CN107679329B - Method and device for integrating various upper computers in aircraft engine control system - Google Patents
Method and device for integrating various upper computers in aircraft engine control system Download PDFInfo
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- CN107679329B CN107679329B CN201710936592.1A CN201710936592A CN107679329B CN 107679329 B CN107679329 B CN 107679329B CN 201710936592 A CN201710936592 A CN 201710936592A CN 107679329 B CN107679329 B CN 107679329B
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Abstract
The invention discloses an integration method of various upper computers in an aircraft engine control system, which comprises the following steps: acquiring configuration information of each upper computer, and forming configuration files of the configuration information of the plurality of upper computers; judging whether the configuration file is empty or not; when the configuration file is not empty, acquiring an installation path of each upper computer in the configuration file; judging whether the installation path of each upper computer in the configuration file is successfully acquired; when the installation path of each upper computer in the configuration file is successfully acquired, dynamically generating a function button of the upper computer according to the installation path of each upper computer; and establishing a left click function and a right click function of the function button aiming at the function button of each upper computer. The invention also discloses an integrated device of various upper computers in the control system of the aero-engine. The integration method of the various upper computers in the aircraft engine control system solves the problem that the various upper computers in the aircraft engine control system are disordered in use.
Description
Technical Field
The invention relates to the technical field of an aero-engine control system, in particular to an integration method of various upper computers in the aero-engine control system and an integration device of various upper computers in the aero-engine control system.
Background
The normal operation of the aircraft engine control system needs a large amount of support of auxiliary operation software, different upper computer tools are developed according to different use conditions and different functions so as to meet the requirements of operations of data monitoring, parameter modification, sensor calibration, software burning, historical data reading and the like of the aircraft engine control system, and therefore the installation and updating management of a plurality of pieces of support software are very necessary.
The personnel that current aeroengine control system ground maintenance equipment used involved are more, and when the staff of difference can't confirm the software of which version of use, will install the software that oneself thought is suitable again, will appear having the host computer software of a plurality of the same functions on the equipment desktop, but the version is different, can become more and more moreover, and the host computer is more and more in disorder, leads to the increase of manpower maintenance cost indirectly.
Therefore, how to avoid the risk caused by the use confusion of a plurality of upper computers becomes a technical problem to be solved urgently by the technical personnel in the field.
Disclosure of Invention
The invention aims to at least solve one of the technical problems in the prior art, and provides an integration method of various upper computers in an aero-engine control system and an integration device of various upper computers in the aero-engine control system so as to solve the problems in the prior art.
As a first aspect of the present invention, there is provided an integration method for multiple types of upper computers in an aircraft engine control system, where the aircraft engine control system includes a control device and multiple types of upper computers connected to the control device, each type of upper computer is configured to send a control instruction to the control device, the control instructions sent by the multiple types of upper computers are different from each other, and each type of upper computer includes configuration information, the integration method includes:
acquiring configuration information of each upper computer, and forming configuration files of the configuration information of the plurality of upper computers, wherein the configuration information of each upper computer stores an installation path of the upper computer;
judging whether the configuration file is empty or not;
when the configuration file is not empty, acquiring an installation path of each upper computer in the configuration file;
judging whether the installation path of each upper computer in the configuration file is successfully acquired;
when the installation path of each upper computer in the configuration file is successfully acquired, dynamically generating a function button of each upper computer according to the installation path of each upper computer;
and establishing a left click function and a right click function of the function button aiming at the function button of each upper computer.
Preferably, the integration method comprises:
and when the configuration file is empty, sending out alarm information of 'failure in reading the configuration file'.
Preferably, the integration method comprises:
and when the installation path of each upper computer in the configuration file is not acquired successfully, sending out alarm information of 'configuration format error'.
Preferably, the obtaining the configuration information of each upper computer and forming the configuration information of the plurality of upper computers into the configuration file includes: and manually forming the configuration information of the plurality of upper computers into configuration files or automatically forming the configuration information of the plurality of upper computers into configuration files.
Preferably, the manually forming the configuration information of the plurality of upper computers into the configuration file includes:
setting the configuration information of each upper computer according to an agreed format;
and forming a configuration file by using the configuration information of the plurality of upper computers set according to the appointed format.
Preferably, the automatically forming the configuration information of the plurality of upper computers into the configuration file includes:
automatically extracting configuration information of each upper computer;
organizing the format of the configuration information of each upper computer according to the automatically extracted configuration information;
and forming a configuration file by the configuration information of each organized upper computer.
Preferably, the left-click function includes that when the function button is clicked through the left key, the upper computer corresponding to the function button is opened.
Preferably, the right click function includes calling up a menu of the upper computer corresponding to the function button when the function button is clicked by the right click.
As a second aspect of the present invention, an integrated device of multiple types of upper computers in an aircraft engine control system is provided, where the aircraft engine control system includes a control device and multiple types of upper computers connected to the control device, each type of upper computer is configured to send a control instruction to the control device, the control instructions sent by the multiple types of upper computers are different from each other, each type of upper computer includes configuration information, and the integrated device includes:
the configuration file forming module is used for acquiring configuration information of each upper computer and forming configuration files of the configuration information of the plurality of upper computers, wherein the configuration information of each upper computer stores an installation path of the upper computer;
the first judgment module is used for judging whether the configuration file is empty or not;
the acquisition module is used for acquiring the installation path of each upper computer in the configuration file when the configuration file is not empty;
the second judgment module is used for judging whether the installation path of each upper computer in the configuration file is successfully acquired;
the function button generation module is used for dynamically generating the function buttons of the upper computers according to the installation paths of the upper computers when the installation paths of the upper computers in the configuration files are successfully acquired;
and the function creating module is used for creating a left click function and a right click function of each function button of the upper computer aiming at the function button.
Preferably, the integrated device further comprises:
the first warning module is used for sending warning information of 'failure in reading the configuration file' when the configuration file is empty;
and the second alarm module is used for sending alarm information of 'configuration format error' when the installation path of each upper computer in the configuration file is not acquired successfully.
According to the method for integrating the plurality of upper computers in the aircraft engine control system, the configuration information of the plurality of different upper computers is formed into the configuration file, the one-to-one mapping of the installation paths of the plurality of upper computers is realized through the configuration file, the source of the used upper computer is ensured to be one, and the plurality of upper computers are integrated together for unified management, so that the problem of increased maintenance cost caused by disordered use when the aircraft engine control system uses the plurality of upper computers is solved through integrating the plurality of upper computers, and meanwhile, the control risk caused by misuse is avoided.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
FIG. 1 is a flow chart of a method for integrating a plurality of upper computers in an aircraft engine control system according to the present invention.
Fig. 2 is a detailed flow chart of a method for integrating various upper computers in the aircraft engine control system provided by the invention.
Fig. 3 is a schematic diagram of the corresponding relationship between configuration files and various upper computers in the integration method of various upper computers in the aircraft engine control system provided by the invention.
Fig. 4 is a schematic structural diagram of an integrated device of various upper computers in the aircraft engine control system provided by the invention.
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present invention, are given by way of illustration and explanation only, not limitation.
As a first aspect of the present invention, there is provided an integration method of multiple types of upper computers in an aircraft engine control system, where, as shown in fig. 1, the aircraft engine control system includes a control device and multiple types of upper computers connected to the control device, each type of upper computer is configured to send a control instruction to the control device, the control instructions sent by the multiple types of upper computers are different from each other, and each type of upper computer includes configuration information, the integration method includes:
s110, obtaining configuration information of each upper computer, and forming configuration files of the configuration information of the plurality of upper computers, wherein the configuration information of each upper computer stores an installation path of the upper computer;
s120, judging whether the configuration file is empty or not;
s130, when the configuration file is not empty, obtaining an installation path of each upper computer in the configuration file;
s140, judging whether the installation path of each upper computer in the configuration file is successfully acquired;
s150, when the installation path of each upper computer in the configuration file is successfully acquired, dynamically generating a function button of each upper computer according to the installation path of each upper computer;
and S160, establishing a left click function and a right click function of the function button aiming at the function button of each upper computer.
According to the method for integrating the plurality of upper computers in the aircraft engine control system, the configuration information of the plurality of different upper computers is formed into the configuration file, the one-to-one mapping of the installation paths of the plurality of upper computers is realized through the configuration file, the source of the used upper computer is ensured to be one, and the plurality of upper computers are integrated together for unified management, so that the problem of increased maintenance cost caused by disordered use when the aircraft engine control system uses the plurality of upper computers is solved through integrating the plurality of upper computers, and meanwhile, the control risk caused by misuse is avoided.
As a specific implementation manner, when the configuration file is empty, an alarm message of "failure in reading the configuration file" is sent out.
It can be understood that when the configuration file is not empty, it indicates that the configuration information of the upper computer forms the configuration file, so that the installation path of the upper computer can be obtained, and if the configuration file is empty, an alarm message is sent.
As another specific implementation manner, when the acquisition of the installation path of each upper computer in the configuration file is unsuccessful, an alarm message of "configuration format error" is sent out.
It can be understood that, when the installation path of the upper computer is acquired, it is possible that the acquisition is unsuccessful due to an error in the configuration file format, and at this time, an alarm message of "configuration format error" needs to be sent.
Specifically, the obtaining of the configuration information of each upper computer and the forming of the configuration information of the plurality of upper computers into the configuration file includes: and manually forming the configuration information of the plurality of upper computers into configuration files or automatically forming the configuration information of the plurality of upper computers into configuration files.
Further specifically, the manually forming configuration information of the plurality of upper computers into the configuration file includes:
setting the configuration information of each upper computer according to an agreed format;
and forming a configuration file by using the configuration information of the plurality of upper computers set according to the appointed format.
Further specifically, the automatically forming the configuration information of the plurality of upper computers into the configuration file includes:
automatically extracting configuration information of each upper computer;
organizing the format of the configuration information of each upper computer according to the automatically extracted configuration information;
and forming a configuration file by the configuration information of each organized upper computer.
Preferably, the left-click function includes that when the function button is clicked through the left key, the upper computer corresponding to the function button is opened.
Preferably, the right click function includes calling up a menu of the upper computer corresponding to the function button when the function button is clicked by the right click.
The specific working flow chart of the method for integrating various upper computers in the control system of the aircraft engine provided by the invention can be shown by referring to fig. 2.
The integration method of the plurality of upper computers in the aircraft engine control system provided by the invention can be used for uniformly managing the plurality of upper computers through the integration tool.
Specifically, the integration tool uses a specific software development environment to create an integration tool framework and set a configuration file of the integration tool, wherein the configuration file describes installation paths of the upper computer software. For ease of understanding, descriptions of configuration examples and formats are provided in configuration files.
Then, according to the installation path of each upper computer software in the configuration file, dynamically generating a corresponding upper computer software icon on the integrated tool interface, wherein each upper computer software icon is designed according to the executable file pattern proportion of the original upper computer software, and each icon is annotated following the name of the original upper computer software, as shown in fig. 3.
The design is that the integrated tool has a top hiding function after being opened. The display and the hiding of the interface are realized through the movement of the mouse, and in order to prevent the hidden position from being forgotten, a small icon mode at the lower right corner of a computer display screen is adopted, and the small icon is clicked to awaken the integrated tool to display the position.
It should be noted that, before using the upper computer software, a user must install the corresponding upper computer software, and after the installation, the complete path of the corresponding upper computer executable file on the computer is written as a piece of configuration information into the configuration file of the integration tool, as shown in fig. 1, the tool provides two configuration methods: 1) manual configuration (configuration format is appointed in the integrated tool configuration file by description words); 2) and dragging the installed executable file of the upper computer software to the interface shortcut configuration of the integration tool (the tool automatically writes information into the configuration file of the integration tool).
It should be further noted that the drag function method is called, logic for automatically setting configuration information is set in the drag function method, the related data information technology is firstly used for obtaining related information of a drag file according to the drag file, file paths, file names and the like in the information are extracted, then the format of the configuration information is organized according to the extracted information, then the configuration file is opened by reading a byte stream text technology, the organized information is written into the configuration file, and then the configuration file is closed, so that the automatic configuration function of the drag file is realized, and the automatic configuration function of the drag file is realized
On one hand, the configuration file is convenient for upper computer software maintenance personnel to search information such as the installation path of the current upper computer software and maintain the update of the upper computer software; on one hand, the current version of each upper computer software is ensured to be the latest, and the loss caused by misuse of the old version software by maintenance personnel is avoided.
In the subsequent use process, the update of the upper computer software may be encountered, and the mobility of the engine maintenance personnel is particularly high, so that the maintenance personnel can find the address of the old version upper computer through the configuration information in the integration tool to update the tool, and in this case, the configuration file of the integration tool does not need to be updated again. If the maintenance personnel need to replace the catalog for reinstallation, the original upper computer configuration information which corresponds to the current upper computer configuration information needing to be updated can be deleted, and then the updated upper computer information can be reconfigured.
The specific use process of the integrated tool in the process of managing various upper computers is as follows: after the upper computer integration tool is started, a byte stream text reading technology is used for opening the configuration file, information in the configuration file is read according to an agreed format and is placed in a cache, then a data stream is closed, and reading of the configuration file is completed. According to the number of the configuration information in the configuration file, the button controls with the corresponding number are generated circularly and dynamically, the arrangement sequence and the positions of the button controls are set automatically, the icon information of each piece of corresponding upper computer software is set in the icon attribute of the button control, and the name information of the upper computer is set in the text attribute of the button control. Meanwhile, the integrated tool interface is amplified in equal proportion according to the maximum position of the button, and the same attributes such as fonts can be beautified.
When the mouse is placed above the button, a small rectangular pop-up window is called, namely, the information is displayed when the mouse pointer of a user is positioned above the control, and the tool information is set as the target address of the tool.
When a right key is clicked, the added menu display control is called by the tool, the menu name defined by a developer is displayed, and functional logic is set in the corresponding menu, for example, the tool self-defines two common functions in the menu, searches for a target and opens a configuration file, when a target search option is clicked, the tool directly calls a starting process resource instruction to open a corresponding folder path according to the configuration information (path information of an upper computer) read into a cache corresponding to the control, so that a target search function is realized; when the option of opening the configuration file is clicked, a process resource starting instruction is directly called to open the configuration file of the tool, and the configuration file is used for viewing configuration information or modifying the configuration information.
When the left key is clicked, the integrated tool extracts the configuration information path and the executable file name corresponding to the control by reading the configuration information in the cache and combining with the correspondingly generated control, opens the corresponding executable file by calling a process resource instruction, and realizes the operation equivalent to finding the corresponding upper computer and opening the upper computer by double clicking
As a second aspect of the present invention, an integrated device of multiple types of upper computers in an aircraft engine control system is provided, where the aircraft engine control system includes a control device and multiple types of upper computers connected to the control device, each type of upper computer is configured to send a control instruction to the control device, the control instructions sent by the multiple types of upper computers are different from each other, each type of upper computer includes configuration information, as shown in fig. 4, the integrated device 10 includes:
the configuration file forming module 110 is used for acquiring configuration information of each upper computer, and forming configuration files of the configuration information of the plurality of upper computers, wherein the configuration information of each upper computer stores an installation path of the upper computer;
a first determining module 120, where the first determining module 120 is configured to determine whether the configuration file is empty;
an obtaining module 130, where the obtaining module 130 is configured to obtain an installation path of each upper computer in the configuration file when the configuration file is not empty;
a second judging module 140, where the second judging module 140 is configured to judge whether obtaining the installation path of each upper computer in the configuration file is successful;
the function button generating module 150 is used for dynamically generating the function button of each upper computer according to the installation path of each upper computer when the installation path of each upper computer in the configuration file is successfully acquired;
a function creating module 160, wherein the function creating module 160 is configured to create a left-click function and a right-click function of each function button of the upper computer.
According to the integration device of the multiple upper computers in the aircraft engine control system, the configuration information of the multiple different upper computers is formed into the configuration file, the one-to-one mapping of the installation paths of the multiple upper computers is realized through the configuration file, the source of the used upper computers is ensured to be one, and the multiple upper computers are integrated together for unified management, so that the problem of increased maintenance cost caused by disordered use when the aircraft engine control system uses the multiple upper computers is solved through integrating the multiple upper computers, and meanwhile, the control risk caused by misuse is avoided.
Specifically, the integrated device 10 further includes:
a first alarm module 170, configured to send an alarm message of "failed reading of the configuration file" when the configuration file is empty;
and the second alarm module 180 is used for sending alarm information of 'configuration format error' when the installation path of each upper computer in the configuration file is not acquired successfully.
It will be understood that the above embodiments are merely exemplary embodiments taken to illustrate the principles of the present invention, which is not limited thereto. It will be apparent to those skilled in the art that various modifications and improvements can be made without departing from the spirit and substance of the invention, and these modifications and improvements are also considered to be within the scope of the invention.
Claims (8)
1. The method for integrating various upper computers in the aircraft engine control system is characterized in that the aircraft engine control system comprises a control device and various upper computers connected with the control device, each upper computer is used for sending a control instruction to the control device, the control instructions sent by the various upper computers are different from each other, each upper computer comprises configuration information, and the method comprises the following steps:
acquiring configuration information of each upper computer, and forming configuration files of the configuration information of the plurality of upper computers, wherein the configuration information of each upper computer stores an installation path of the upper computer;
judging whether the configuration file is empty or not;
when the configuration file is not empty, acquiring an installation path of each upper computer in the configuration file;
judging whether the installation path of each upper computer in the configuration file is successfully acquired;
when the installation path of each upper computer in the configuration file is successfully acquired, dynamically generating a function button of each upper computer according to the installation path of each upper computer;
establishing a left-key clicking function and a right-key clicking function of each function button of each upper computer;
the left key clicking function comprises that when the function button is clicked through the left key, the upper computer corresponding to the function button is opened;
and the right click function comprises calling out a menu of the upper computer corresponding to the function button when the function button is clicked through the right click.
2. The method of integrating a plurality of host computers in an aircraft engine control system according to claim 1, wherein the method of integrating comprises:
and when the configuration file is empty, sending out alarm information of 'failure in reading the configuration file'.
3. The method of integrating a plurality of host computers in an aircraft engine control system according to claim 1, wherein the method of integrating comprises:
and when the installation path of each upper computer in the configuration file is not acquired successfully, sending out alarm information of 'configuration format error'.
4. The method for integrating a plurality of upper computers in an aircraft engine control system according to any one of claims 1 to 3, wherein the step of acquiring the configuration information of each upper computer and forming the configuration information of the plurality of upper computers into the configuration file comprises the steps of: and manually forming the configuration information of the plurality of upper computers into configuration files or automatically forming the configuration information of the plurality of upper computers into configuration files.
5. The method of claim 4, wherein manually forming the configuration information of the plurality of upper computers into the configuration file comprises:
setting the configuration information of each upper computer according to an agreed format;
and forming a configuration file by using the configuration information of the plurality of upper computers set according to the appointed format.
6. The method of integrating a plurality of upper computers in an aircraft engine control system according to claim 4, wherein automatically forming configuration information of the plurality of upper computers into a configuration file comprises:
automatically extracting configuration information of each upper computer;
organizing the format of the configuration information of each upper computer according to the automatically extracted configuration information;
and forming a configuration file by the configuration information of each organized upper computer.
7. The utility model provides an integrated device of multiple host computer in aeroengine control system, its characterized in that, including controlling means in the aeroengine control system and with the multiple host computer that controlling means connects, every kind of host computer be used for to controlling means sends control command, and the control command that multiple host computer sent is different each other, and every kind of host computer all includes configuration information, integrated device includes:
the configuration file forming module is used for acquiring configuration information of each upper computer and forming configuration files of the configuration information of the plurality of upper computers, wherein the configuration information of each upper computer stores an installation path of the upper computer;
the first judgment module is used for judging whether the configuration file is empty or not;
the acquisition module is used for acquiring the installation path of each upper computer in the configuration file when the configuration file is not empty;
the second judgment module is used for judging whether the installation path of each upper computer in the configuration file is successfully acquired;
the function button generation module is used for dynamically generating the function buttons of the upper computers according to the installation paths of the upper computers when the installation paths of the upper computers in the configuration files are successfully acquired;
the function creating module is used for creating a left-click function and a right-click function of each function button of the upper computer aiming at the function button;
the left key clicking function comprises that when the function button is clicked through the left key, the upper computer corresponding to the function button is opened;
and the right click function comprises calling out a menu of the upper computer corresponding to the function button when the function button is clicked through the right click.
8. The integrated device of a plurality of upper computers in an aircraft engine control system according to claim 7, wherein the integrated device further comprises:
the first warning module is used for sending warning information of 'failure in reading the configuration file' when the configuration file is empty;
and the second alarm module is used for sending alarm information of 'configuration format error' when the installation path of each upper computer in the configuration file is not acquired successfully.
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| US7266807B2 (en) * | 2002-12-20 | 2007-09-04 | Hitachi, Ltd. | Method for integration edition of setting file and setting file integration base |
| CN103455640A (en) * | 2013-09-29 | 2013-12-18 | 宇龙计算机通信科技(深圳)有限公司 | Method and device for displaying file management interfaces |
| CN103995833A (en) * | 2014-04-21 | 2014-08-20 | 深圳天珑无线科技有限公司 | Method and device for sharing configuration information |
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