CN105242997A - Automatic test method and apparatus for airborne computer - Google Patents
Automatic test method and apparatus for airborne computer Download PDFInfo
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- CN105242997A CN105242997A CN201510493044.7A CN201510493044A CN105242997A CN 105242997 A CN105242997 A CN 105242997A CN 201510493044 A CN201510493044 A CN 201510493044A CN 105242997 A CN105242997 A CN 105242997A
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Abstract
The invention provides an automatic test method and apparatus for an airborne computer. The method comprises: reading a pre-defined use case file and obtaining input control logic information and output control logic information of the airborne computer; generating a drive signal of the airborne computer according to the input control logic information, and inputting the drive signal to the airborne computer; acquiring a feedback signal corresponding to the drive signal, fed back by the airborne computer according to the output control logic information; and automatically testing the airborne computer according to the feedback signal. Through the automatic test method and apparatus, the problem of low test efficiency in related technologies is solved, so that the effect of improving the test efficiency is achieved.
Description
Technical field
The present invention relates to flight simulation field, in particular to a kind of airborne computer automatic test approach and device.
Background technology
In aircraft type development in the past, because aircraft volume is little, function is relatively simple, is all by building actual loading test platform and simple logic testing apparatus manually completes airborne computer test usually.Along with the development of modern technical aeronautics, aircraft system is tending towards comprehensive integrated control, thus it is complicated to make airborne computer have steering logic function, control assembly, controling parameters are various, the features such as data transmission information amount is maximum, adopt manpower, the financial resources of traditional verification experimental verification method meeting at substantial, Development Schedule can not ensure simultaneously.So the test completing airborne computer accurately, fast seems promising important.
Summary of the invention
The invention provides a kind of airborne computer automatic test approach and device, at least to solve the problem that in correlation technique, testing efficiency is not high, and then reach the effect improving testing efficiency.
According to an aspect of the present invention, provide a kind of airborne computer automatic test approach, the method comprises: read predefined use-case file, obtains input control logic information and the output control logic information of described airborne computer; Generate the pumping signal of described airborne computer according to described input control logic information, and described pumping signal is input to described airborne computer; The feedback signal corresponding to described pumping signal of airborne computer feedback according to described output control logic information acquisition; Automatically described airborne computer is tested according to described feedback signal.
Preferably, read predefined described use-case file, the described input control logic obtaining described airborne computer comprises: from described use-case file, read described input control logic information, wherein, described input control logic information comprises: hardware device ID, the first output signal of described hardware device, the output order of described first output signal of described hardware device, wherein, described hardware device is used for simulated aircraft equipment, and communicates with described airborne computer; Described first output signal is the signal that described hardware device outputs to described airborne computer.
Preferably, generate the pumping signal of described airborne computer according to described input control logic information, and described pumping signal is input to described airborne computer comprises: determine described hardware device ID according to described output order; Described hardware device is determined according to described hardware device ID; Control described hardware device and export described first output signal, and described first output signal is input in described airborne computer as described pumping signal.
Preferably, read predefined described use-case file, the described output control logic information obtaining described airborne computer comprises: from described use-case file, read described output control logic information, wherein, described output control logic information comprises: hardware device ID, the expection output valve of predefined described hardware device, the acquisition order of the first input signal of described hardware device, wherein, described first input signal is the signal that described hardware device exported to by described airborne computer.
Preferably, according to described output control logic information acquisition, the described feedback signal corresponding to described pumping signal of airborne computer feedback comprises: determine described hardware device ID according to described acquisition order; Described hardware device is determined according to described hardware device ID; Using described first input signal of described feedback signal as described hardware device, be input to described hardware device.
Preferably, automatically test described airborne computer and comprise: the processing costs obtaining described hardware device according to described feedback signal, wherein, described processing costs is that described hardware device processes rear generation to described first input signal; More described processing costs and described expection output valve, test described airborne computer whether normal operation according to comparative result.
According to a further aspect in the invention, providing a kind of airborne computer automatic testing equipment, comprising: read module, for reading predefined use-case file, obtaining input control logic information and the output control logic information of described airborne computer; Pumping signal generation module, for generating the pumping signal of described airborne computer according to described input control logic information, and is input to described airborne computer by described pumping signal; Feedback signal generation module, for the feedback signal corresponding to described pumping signal of the feedback of airborne computer according to described output control logic information acquisition; Test module, for automatically testing described airborne computer according to described feedback signal.
Preferably, described pumping signal generation module also for reading described input control logic information from described use-case file, wherein, described input control logic information comprises: hardware device ID, first output signal of described hardware device, the output order of described first output signal of described hardware device, wherein, described hardware device is used for simulated aircraft equipment, and communicates with described airborne computer; Described first output signal is the signal that described hardware device outputs to described airborne computer.
Preferably, described pumping signal generation module also comprises: hardware determining unit, for determining described hardware device ID according to described output order, and determines described hardware device according to described hardware device ID; Control module, exports described first output signal for controlling described hardware device, and described first output signal is input in described airborne computer as described pumping signal.
Preferably, described feedback signal generation module also for reading described output control logic information from described use-case file, wherein, described output control logic information comprises: hardware device ID, the expection output valve of predefined described hardware device, the acquisition order of the first input signal of described hardware device, wherein, described first input signal is the signal that described hardware device exported to by described airborne computer.
By the present invention, by the following technical solutions: read predefined use-case file, input control logic information and the output control logic information of described airborne computer is obtained; Generate the pumping signal of described airborne computer according to described input control logic information, and described pumping signal is input to described airborne computer; The feedback signal corresponding to described pumping signal of airborne computer feedback according to described output control logic information acquisition; Automatically test described airborne computer according to described feedback signal, solve the problem that in correlation technique, testing efficiency is not high, and then reach the effect improving testing efficiency.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide a further understanding of the present invention, and form a application's part, schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the process flow diagram of the airborne computer automatic test approach according to the embodiment of the present invention;
Fig. 2 is the structured flowchart of the airborne computer automatic testing equipment according to the embodiment of the present invention;
Fig. 3 is the structured flowchart of the airborne computer Auto-Test System according to the embodiment of the present invention;
Fig. 4 is the structural representation according to embodiment of the present invention use-case file.
Embodiment
Hereinafter also describe the present invention in detail with reference to accompanying drawing in conjunction with the embodiments.It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combine mutually.
Provide a kind of airborne computer automatic test approach in the present embodiment, Fig. 1 is the process flow diagram of the airborne computer automatic test approach according to the embodiment of the present invention, and as shown in Figure 1, this flow process comprises the steps:
Step S102, reads predefined use-case file, obtains input control logic information and the output control logic information of described airborne computer;
In one embodiment, read predefined described use-case file, the described input control logic obtaining described airborne computer comprises: from described use-case file, read described input control logic information, wherein, described input control logic information comprises: hardware device ID, the first output signal of described hardware device, the output order of described first output signal of described hardware device, wherein, described hardware device is used for simulated aircraft equipment, and communicates with described airborne computer; Described first output signal is the signal that described hardware device outputs to described airborne computer.
In another embodiment, read predefined described use-case file, the described output control logic information obtaining described airborne computer comprises: from described use-case file, read described output control logic information, wherein, described output control logic information comprises: hardware device ID, the expection output valve of predefined described hardware device, the acquisition order of the first input signal of described hardware device, wherein, described first input signal is the signal that described hardware device exported to by described airborne computer.
Step S104, generates the pumping signal of described airborne computer, and described pumping signal is input to described airborne computer according to described input control logic information;
In one embodiment, generate the pumping signal of described airborne computer according to described input control logic information, and described pumping signal is input to described airborne computer comprises: determine described hardware device ID according to described output order; Described hardware device is determined according to described hardware device ID; Control described hardware device and export described first output signal, and described first output signal is input in described airborne computer as described pumping signal.Preferably, generate the pumping signal of described airborne computer according to described input control logic information, and described pumping signal is input to described airborne computer comprises: determine described hardware device ID according to described output order; Described hardware device is determined according to described hardware device ID; Control described hardware device and export described first output signal, and described first output signal is input in described airborne computer as described pumping signal.
Step S106, the feedback signal corresponding to described pumping signal of airborne computer feedback according to described output control logic information acquisition;
In one embodiment, according to described output control logic information acquisition, the described feedback signal corresponding to described pumping signal of airborne computer feedback comprises: determine described hardware device ID according to described acquisition order; Described hardware device is determined according to described hardware device ID; Using described first input signal of described feedback signal as described hardware device, be input to described hardware device.
Step S108, tests described airborne computer automatically according to described feedback signal.
In one embodiment, automatically test described airborne computer and comprise: the processing costs obtaining described hardware device according to described feedback signal, wherein, described processing costs is that described hardware device processes rear generation to described first input signal; More described processing costs and described expection output valve, test described airborne computer whether normal operation according to comparative result.
By above-mentioned steps, solve the problem that in correlation technique, testing efficiency is not high, and then reach the effect improving testing efficiency.
Additionally provide a kind of airborne computer automatic testing equipment in the present embodiment, this device is used for realizing above-described embodiment and preferred implementation, has carried out repeating no more of explanation.As used below, term " module " can realize the software of predetermined function and/or the combination of hardware.Although the device described by following examples preferably realizes with software, hardware, or the realization of the combination of software and hardware also may and conceived.
Fig. 2 is the structured flowchart of the airborne computer automatic testing equipment according to the embodiment of the present invention, and as shown in Figure 2, this device comprises: read module 22, pumping signal generation module 24, feedback signal generation module 26 and test module 28.
Read module 22, for reading predefined use-case file, obtains input control logic information and the output control logic information of described airborne computer;
In one embodiment, read module 22 also for reading described input control logic information from described use-case file, wherein, described input control logic information comprises: hardware device ID, first output signal of described hardware device, the output order of described first output signal of described hardware device, wherein, described hardware device is used for simulated aircraft equipment, and communicates with described airborne computer; Described first output signal is the signal that described hardware device outputs to described airborne computer.
In another embodiment, described read module 22 also for reading described output control logic information from described use-case file, wherein, described output control logic information comprises: hardware device ID, the expection output valve of predefined described hardware device, the acquisition order of the first input signal of described hardware device, wherein, described first input signal is the signal that described hardware device exported to by described airborne computer.
Pumping signal generation module 24, for generating the pumping signal of described airborne computer according to described input control logic information, and is input to described airborne computer by described pumping signal; In addition, described pumping signal generation module 24 also comprises: hardware determining unit, for determining described hardware device ID according to described output order, and determines described hardware device according to described hardware device ID; Control module, exports described first output signal for controlling described hardware device, and described first output signal is input in described airborne computer as described pumping signal.
Feedback signal generation module 26, for the feedback signal corresponding to described pumping signal of the feedback of airborne computer according to described output control logic information acquisition; In one embodiment, described feedback signal generation module 26 is also for determining described hardware device ID according to described acquisition order; Described hardware device is determined according to described hardware device ID; Using described first input signal of described feedback signal as described hardware device, be input to described hardware device.Test module 28, for automatically testing described airborne computer according to described feedback signal.
Test module 28, for automatically testing described airborne computer according to described feedback signal.In one embodiment, test module 28 is also for obtaining the processing costs of described hardware device, and wherein, described processing costs is that described hardware device processes rear generation to described first input signal; More described processing costs and described expection output valve, test described airborne computer whether normal operation according to comparative result.
Be described below in conjunction with the preferred embodiment of the present invention.
The invention provides a kind of airborne computer automatic test approach and device, the method comprises: read predefined use-case file, obtains input control logic information and the output control logic information of above-mentioned airborne computer; Generate the pumping signal of above-mentioned airborne computer according to above-mentioned input control logic information, and above-mentioned pumping signal is input to above-mentioned airborne computer; According to the feedback signal corresponding to above-mentioned pumping signal of above-mentioned output control logic information acquisition above-mentioned airborne computer feedback; Automatically above-mentioned airborne computer is tested according to above-mentioned feedback signal.By the present invention, solve the problem that in correlation technique, testing efficiency is not high, and then reach the effect improving testing efficiency.
The airborne computer automatic test approach based on model that the embodiment of the present invention provides, the method comprises the following steps:
Step 1:
Hardware structure designs.According to the hardware interface type of tested carrying computer, selecting can the hardware device of test machine borne computer.
Step 2:
System simulation model designs.According to system under test (SUT) function, performance logic, set up component-level, system integration project test model.
Step 3:
Automatic test case designs.According to function, the performance logic of airborne computer content measurement, coupling system realistic model, use the automatic use-case of MicrosoftOfficeWord Software for Design according to test case template, use-case comprises use-case title, use-case numbering, performs step, exports the content such as step, expected results.
Step 4:
Use-case imports.Adopt the upper computer software design use-cases such as LABVIEW to import module, adopt the automatic test case that use-case importing module steps for importing 3 designs.
Step 5:
Use-case decoding.Use-case decoding is convert the information of the test case of importing to upper computer software discernible information.This step is realized by retrieve data library file.Database file comprises the corresponding relation of use-case information and upper computer software identifiable design information, comprising type, affiliated, title, code, collection, emulation, conversion K, conversion B, acquiescence etc.
Step 6:
Use-case performs.During open-loop test, according to the information of the automatic test case of decoding, automatic testing software directly controls corresponding hardware device excitation and image data according to the testing procedure of use-case; During closed loop test, according to the information of the automatic test case of decoding, automatic testing software first controls corresponding hardware device image data according to the testing procedure of use-case, then the data of collection are input to system simulation model to calculate, finally result of calculation are fed back to airborne computer by hardware device;
Step 7:
Qualification determination, the Output rusults of the airborne computer of collection and the expected results of automatic test case are compared, whether discriminating test result is qualified, and generates test report.
The present invention has following beneficial effect:
First, adopt MicrosoftOfficeWord Software for Design test case, use-case template is easily understood, and user is easy to start with.
Secondly, test case is designed by user oneself, and user can need selectivity to carry out case designing according to Project R&D, and content measurement is flexible, maintainable strong.
Again, all testing processs and parameter are all controlled automatically by software, compare manual test, largely save the time of test.
Automatic testing software according to the function of airborne computer, performance logic flexible design automatic test case, and can complete test fast and effectively, has the features such as simple to operate, test speed fast, maintainability is strong.
Obviously, those skilled in the art should be understood that, above-mentioned of the present invention each module or each step can realize with general calculation element, they can concentrate on single calculation element, or be distributed on network that multiple calculation element forms, alternatively, they can realize with the executable program code of calculation element, thus, they can be stored and be performed by calculation element in the storage device, and in some cases, step shown or described by can performing with the order be different from herein, or they are made into each integrated circuit modules respectively, or the multiple module in them or step are made into single integrated circuit module to realize.Like this, the present invention is not restricted to any specific hardware and software combination.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. an airborne computer automatic test approach, is characterized in that, comprising:
Read predefined use-case file, obtain input control logic information and the output control logic information of described airborne computer;
Generate the pumping signal of described airborne computer according to described input control logic information, and described pumping signal is input to described airborne computer;
The feedback signal corresponding to described pumping signal of airborne computer feedback according to described output control logic information acquisition;
Automatically described airborne computer is tested according to described feedback signal.
2. method according to claim 1, is characterized in that, read predefined described use-case file, the described input control logic obtaining described airborne computer comprises:
Described input control logic information is read from described use-case file, wherein, described input control logic information comprises: hardware device ID, first output signal of described hardware device, the output order of described first output signal of described hardware device, wherein, described hardware device is used for simulated aircraft equipment, and communicates with described airborne computer; Described first output signal is the signal that described hardware device outputs to described airborne computer.
3. method according to claim 2, is characterized in that, generates the pumping signal of described airborne computer according to described input control logic information, and described pumping signal is input to described airborne computer comprises:
Described hardware device ID is determined according to described output order;
Described hardware device is determined according to described hardware device ID;
Control described hardware device and export described first output signal, and described first output signal is input in described airborne computer as described pumping signal.
4. according to the method in any one of claims 1 to 3, it is characterized in that, read predefined described use-case file, the described output control logic information obtaining described airborne computer comprises:
Described output control logic information is read from described use-case file, wherein, described output control logic information comprises: hardware device ID, the expection output valve of predefined described hardware device, the acquisition order of the first input signal of described hardware device, wherein, described first input signal is the signal that described hardware device exported to by described airborne computer.
5. method according to claim 4, is characterized in that, according to described output control logic information acquisition, the described feedback signal corresponding to described pumping signal of airborne computer feedback comprises:
Described hardware device ID is determined according to described acquisition order;
Described hardware device is determined according to described hardware device ID;
Using described first input signal of described feedback signal as described hardware device, be input to described hardware device.
6. method according to claim 5, is characterized in that, automatically tests described airborne computer comprise according to described feedback signal:
Obtain the processing costs of described hardware device, wherein, described processing costs is that described hardware device processes rear generation to described first input signal;
More described processing costs and described expection output valve, test described airborne computer whether normal operation according to comparative result.
7. an airborne computer automatic testing equipment, is characterized in that, comprising:
Read module, for reading predefined use-case file, obtains input control logic information and the output control logic information of described airborne computer;
Pumping signal generation module, for generating the pumping signal of described airborne computer according to described input control logic information, and is input to described airborne computer by described pumping signal;
Feedback signal generation module, for the feedback signal corresponding to described pumping signal of the feedback of airborne computer according to described output control logic information acquisition;
Test module, for automatically testing described airborne computer according to described feedback signal.
8. device according to claim 7, it is characterized in that, described read module module also for reading described input control logic information from described use-case file, wherein, described input control logic information comprises: hardware device ID, the first output signal of described hardware device, the output order of described first output signal of described hardware device, wherein, described hardware device is used for simulated aircraft equipment, and communicates with described airborne computer; Described first output signal is the signal that described hardware device outputs to described airborne computer.
9. device according to claim 8, is characterized in that, described pumping signal generation module also comprises:
Hardware determining unit, for determining described hardware device ID according to described output order, and determines described hardware device according to described hardware device ID;
Control module, exports described first output signal for controlling described hardware device, and described first output signal is input in described airborne computer as described pumping signal.
10. the device according to any one of claim 7 to 9, it is characterized in that, described read module also for reading described output control logic information from described use-case file, wherein, described output control logic information comprises: hardware device ID, the expection output valve of predefined described hardware device, the acquisition order of the first input signal of described hardware device, wherein, described first input signal is the signal that described hardware device exported to by described airborne computer.
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Application publication date: 20160113 |