CN213749073U

CN213749073U - Aeroengine detector

Info

Publication number: CN213749073U
Application number: CN202023107080.0U
Authority: CN
Inventors: 陈庆贵; 孙护国; 谢镇波; 蔡娜; 曾义伦; 李明; 谢静; 马中原
Original assignee: Qingdao Campus of Naval Aviation University of PLA
Current assignee: Qingdao Campus of Naval Aviation University of PLA
Priority date: 2020-12-22
Filing date: 2020-12-22
Publication date: 2021-07-20
Anticipated expiration: 2030-12-22

Abstract

The utility model relates to an aeroengine check out test set field specifically is an aeroengine detector, including for military use reinforcement portable machine, PCI integrated circuit board, external communication bus, for military use reinforcement portable machine has PCI integrated circuit board slot, the PCI integrated circuit board is installed in for military use reinforcement portable machine's PCI integrated circuit board slot, the PCI integrated circuit board passes through external communication bus links to each other with aeroengine's electronic regulator. The utility model is used for the state data, the fault data of record, storage and playback aeroengine can realize the detection of aeroengine state, the playback of engine state data and fault data effectively, maintain and provide support with the troubleshooting for aeroengine's use, and can normally work under rugged environment, portable.

Description

Aeroengine detector

Technical Field

The utility model relates to an aeroengine check out test set field, in particular to aeroengine detector that can carry out aeroengine state detection and auxiliary fault diagnosis.

Background

The aircraft engine adopts the electronic regulator to control the work of the engine, because no instrument is used for displaying the working parameters of the engine, such as rotating speed and exhaust temperature, and the flight parameter recorder does not record the relevant parameters of the engine, and the data in the electronic regulator can not be obtained after the engine is stopped, the working state of the engine can only be sensed by a limited signal lamp on a control panel when the aircraft engine works, the exact state information and fault information of the aircraft engine can not be mastered, and the difficulty in use, maintenance and troubleshooting of the aircraft engine is increased.

The conventional aircraft engine detector only displays the engine state detection result in real time and cannot record and store engine state data, fault data and the like, so that the aircraft engine cannot check historical data such as rotating speed, exhaust temperature and the like under the fault conditions such as overtemperature, overtravel and the like, great trouble is caused to mastering the working state and exact fault information of the aircraft engine, and the condition monitoring and fault elimination of the aircraft engine are extremely unfavorable.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a detectable aeroengine operating condition, can record, save, playback and the aeroengine detector who reports an emergency and asks for help or increased vigilance to data such as aeroengine state data, trouble data to solve the unable problem or one of the problem of recording, saving, playback aeroengine state data, trouble data of current aeroengine detector.

In order to achieve the above object, the utility model adopts the following technical scheme:

the utility model provides an aeroengine detector, includes for military use reinforcement portable machine, PCI integrated circuit board, external communication bus, for military use reinforcement portable machine has PCI integrated circuit board slot, the PCI integrated circuit board is installed in for military use reinforcement portable machine's PCI integrated circuit board slot, the PCI integrated circuit board passes through external communication bus links to each other with aeroengine's electronic regulator.

Furthermore, the military reinforced portable computer further comprises a computer body, a keyboard, a display screen, a PCI board card interface, a power supply interface, a USB interface and a network cable interface.

Further, the chip of the PCI board card is an ARINC429 chip, and includes 4 receiving channels and 2 transmitting channels.

Furthermore, the external communication bus adopts an ARINC429 twisted pair, one end of the external communication bus is provided with an EP-H6272-1T2R connector, and the other end of the external communication bus is provided with a ZH23-19/22P-6-BC-1610 and 0093 connector.

The utility model discloses following beneficial effect has:

the utility model discloses following beneficial effect has:

the utility model relates to an aeroengine detector realizes the data transmission of aeroengine electronic governor to between the aeroengine detector PCI integrated circuit board through ARINC429 bus. The PCI board card is arranged in a PCI board card slot of the military reinforced portable machine, and the communication between the PCI board card and the PCI board card slot is completed by a PCI bus. The PCI board card is connected with an electronic regulator of the aircraft engine through the external communication bus, and the received data is decoded into data with practical significance according to a communication protocol through detection software and displayed on a good interface, so that the purposes of reproducing the working state of the engine, carrying out state detection and fault statistics on the engine are achieved, the recording, storage and playback of state data, fault data and the like of the aircraft engine can be realized, the state detection, use maintenance and troubleshooting of the aircraft engine are facilitated, the electronic regulator can normally work in a severe environment, and the electronic regulator is convenient to carry.

Drawings

Fig. 1 is a schematic structural diagram of the present invention.

Detailed Description

The embodiments of the invention will be described in detail below with reference to the drawings, but the invention can be implemented in many different ways as defined and covered by the claims.

Referring to fig. 1, the preferred embodiment of the utility model provides an aeroengine detector, including for military use reinforcement portable machine 1, PCI integrated circuit board 2, external communication bus 3, for military use reinforcement portable machine adopts salt fog prevention, anti vibration, shock resistance design, including 1 fuselage, 1 keyboard, 1 display screen, 1 PCI integrated circuit board slot 5, 1 PCI integrated circuit board interface, 1 power source, 2 USB interfaces and 2 net twine interfaces. The built-in lithium battery is 5200mAH/22.2V, the continuous working time exceeds 2h, the memory is 4GB DDR3, the processor is intel Corei7, the dominant frequency is 2.1GHz, and the portable lithium battery can work in a severe environment and is convenient to carry about.

The PCI board card 2 is an ARINC429 board card, is provided with 4 receiving channels and 2 sending channels, can perform odd/even/no check through software, has a baud rate of 100K, and has a timestamp precision of 1us for a control card.

The external communication bus 3 adopts an ARINC429 twisted pair, one end of the external communication bus is provided with an EP-H6272-1T2R connector for connecting an electronic regulator 4 of the aircraft engine, and the other end of the external communication bus is provided with a ZH23-19/22P-6-BC-1610 and 0093 connector for connecting a PCI board card interface.

The electronic regulator 4 transmits data containing the technical state and the fault information of the aero-engine to the PCI board card 2 through an ARINC429 bus, the data are sent to a cache of the PCI board card 2 under the unified logic control of the FPGA, and the data in the cache enter the military reinforcement portable machine 1 through the PCI bus under the control of system software.

In this embodiment, preferably, Windows is used as the operating system of the detection software, and LabWindows/CVI is used as the development platform. The system software comprises a PCI board card driving program and detection software. And the PCI board card driving program is used for driving the PCI board card. The detection software adopts a modular design and comprises six modules of system self-inspection, data receiving, data analysis, data mining, use help and quitting.

The system self-checking comprises a board card self-checking module and a line self-checking module. The board self-inspection mainly refers to the function self-inspection of the ARINC429 board, and is completed by driving the board through a self-inspection command sent by a main control computer by using the self-inspection function of the board; the line self-test checks whether the electronic regulator and ARINC429 bus connection lines are intact by calling the ARINC429 test word sent by the electronic regulator.

The data receiving comprises two modules of starting data receiving and stopping data receiving, the ARINC429 data receiving and storing are completed, and the modules adopt a multi-thread mode and a TDMS fast storage mode.

The data analysis comprises three modules of data selection and analysis, fault statistics and report generation and storage. The data analysis of the parameter words and the discrete words is realized, all parameter values and corresponding time corresponding to the words in the once received data are formed and displayed by a graph curve, and the requirements of local amplification observation and parameter value interaction are met. The data selection and analysis module realizes the final result statistics of the parameter words and the discrete words of the received data at one time. And the fault counting module automatically identifies faults and judges the types of the faults according to the final counting results of the parameter words and the discrete words, and counts the fault words. And the report generation and storage module dynamically generates an EXECL table for storage by taking the current airplane number, the auxiliary engine number and the data downloading time as file names.

The data mining comprises two modules of parameter word data mining and discrete word data mining. And the parameter word data mining carries out data mining on the selected parameter words according to the selected parameter words, and the discrete word data mining carries out data mining on the selected discrete words according to the selected discrete words.

The use help comprises a system use instruction module which is used for displaying the use instruction of the engine detector and assisting personnel to correctly use the aircraft engine detector.

And exiting the software system for exiting the aircraft engine detector.

The utility model relates to an aeroengine detector has not only realized aeroengine's state detection, carries out the unusual warning of aeroengine state, can also realize aeroengine state data, fault data's record, storage and playback, can look over aeroengine's state, trouble historical data, for aeroengine's state detection, use to maintain and arrange the trouble and provide support.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides an aeroengine detector, its characterized in that, includes for military use portable (1) of consolidating, PCI integrated circuit board (2), external communication bus (3), for military use portable (1) of consolidating has PCI integrated circuit board slot (5), PCI integrated circuit board (2) with for military use portable (1) of consolidating PCI integrated circuit board slot grafting, PCI integrated circuit board (2) are passed through external communication bus (3) link to each other with aeroengine's electronic regulator (4).

2. The aircraft engine detector according to claim 1, wherein the military ruggedized portable machine (1) further comprises a body, a keyboard, a display screen, a PCI board interface, a power supply interface, a USB interface, and a network cable interface.

3. The aircraft engine detector according to claim 1, characterized in that the chip of the PCI card (2) is an ARINC429 chip, comprising 4 receive channels and 2 transmit channels, and the PCI card can be inserted into the PCI slot of the military ruggedized portable machine.

4. The aircraft engine detector as claimed in claim 1, wherein the external communication bus (3) is an ARINC429 twisted pair, one end of which is provided with an EP-H6272-1T2R connector for connecting an electronic regulator, and the other end of which is provided with a ZH23-19/22P-6-BC-1610 and 0093 connector for connecting with the PCI card interface.