "modules", "engines", "units", "components" or "systems". The processor may 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 disclosure of this application and thus help understand one or more embodiments of the invention, in the above description of the embodiments of this application, multiple features are sometimes combined into one embodiment, figure or description thereof. However, this disclosure method does not mean that the features required by the object of this 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 single embodiment disclosed above.

[0052] Although the present application has been described with reference to the current specific embodiments, ordinary technicians in this technical field should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or substitutions may be made without departing from the spirit of the present application. Therefore, as long as the changes and modifications to the above embodiments are within the essential spirit of the present application, they 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 debug signal integration and transmission device, comprising a debug signal generation and transmission module, a signal conditioning module and a multi-interface adapter connector module connected to each other; A debugging control terminal connected to the debugging signal integration and transmission device; The multi-interface adapter connector module is connected to the corresponding interfaces of the aircraft 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 submodules corresponding to multiple aircraft 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 signal types.

2. The debugging system of the aircraft engine monitoring device according to claim 1, characterized in that: The multiple signal conditioning submodules include a thermal resistor signal conditioning submodule, a thermocouple signal conditioning submodule, a gas pressure resistance signal conditioning submodule and a voltage signal conditioning submodule; the thermal resistor 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 of 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 of the aircraft engine monitoring device according to claim 1, characterized in that: The multiple signal conditioning submodules include a rotation speed frequency signal conditioning submodule and a vibration charge signal conditioning submodule; the rotation speed frequency signal conditioning submodule and the vibration charge signal conditioning submodule are connected to the analog signal input and output module.

5. The debugging system of the aircraft engine monitoring device according to claim 4, characterized in that: 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 end, a second input end, a third output end and a switching connection end; The aviation plug connector is connected to the vibration charge conditioning submodule via a first connection line to receive the vibration charge simulation signal and transmit it to the aircraft engine monitoring device; the aviation plug connector is also connected to the third output end of the first switch switching module via a second connection line; The first input end and the second input end of the first switch switching module are respectively connected to the speed signal input interface and the speed frequency signal conditioning submodule; Based on the first switching control signal issued by the debugging control terminal, the first switch switching module connects the switching connection end to the first input end or the second input end, so as 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 end, and transmit it to the aircraft engine monitoring device through the aviation plug connector.

6. The debugging system of the aircraft engine monitoring device according to claim 5, characterized in that: The speed frequency test signal is generated by an engine electronic controller test piece connected to the speed signal input interface.

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

8. The debugging system of the aircraft engine monitoring device according to claim 5, characterized in that: A first signal conversion device is also provided between the speed signal input interface and the first input end of the first switch switching module to perform communication type conversion on the speed frequency test signal input through the speed signal input interface.

9. The debugging system of the aircraft engine monitoring device according to claim 5, characterized in that: The speed signal input interface includes a bayonet nut connector.

10. The debugging system of the aircraft engine monitoring device according to claim 1, characterized in that: The debugging signal integration and transmission device also includes a network adapter module, a first connection end of the network adapter module is connected to the debugging control terminal, and a 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 to serve as a first transmission path for debugging instructions and data.

11. The debugging system of the aircraft engine monitoring device according to claim 1, characterized in that: The debugging signal integration and transmission device also includes a universal serial bus module; the debugging signal generation and transmission module includes a serial port communication module and an aviation 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 port communication module and the aviation Ethernet communication module to serve as a second transmission path for debugging instructions and data.

12. The debugging system of 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 demarcation module, a debugging data storage and management module and a debugging process control module.

13. The debugging system of 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; a first connection end of the power supply module is connected to a power input signal, and a second connection end of the power supply module is connected to the debugging signal integration and transmission device and a multi-interface adapter connector module.

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