CN112943450A - Engine monitoring device - Google Patents
Engine monitoring device Download PDFInfo
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- CN112943450A CN112943450A CN201911257672.XA CN201911257672A CN112943450A CN 112943450 A CN112943450 A CN 112943450A CN 201911257672 A CN201911257672 A CN 201911257672A CN 112943450 A CN112943450 A CN 112943450A
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- vibration
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B77/00—Component parts, details or accessories, not otherwise provided for
- F02B77/08—Safety, indicating or supervising devices
Abstract
The invention relates to an engine monitoring device for monitoring the real-time working state of an engine, which comprises: the vibration conditioning circuits are coupled to a single vibration sensor and used for respectively adopting different conditioning parameters to perform signal conditioning on vibration signals acquired by the vibration sensor so as to obtain a plurality of vibration conditioning signals; and the processing modules are correspondingly coupled to the vibration conditioning circuits, are used for processing and analyzing the vibration conditioning signals, and are correspondingly coupled to the communication modules so as to respectively perform data interaction with the airborne equipment and/or the ground equipment, wherein the processing modules are respectively designed in different development assurance levels. The vibration signal acquisition system can send the vibration signal with high precision and small range to the processing module needing high vibration precision, and send the vibration signal with large range and low precision to the processing module needing large range, thereby taking the vibration signal acquisition range and precision requirements of the whole aeroengine health management system into consideration.
Description
Technical Field
The invention relates to the field of monitoring technology of an aircraft engine and airborne electronic equipment of the engine, in particular to an engine monitoring device with multi-channel signal conditioning and multiple development guarantee levels.
Background
The main function of the aeroengine health management system is to monitor the real-time working state of the engine and provide data and suggestions for engine fault diagnosis and maintenance. The engine monitoring device is an important part of an aircraft engine health management system, can collect and store signals of engine sensors, and combines data sent by an engine electronic controller for processing and analysis, so as to calculate the real-time vibration level of an engine, monitor the running state of the engine, predict potential faults, generate fault diagnosis reports and maintenance suggestions, and transmit engine health information to an airplane, the engine electronic controller or other ground equipment.
The existing engine monitoring device mainly comprises a sensor signal acquisition module, a processor module, a data storage module and a communication module. The main functions of the engine monitoring device include: collecting sensor signals (mainly collecting signals of a vibration sensor and a rotating speed sensor); communicate with other on-board electronics (e.g., engine electronic controllers) to derive other desired signals therefrom (e.g., temperature, pressure, position, angle signals, etc.); calculating the vibration level of the engine by using the collected vibration and rotating speed signals and sending the vibration level to the cockpit; storing engine operating data; predicting a potential failure; generating a fault diagnosis report; and generating a maintenance recommendation.
The vibration signal acquisition function of the engine monitoring device on the current aircraft engine generally comprises a charge amplifier, a filter circuit, an amplifying circuit and an analog-digital conversion circuit. Furthermore, for each vibration sensor, only one channel is usually provided for vibration signal conditioning. Limited by the bandwidth and amplification factor of the filter circuit, and difficult to simultaneously consider wide range and high precision. If the channel range is large, it is difficult to measure a vibration signal having a small amplitude. If the channel range is small, the vibration signal with large amplitude cannot be measured.
Therefore, in order to overcome the above-mentioned defects in the prior art, there is a need in the art for an aircraft engine monitoring technology, which is used for sending a high-precision small-range vibration signal to a processing module requiring high vibration precision and sending a large-range low-precision vibration signal to a processing module requiring a large range, so as to meet the requirements of vibration signal acquisition range and precision of the whole aircraft engine health management system.
Disclosure of Invention
The following presents a simplified summary of one or more aspects in order to provide a basic understanding of such aspects. This summary is not an extensive overview of all contemplated aspects, and is intended to neither identify key or critical elements of all aspects nor delineate the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form as a prelude to the more detailed description that is presented later.
In order to overcome the defects in the prior art, the invention provides the engine monitoring device with multi-channel signal conditioning and multi-development guarantee levels, which is used for sending the vibration signals with high precision and small range to the processing module needing high vibration precision and sending the vibration signals with large range and low precision to the processing module needing large range, thereby considering the requirements of vibration signal acquisition range and precision of the whole aeroengine health management system.
The engine monitoring device provided by the invention is used for monitoring the real-time working state of the engine. The engine monitoring device includes: the vibration conditioning circuits are coupled to a single vibration sensor and used for respectively adopting different conditioning parameters to perform signal conditioning on vibration signals acquired by the vibration sensor so as to obtain a plurality of vibration conditioning signals; and the processing modules are correspondingly coupled to the vibration conditioning circuits, are used for processing and analyzing the vibration conditioning signals, and are correspondingly coupled to the communication modules so as to respectively perform data interaction with the airborne equipment and/or the ground equipment, wherein the processing modules are respectively designed in different development assurance levels.
Preferably, in the above-described engine monitoring apparatus provided by the present invention, each processing module and the vibration conditioning circuit and the communication module coupled thereto may be designed with a consistent level of development assurance.
Preferably, in the engine monitoring apparatus provided by the present invention, each of the vibration conditioning circuits may include an amplifying circuit and a filtering circuit, and the amplifying circuits and the filtering circuits of the plurality of vibration conditioning circuits may perform amplification and filtering using different amplification parameters and filtering parameters, respectively.
Preferably, in the above-described engine monitoring apparatus provided by the present invention, the plurality of processing modules may include a first processing module and a second processing module, the plurality of vibration conditioning circuits may include a first vibration conditioning circuit and a second vibration conditioning circuit,
the amplification factor of the amplification circuit of the first vibration conditioning circuit may be smaller than the amplification factor of the amplification circuit of the second vibration conditioning circuit, and the filter bandwidth of the filter circuit of the first vibration conditioning circuit may be larger than the filter bandwidth of the filter circuit of the second vibration conditioning circuit.
Preferably, in the above-described engine monitoring apparatus provided by the present invention, a development assurance level of the first processing module and the first vibration conditioning circuit may be higher or lower than a development assurance level of the second processing module and the second vibration conditioning circuit.
Preferably, in the engine monitoring device provided by the present invention, two non-vibration conditioning circuits may be further included, and are respectively coupled to different signal sensors to condition the received sensing signals, and the two non-vibration conditioning circuits may include different development assurance levels, wherein a non-vibration conditioning circuit with a high development assurance level may be coupled to a processing module with a high development assurance level in the first processing module and the second processing module, and a non-vibration conditioning circuit with a low development assurance level may be coupled to a processing module with a low development assurance level in the first processing module and the second processing module.
Alternatively, in the above-described engine monitoring apparatus provided by the present invention, the plurality of vibration conditioning circuits may be coupled to the vibration sensor through a charge amplifier.
Alternatively, in the above-described engine monitoring apparatus provided by the present invention, the plurality of processing modules may be implemented by a plurality of discrete processors or by a single processor.
Optionally, in the engine monitoring device provided by the invention, each vibration conditioning circuit may further include an analog-to-digital conversion circuit and a buffer.
Optionally, in the engine monitoring device provided by the present invention, a storage module coupled to the plurality of processing modules may be further included for storing the analyzed and processed data.
Drawings
The above features and advantages of the present disclosure will be better understood upon reading the detailed description of embodiments of the disclosure in conjunction with the following drawings. In the drawings, components are not necessarily drawn to scale, and components having similar relative characteristics or features may have the same or similar reference numerals.
FIG. 1 illustrates a schematic diagram of a signal conditioning module of an engine monitoring device provided in accordance with an embodiment of the present invention.
Fig. 2 shows a schematic configuration diagram of an engine monitoring apparatus provided according to an embodiment of the present invention.
Reference numerals
10 an engine monitoring device;
110a, 110b communication module;
120a, 120b processor module;
130a, 130b vibration conditioning circuits;
140 a charge amplifier;
150 a storage module;
160 other conditioning circuits;
20 an airplane;
30 an electronic controller;
40 other on-board devices;
50 ground equipment;
60 a vibration sensor;
70 other sensors.
Detailed Description
The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will become apparent to those skilled in the art from the present disclosure. While the invention will be described in connection with the preferred embodiments, there is no intent to limit its features to those embodiments. On the contrary, the invention is described in connection with the embodiments for the purpose of covering alternatives or modifications that may be extended based on the claims of the present invention. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. The invention may be practiced without these particulars. Moreover, some of the specific details have been left out of the description in order to avoid obscuring or obscuring the focus of the present invention.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Additionally, the terms "upper," "lower," "left," "right," "top," "bottom," "horizontal," "vertical" and the like as used in the following description are to be understood as referring to the segment and the associated drawings in the illustrated orientation. The relative terms are used for convenience of description only and do not imply that the described apparatus should be constructed or operated in a particular orientation and therefore should not be construed as limiting the invention.
It will be understood that, although the terms first, second, third, etc. may be used herein to describe various elements, regions, layers and/or sections, these elements, regions, layers and/or sections should not be limited by these terms, but rather are used to distinguish one element, region, layer and/or section from another element, region, layer and/or section. Thus, a first component, region, layer or section discussed below could be termed a second component, region, layer or section without departing from some embodiments of the present invention.
As described above, the bandwidth and the amplification factor of the filter circuit of the engine monitoring device in the conventional aircraft engine are limited, and it is difficult to achieve both a wide range and high accuracy. If the channel range is large, it is difficult to measure a vibration signal having a small amplitude. If the channel range is small, the vibration signal with large amplitude cannot be measured.
In order to overcome the defects in the prior art, the invention provides the engine monitoring device with multi-channel signal conditioning and multi-development guarantee levels, which is used for sending the vibration signals with high precision and small range to the processing module needing high vibration precision and sending the vibration signals with large range and low precision to the processing module needing large range, thereby considering the requirements of vibration signal acquisition range and precision of the whole aeroengine health management system.
The engine monitoring device provided by the invention can be used for monitoring the real-time working state of the engine. The engine monitoring device may include a plurality of vibration conditioning circuits coupled to the same vibration sensor, and a plurality of processing modules correspondingly coupled to the plurality of vibration conditioning circuits. The plurality of vibration conditioning circuits can be used for performing signal conditioning on vibration signals collected by the coupled vibration sensor by adopting different conditioning parameters respectively so as to obtain a plurality of vibration conditioning signals. The processing modules can be designed according to different development assurance levels respectively, and are used for processing a plurality of vibration conditioning signals obtained through analysis and sending the analysis results to corresponding airborne equipment and/or ground equipment for data interaction.
Referring to fig. 1, fig. 1 illustrates a schematic diagram of a signal conditioning module of an engine monitoring device provided in accordance with an embodiment of the present invention.
In one embodiment of the invention, as shown in fig. 1, a plurality of vibration conditioning circuits 130a, 130b of the engine monitoring apparatus may be provided in one signal conditioning module 15. The sensor signals collected by the vibration sensor 60 and other sensors 70 of the engine monitoring device may be conditioned by the signal conditioning module 15 and sent to the respective processor modules 120a, 120b for processing and analysis.
In some embodiments, the vibration conditioning circuit 130a may include a buffer 131a, an analog-to-digital conversion circuit 132a, an amplification circuit 133a, and a filter circuit 134a, and is coupled to the corresponding processing module 120 a. The vibration conditioning circuit 130b may include a buffer 131b, an analog-to-digital conversion circuit 132b, an amplification circuit 133b, and a filter circuit 134b, and is coupled to the corresponding processing module 120 b. The processing module 120a and the processing module 120b may be implemented by a plurality of discrete processors, or may be implemented by a single processor.
The filter circuits 134a and 134b can be used for filtering out ripples, interference and noise in the sensor signals, so that the detection accuracy of the vibration condition of the engine is improved, and the vibration conditioning circuits 130a and 130b are protected. The amplification circuits 133a, 133b described above may be used to amplify the filtered sensor signals to an amplitude suitable for processing by the analog-to-digital conversion circuits 132a, 132b for signal conditioning of the acquired vibration parameters. The analog-to-digital conversion circuits 132a, 132b may be used to convert the obtained analog signals such as voltage, current, etc. into digital signals suitable for the processing modules 120a, 120b to process and analyze the vibration-conditioned signals by the processing modules 120a, 120 b. The buffers 131a, 131b may be used to temporarily store the received vibration-conditioned signals for reading and analysis by the processing modules 120a, 120b based on the development assurance levels of the various different types of vibration-conditioned signals.
The above-described development assurance levels are technical criteria well known to those skilled in the art and may be determined based on the corresponding risk of failure of the engine function. In some embodiments, the development assurance levels may be classified as A, B, C, D, E from high to low, based on five levels of failure hazard, catastrophic, hazardous, major, minor, and no safety impact. The higher the development assurance level, the more software and hardware design activities are required, the higher the development cost and the longer the development period.
In some embodiments, each vibration conditioning circuit 130a, 130b may be coupled to the vibration sensor 60 of the engine monitoring device via a charge amplifier 140 for acquiring the sensor signal collected by the vibration sensor 60 and converting it to a voltage signal indicative of the engine vibration condition. Specifically, when the charge signal collected by the vibration sensor 60 indicative of the engine vibration condition enters the signal conditioning module 15, the charge amplifier 140 may first convert the charge signal to a voltage signal. The voltage signal may then be split into two paths, one of which is conditioned by the vibration conditioning circuit 130a and the other of which is conditioned by the vibration conditioning circuit 130 b.
In some embodiments, the two vibration conditioning circuits 130a, 130b may employ different filtering parameters and amplification factors to obtain vibration signals of different frequencies, amplitudes, and precisions. Specifically, the filter circuit 134a of the vibration conditioning circuit 130a may employ broadband filtering, and the amplifier circuit 133a thereof may employ low-power amplification, so as to output a vibration conditioning signal with a full-band and a large range. Meanwhile, the filter circuit 134b of the vibration conditioning circuit 130b may employ narrow-band filtering, and the amplifier circuit 133b may employ high-power amplification, so as to output a vibration conditioning signal with a small range of partial frequency band.
That is, the amplification factor of the amplifying circuit 133a of the vibration conditioning circuit 130a may be less than the amplification factor of the amplifying circuit 133b of the vibration conditioning circuit 130b, and the filter bandwidth of the filter circuit 134a of the vibration conditioning circuit 130a may be greater than the filter bandwidth of the filter circuit 134b of the vibration conditioning circuit 130 b. The full-band wide-range vibration conditioning signal obtained by signal conditioning of the vibration conditioning circuit 130a may have a low accuracy, and the partial-band small-range vibration conditioning signal obtained by signal conditioning of the vibration conditioning circuit 130b may have a high accuracy.
Because the full-band wide-range vibration conditioning signal and the partial-band small-range vibration conditioning signal are obtained by conditioning the sensor signal acquired by the same vibration sensor, and the vibration conditions of the engine indicated by the two signals are consistent, the functions can be complemented. The full-band wide-range vibration conditioning signal with large range and low precision is sent to the processing module 120a needing the large range for processing and analysis, the partial-band small-range vibration conditioning signal with high precision and small range is sent to the processing module 120b needing the high vibration precision for processing and analysis, and the engine monitoring device can output a proper vibration conditioning signal in a targeted manner according to different application scenes or system function requirements so as to take account of vibration signal acquisition range and precision requirements of the whole aeroengine health management system.
In a preferred embodiment, the vibration conditioning circuit 130a may be developed at a higher warranty level than the vibration conditioning circuit 130 b. Accordingly, the development assurance level of the process module 120a may be higher than that of the process module 120 b. The processing module 120a and the vibration conditioning circuit 130a coupled thereto may be designed in accordance with a consistent level of development assurance. The processing module 120b and the vibration conditioning circuit 130b coupled thereto may be designed in accordance with a consistent level of development assurance.
By configuring a higher development assurance level for the vibration conditioning circuit 130a and the processing module 120a, real-time and accurate full-band and wide-range vibration data can be preferentially obtained in a targeted manner, so that the requirement of wide-range monitoring of the health management system of the aircraft engine is emphatically met. Accordingly, the real-time performance and accuracy of high-precision vibration data of a small range of a partial frequency band measured by the engine monitoring device are appropriately lowered, thereby reducing the design cost of the engine monitoring device and shortening the design cycle thereof.
It will be appreciated by those skilled in the art that the above-described scheme for configuring the vibration conditioning circuit 130a and the processing module 120a with a higher level of development assurance is only one example provided by the present invention, and is provided primarily for clearly illustrating the concepts of the present invention and to provide a specific scheme for facilitating implementation by the public and not for limiting the scope of the present invention.
Optionally, in another embodiment of the present invention, a higher development assurance level may also be configured for the vibration conditioning circuit 130b and the processing module 120b, so as to preferentially obtain real-time, accurate, high-precision vibration data with a small range in a partial frequency band, so as to meet the requirement of high-precision monitoring of the health management system of the aircraft engine. Accordingly, the real-time performance and accuracy of the full-band wide-range vibration data measured by the engine monitoring device are properly reduced, thereby reducing the design cost of the engine monitoring device and shortening the design cycle thereof.
As shown in FIG. 1, in one embodiment of the present invention, the signal conditioning module 15 of the engine monitoring device may further include a non-vibratory conditioning circuit 160. The non-vibrating conditioning circuit 160 may be coupled to other sensors 70 for conditioning other sensing signals received. The other sensors 70 include, but are not limited to, one or more of a rotational speed sensor, a temperature sensor, a pressure sensor, a position sensor, and an angle sensor.
In some embodiments, the non-vibration conditioning circuit 160 may specifically include two non-vibration conditioning circuits. The two non-vibrating conditioning circuits may include different levels of development assurance. A high development assurance level non-vibratory conditioning circuit may be coupled to a high development assurance level processing module 120a and a low development assurance level non-vibratory conditioning circuit may be coupled to a low development assurance level processing module 120 b.
In some embodiments, the engine speed sensor may be coupled to the high development warranty grade non-vibratory conditioning circuit to provide more support for activities in its software and hardware planning, development, and validation to accurately reflect the engine speed information in the cockpit in real time to maintain the flight status of the aircraft.
In some embodiments, temperature sensors, pressure sensors, position sensors and/or angle sensors are used only to provide recommendations for ground maintenance of the engine, and the low-warranty level non-vibratory conditioning circuits described above may be coupled, thereby reducing the design cost and cycle time of the engine monitoring device.
Referring further to fig. 2, fig. 2 is a schematic structural diagram of an engine monitoring apparatus according to an embodiment of the present invention.
As shown in fig. 2, in one embodiment of the invention, the processor module 120a of the engine monitoring apparatus 10 may be correspondingly coupled to the communication module 110a and perform data interaction with the aircraft 20, the electronic controller 30, the other on-board devices 40, the ground devices 50, and the communication module 110b through the communication module 110 a. Processor module 120b of engine monitoring device 10 may be correspondingly coupled to communication module 110b and perform data interaction with aircraft 20, electronic controller 30, other on-board equipment 40, ground equipment 50, and communication module 110a via communication module 110 b.
In some embodiments, the processing module 120a, and the vibration conditioning circuit 130a and the communication module 110a coupled thereto, may be designed in accordance with a consistent high level of development assurance to provide more support for the engine vibration signals collected by the vibration sensor and the engine speed signals collected by the speed sensor during software and hardware planning, development and verification to accurately reflect the vibration information and speed information of the engine in the cockpit in real time to maintain the flight status of the aircraft.
In some embodiments, the processing module 120b and the vibration conditioning circuit 130b and the communication module 110b coupled thereto may be designed with a consistent low level of development assurance, thereby reducing the design cost and the design cycle of the engine monitoring device while ensuring that the low level of development assurance functions do not affect the high level of development assurance functions in the processor software functions.
As shown in FIG. 2, in one embodiment of the present invention, the engine monitoring device 10 may further include a memory module 150. The storage module 150 may be coupled to the processing modules 120a, 120b for storing the analyzed data. In some embodiments, processor module 120a may also store the required data to memory module 150 after completing data interaction with aircraft 20, electronic controller 30, other on-board devices 40, ground devices 50, and communication module 110b via communication module 110 a. In some embodiments, processor module 120b may also store the required data to memory module 150 after completing data interaction with aircraft 20, electronic controller 30, other on-board devices 40, ground devices 50, and communication module 110a via communication module 110 b.
It will be appreciated by those skilled in the art that the signal conditioning module comprising the two vibration conditioning circuits 130a, 130b described above is only one embodiment provided by the present invention, and is mainly used to clearly illustrate the concept of the present invention and provide a specific solution for the implementation by the public without limiting the scope of protection of the present invention.
In a preferred embodiment, the engine monitoring device may further comprise three or more vibration conditioning circuits. The multiple vibration conditioning circuits can be coupled to the same vibration sensor, are designed according to different development assurance levels, and are used for performing signal conditioning on vibration signals acquired by the vibration sensor by adopting different conditioning parameters respectively to obtain multiple vibration conditioning signals. Accordingly, the engine monitoring apparatus may further include three or more processing modules. The processing modules can be correspondingly coupled to the vibration conditioning circuits and designed with the development guarantee level consistent with the vibration conditioning circuits coupled with the processing modules for processing and analyzing the obtained vibration conditioning signals. In some embodiments, the plurality of processing modules may be correspondingly coupled to the plurality of communication modules for performing data interaction with the onboard equipment and/or the ground equipment, respectively, so as to provide the vibration conditioning signals obtained by conditioning the most appropriate amplification parameters and filtering parameters for the onboard equipment and/or the ground equipment corresponding to each communication module, respectively. In some embodiments, the development assurance levels of the plurality of vibration conditioning circuits and the plurality of processing modules may be designed based on the development assurance levels of the corresponding communication modules.
The previous description of the disclosure is provided to enable any person skilled in the art to make or use the disclosure. Various modifications to the disclosure will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other variations without departing from the spirit or scope of the disclosure. Thus, the disclosure is not intended to be limited to the examples and designs described herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. An engine monitoring device for monitoring a real-time operating condition of an engine, the engine monitoring device comprising:
the vibration conditioning circuits are coupled to a single vibration sensor and used for respectively adopting different conditioning parameters to perform signal conditioning on vibration signals acquired by the vibration sensor so as to obtain a plurality of vibration conditioning signals; and
and the processing modules are correspondingly coupled to the vibration conditioning circuits, are used for processing and analyzing the vibration conditioning signals, and are correspondingly coupled to the communication modules so as to respectively perform data interaction with the airborne equipment and/or the ground equipment, wherein the processing modules are respectively designed in different development assurance levels.
2. The engine monitoring device of claim 1, wherein each processing module and the vibration conditioning circuit and communication module coupled thereto are designed with a consistent level of development assurance.
3. The engine monitoring device of claim 2, wherein each vibration conditioning circuit includes an amplifying circuit and a filtering circuit, the amplifying circuits and filtering circuits of the plurality of vibration conditioning circuits performing amplification and filtering using different amplification parameters and filtering parameters, respectively.
4. The engine monitoring device of claim 3, wherein the plurality of processing modules includes a first processing module and a second processing module, the plurality of vibration conditioning circuits includes a first vibration conditioning circuit and a second vibration conditioning circuit,
the amplification factor of the amplification circuit of the first vibration conditioning circuit is smaller than that of the amplification circuit of the second vibration conditioning circuit, and the filter bandwidth of the filter circuit of the first vibration conditioning circuit is larger than that of the filter circuit of the second vibration conditioning circuit.
5. The engine monitoring device of claim 4, wherein a development assurance level of the first processing module and the first vibration conditioning circuit is higher or lower than a development assurance level of the second processing module and the second vibration conditioning circuit.
6. The engine monitoring device of claim 5, further comprising two non-vibratory conditioning circuits coupled to different signal sensors respectively to condition the received sensed signals, the two non-vibratory conditioning circuits including different levels of development assurance, wherein a high level of development assurance non-vibratory conditioning circuit is coupled to a high level of development assurance processing module of the first and second processing modules and a low level of development assurance non-vibratory conditioning circuit is coupled to a low level of development assurance processing module of the first and second processing modules.
7. The engine monitoring device of claim 1, wherein the plurality of vibration conditioning circuits are coupled to the vibration sensor through a charge amplifier.
8. The engine monitoring apparatus of claim 1, wherein the plurality of processing modules are implemented by a plurality of discrete processors or by a single processor.
9. An engine monitoring device as set forth in claim 3 wherein each vibration conditioning circuit further comprises an analog to digital conversion circuit and a buffer.
10. The engine monitoring device of claim 1, further comprising a storage module coupled to the plurality of processing modules for storing the analyzed processed data.
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| CN201911257672.XA CN112943450A (en) | 2019-12-10 | 2019-12-10 | Engine monitoring device |
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Application publication date: 20210611 |