CN204286792U - A kind of two remaining Aerial weapon equipment state monitoring apparatus - Google Patents
A kind of two remaining Aerial weapon equipment state monitoring apparatus Download PDFInfo
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Abstract
A kind of two remaining Aerial weapon equipment state monitoring apparatus, comprise first passage, second channel, first passage, data are exchanged by parallel interface between second channel, interchannel mutual inspection and redundancy management, first passage, second channel comprises Signal-regulated kinase respectively, digital sampling and processing, display module and power module, Signal-regulated kinase connects first passage simultaneously, digital sampling and processing in second channel, digital sampling and processing is connected with display module, power module and Signal-regulated kinase, digital sampling and processing, display module connects and provides power supply.The utility model can solve the problems such as Aerial weapon equipment parameter acquisition, analysis, storage, alarm, synthesis display, data sharing, monitors aviation whirlpool axle machine engine behavior effectively constantly.
Description
Technical field
The utility model belongs to airborne technical field of electronic products, realize coupling Aerial weapon equipment status monitoring, be specifically related to the technology such as parameter acquisition, small signal process, data analysis, trend analysis, bus communication, redundancy management, virtual instrument synthesis display.
Background technology
Early stage, Aerial weapon equipment was mainly from what abroad introduce, and because technical protection bus data cannot obtain, engine parameter collection display all adopts analog combination instrument, and this has had a strong impact on the development of Chinese operational aircraft.When showing with analog combination instrument, man-machine interaction is poor, data without sharing, precision is low, without remaining, poor reliability, volume greatly, its volume occupies a big chunk of front deck, and layout is in disorder.Along with improving constantly of equipment Requirement, traditional analog combination instrument has been difficult to meet these requirements, the synthesization of engine state monitor and whole avionics system, digitizing and intellectuality must be realized, the overall performance of aircraft could be improved, propose Aerial weapon equipment and carry out digitized status monitoring.
Summary of the invention
In order to solve the problem such as state parameter collection, computational analysis, storage, alarm, synthesis display, data sharing of coupling Aerial weapon equipment, goal of the invention of the present utility model is to provide a kind of two remaining Aerial weapon equipment state monitoring apparatus, for improving functional reliability, the man-machine interaction of Aerial weapon equipment, powerful guarantee is played to the application of Aerial weapon equipment, meets modern advanced avionics system requirement.
Goal of the invention of the present utility model is achieved through the following technical solutions:
A kind of two remaining Aerial weapon equipment state monitoring apparatus, comprise first passage, second channel, first passage, data are exchanged by parallel interface between second channel, interchannel mutual inspection and redundancy management, first passage, second channel comprises Signal-regulated kinase respectively, digital sampling and processing, display module and power module, Signal-regulated kinase connects first passage simultaneously, digital sampling and processing in second channel, digital sampling and processing is connected with display module, power module and Signal-regulated kinase, digital sampling and processing, display module connects and provides power supply, first passage, the Signal-regulated kinase of second channel receives Left Hand Engine respectively, right engine upper sensor signal, discrete magnitude signal and frequency signal, convert analog quantity to single-ended or differential signal, discrete magnitude signal and frequency signal are carried out isolating and nursing one's health and the signal after conditioning is sent to first passage, the middle digital sampling and processing of second channel, data acquisition module simultaneously carries out communication with EECU1, EECU2 and air data computer by ARINC429, receives engine, atmospheric temperature information, and the signal after the conditioning of binding signal conditioning module carries out gathering, computational analysis, the information of the collection of digital sampling and processing, computational analysis and reception shows by display module.
According to above-mentioned feature, described digital sampling and processing is PC104 embedded computer.
According to above-mentioned feature, described digital sampling and processing comprises data acquisition module, processor module and ARINC429 interface module, data acquisition module and first passage, the Signal-regulated kinase of second channel connects, RINC429 interface module and EECU1, EECU2 is connected with air data computer, processor module and data acquisition module, ARINC429 interface module is connected with display module, processor module is to the simulating signal being converted into digital signal through data acquisition module, the discrete engine received with frequency signal and RINC429 interface module, atmospheric temperature data carry out computational analysis.
Advantage of the present utility model: the above shortcoming that analog combination instrument the first, can be overcome, and have that display quality is high, display mode flexibly, be easy to interpretation, the advantage such as information fusion is shared, integrated level is high, flexible configuration, easy for installation, highly versatile, power consumption are little, lightweight.It greatly reduces the working load of pilot in flight course, for pilot shows the state of engine, pilot is enable to recognize the working condition of engine constantly, as parameters such as motor oil pressure, fuel pressure, oil temperature, fuel oil temperature, power supplys, for multifunction display provides backup display information, the information of recording engine operating history and other necessity.For EECU provides necessary parameter, and output engine alarm signal.Improve Operational Effectiveness Rat; Engine warning information can be sent when engine breakdown to ensure flight safety, improve the maintenance efficiency on ground crew ground, improve the attendance rate of aircraft.
The second, this system can monitor the working status parameter of Aerial weapon equipment in the process run effectively, and the variation tendency of these parameters, with their serviceability and malfunction and development trend thereof, the control system for engine provides reliable foundation.The duty of Real-Time Monitoring engine, continuous record and storage working status parameter, effectively can improve the safety and reliability of engine, status monitoring is one of important measures of engine condition based maintenance, 1, it can determine rapidly and accurately trouble location and fault severity level, be conducive to guaranteeing aircraft safety and reducing the human and material resources dropping into maintenance, shorten the off-air time of engine, improve the utilization factor of aircraft; 2, it is the necessary means and the prerequisite that realize advanced maintenance database (turning to the maintenance database of " centered by reliability " from the maintenance database of empirical " to put prevention first ") and maintenance mode (turning to hard time maintenance, condition maintenarnce and status monitoring three kinds of modes from simple hard time maintenance mode).3, it can improve the reliability of engine, improves the security that aircraft runs; Shorten the maintenance cycle of engine, simplify maintenance step, reduce maintenance cost.4th, it can provide the important system information such as engine, lubricating oil, fuel oil, hydraulic pressure, power supply accurately for pilot, enables pilot grasp engine current operating conditions, improves man-machine efficacy, improve task completion rate.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Embodiment
Below in conjunction with Fig. 1, the utility model is described in further detail.
As shown in Figure 1, a kind of two remaining Aerial weapon equipment state monitoring apparatus of the utility model, be cross-linked by cable on machine and engine, kinematic train, machine upper sensor and electronic control equipment for engine (EECU), by data bus and signal acquisition circuit Real-time Collection and monitoring engine current operating conditions and fuel system, hydraulic system, oil system, power-supply system information, for pilot provides engine parameters instruction accurately.And alarm instruction and failure logging are provided to the failure message of said system, retain necessary download interface, for ground maintenance.
The utility model adopts binary channels pattern, include first passage and second channel, each passage configures independently Signal-regulated kinase, digital sampling and processing, display module and power module, and two independently data acquisition process and display module are respectively two displays be placed in a cabinet and provide synthesis display information.Each passage can independent acquisition and process Left Hand Engine and other parameter of right engine, EECU1, EECU2, atmosphere data and helicopter and information.
Power module is display module, digital sampling and processing, Signal-regulated kinase etc. provide required supply voltage.
Signal-regulated kinase in each passage receives engine, right engine upper sensor signal, discrete magnitude signal and frequency signal respectively, analog quantity converts single-ended and simulating signal that is difference to, discrete and frequency signal are carried out isolating and nursing one's health, the signal after conditioning gives the digital sampling and processing of first passage and second channel.
The each passage of digital sampling and processing respectively selects a PC104 embedded computer, comprises processor module, data acquisition module and ARINC429 interface module.Data acquisition module is by the simulating signal after the conditioning of two Signal-regulated kinase, discrete and frequency signal collection be converted into digital signal and hand over processor module to carry out calculation process, ARINC429 interface module is by carrying out communication with EECU1, EECU2 and air data computer, and the information such as engine, atmospheric temperature that receives hands over processor module to carry out calculation process.
Display module is according to display page requirement, after relevant data process under processor module controls, directly deliver on integrated display by RS422 with forms such as virtual instrument and figure, page data, bell characters, display engine parameter and running state information, switch display page by the button in light guide plate.
Exchange data by parallel interface between two channel processors, carry out interchannel mutual inspection and redundancy management.
During normal work, upper channel mainly processes homepage (the sending out ginseng information page) information required for display; Lower channel mainly processes the information such as lubricating oil, fuel oil, hydraulic pressure, power supply required for the display of sub-page face.
Wherein during a channel failure, system enters degradation mode of operation, at another passage display composite information page, to ensure that flight is normally carried out.
When helicopter landing, display flight report page.
The above is only preferred implementation of the present utility model; should be understood that; for those skilled in the art; under the prerequisite not departing from the utility model know-why; can also make some improvement and modification, these improve and modification also should be considered as protection domain of the present utility model.
Claims (3)
1. a two remaining Aerial weapon equipment state monitoring apparatus, comprises first passage, second channel, is characterized in that: first passage, data are exchanged by parallel interface between second channel, interchannel mutual inspection and redundancy management, first passage, second channel comprises Signal-regulated kinase respectively, digital sampling and processing, display module and power module, Signal-regulated kinase connects first passage simultaneously, digital sampling and processing in second channel, digital sampling and processing is connected with display module, power module and Signal-regulated kinase, digital sampling and processing, display module connects and provides power supply, first passage, the Signal-regulated kinase of second channel receives Left Hand Engine respectively, right engine upper sensor signal, discrete magnitude signal and frequency signal, convert analog quantity to single-ended or differential signal, discrete magnitude signal and frequency signal carried out isolating and nursing one's health and the signal after conditioning is sent to first passage, the middle digital sampling and processing of second channel, data acquisition module simultaneously carries out communication with EECU1, EECU2 and air data computer by ARINC429, receives engine, atmospheric temperature information, and the signal after the conditioning of binding signal conditioning module carries out gathering, computational analysis, the information of the collection of digital sampling and processing, computational analysis and reception shows by display module.
2. according to claim 1 pair of remaining Aerial weapon equipment state monitoring apparatus, is characterized in that described digital sampling and processing is PC104 embedded computer.
3. according to claim 1 pair of remaining Aerial weapon equipment state monitoring apparatus, it is characterized in that described digital sampling and processing comprises data acquisition module, processor module and ARINC429 interface module, data acquisition module and first passage, the Signal-regulated kinase of second channel connects, RINC429 interface module and EECU1, EECU2 is connected with air data computer, processor module and data acquisition module, ARINC429 interface module is connected with display module, processor module is to the simulating signal being converted into digital signal through data acquisition module, the discrete engine received with frequency signal and RINC429 interface module, atmospheric temperature data carry out computational analysis.
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104793089A (en) * | 2015-05-05 | 2015-07-22 | 江西洪都航空工业集团有限责任公司 | Onboard height indicator and preselector testing device based on redundancy management |
| CN106081046A (en) * | 2016-07-13 | 2016-11-09 | 中国电子科技集团公司第三十八研究所 | A kind of double remaining aerostatics measure and control device |
| CN106200527A (en) * | 2016-08-12 | 2016-12-07 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of airborne air data system data capture method based on double remainings |
| CN108426717A (en) * | 2018-05-02 | 2018-08-21 | 中国航发湖南动力机械研究所 | Engine test abnormal parameters situation automatic judging method and storage medium |
| CN110879549A (en) * | 2019-11-28 | 2020-03-13 | 四川泛华航空仪表电器有限公司 | Redundancy measurement framework based on cross-comparison method and redundancy management method |
| CN111963322A (en) * | 2020-08-26 | 2020-11-20 | 四川海特亚美航空技术有限公司 | Turboshaft engine binary channels electronic control system data acquisition system |
| CN112098106A (en) * | 2020-08-14 | 2020-12-18 | 陕西千山航空电子有限责任公司 | Turboshaft engine state monitoring device |
| CN112504687A (en) * | 2020-10-30 | 2021-03-16 | 哈尔滨飞机工业集团有限责任公司 | Helicopter binary channels engine parameter acquisition display system |
| CN112748751A (en) * | 2020-12-22 | 2021-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Digital airplane environment control system and method |
| CN113934153A (en) * | 2020-06-29 | 2022-01-14 | 中国航发商用航空发动机有限责任公司 | Multi-channel simulation method and system for aircraft engine control system |
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2014
- 2014-12-01 CN CN201420743484.4U patent/CN204286792U/en active Active
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104793089A (en) * | 2015-05-05 | 2015-07-22 | 江西洪都航空工业集团有限责任公司 | Onboard height indicator and preselector testing device based on redundancy management |
| CN106081046A (en) * | 2016-07-13 | 2016-11-09 | 中国电子科技集团公司第三十八研究所 | A kind of double remaining aerostatics measure and control device |
| CN106081046B (en) * | 2016-07-13 | 2018-02-16 | 中国电子科技集团公司第三十八研究所 | A kind of double remaining aerostatics measure and control devices |
| CN106200527A (en) * | 2016-08-12 | 2016-12-07 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of airborne air data system data capture method based on double remainings |
| CN108426717A (en) * | 2018-05-02 | 2018-08-21 | 中国航发湖南动力机械研究所 | Engine test abnormal parameters situation automatic judging method and storage medium |
| CN108426717B (en) * | 2018-05-02 | 2020-03-24 | 中国航发湖南动力机械研究所 | Method for automatically judging abnormal conditions of engine test parameters and storage medium |
| CN110879549A (en) * | 2019-11-28 | 2020-03-13 | 四川泛华航空仪表电器有限公司 | Redundancy measurement framework based on cross-comparison method and redundancy management method |
| CN113934153A (en) * | 2020-06-29 | 2022-01-14 | 中国航发商用航空发动机有限责任公司 | Multi-channel simulation method and system for aircraft engine control system |
| CN112098106A (en) * | 2020-08-14 | 2020-12-18 | 陕西千山航空电子有限责任公司 | Turboshaft engine state monitoring device |
| CN111963322A (en) * | 2020-08-26 | 2020-11-20 | 四川海特亚美航空技术有限公司 | Turboshaft engine binary channels electronic control system data acquisition system |
| CN112504687A (en) * | 2020-10-30 | 2021-03-16 | 哈尔滨飞机工业集团有限责任公司 | Helicopter binary channels engine parameter acquisition display system |
| CN112748751A (en) * | 2020-12-22 | 2021-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Digital airplane environment control system and method |
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