CN112540891A - Remote control method and device for avionic bus test equipment - Google Patents
Remote control method and device for avionic bus test equipment Download PDFInfo
- Publication number
- CN112540891A CN112540891A CN202110111207.6A CN202110111207A CN112540891A CN 112540891 A CN112540891 A CN 112540891A CN 202110111207 A CN202110111207 A CN 202110111207A CN 112540891 A CN112540891 A CN 112540891A
- Authority
- CN
- China
- Prior art keywords
- test equipment
- module
- input
- avionic
- bus
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 260
- 238000000034 method Methods 0.000 title claims abstract description 30
- 238000004088 simulation Methods 0.000 claims abstract description 38
- 238000006243 chemical reaction Methods 0.000 claims abstract description 21
- 238000004458 analytical method Methods 0.000 claims abstract description 18
- 230000003993 interaction Effects 0.000 claims description 8
- 230000008520 organization Effects 0.000 claims description 6
- 238000012795 verification Methods 0.000 claims description 6
- 238000012423 maintenance Methods 0.000 abstract description 6
- 230000006870 function Effects 0.000 description 23
- 238000010586 diagram Methods 0.000 description 16
- 238000012545 processing Methods 0.000 description 5
- 230000004044 response Effects 0.000 description 4
- 238000004891 communication Methods 0.000 description 3
- 230000005284 excitation Effects 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- 238000012812 general test Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 238000003491 array Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004590 computer program Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000013024 troubleshooting Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/22—Detection or location of defective computer hardware by testing during standby operation or during idle time, e.g. start-up testing
- G06F11/2205—Detection or location of defective computer hardware by testing during standby operation or during idle time, e.g. start-up testing using arrangements specific to the hardware being tested
- G06F11/221—Detection or location of defective computer hardware by testing during standby operation or during idle time, e.g. start-up testing using arrangements specific to the hardware being tested to test buses, lines or interfaces, e.g. stuck-at or open line faults
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/005—Testing of electric installations on transport means
- G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/22—Detection or location of defective computer hardware by testing during standby operation or during idle time, e.g. start-up testing
- G06F11/26—Functional testing
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
- G06F16/20—Information retrieval; Database structures therefor; File system structures therefor of structured data, e.g. relational data
- G06F16/21—Design, administration or maintenance of databases
- G06F16/211—Schema design and management
Landscapes
- Engineering & Computer Science (AREA)
- Theoretical Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- Quality & Reliability (AREA)
- Databases & Information Systems (AREA)
- Data Mining & Analysis (AREA)
- Selective Calling Equipment (AREA)
Abstract
The invention discloses a remote control method and a remote control device for avionics bus test equipment. The remote control method comprises the steps of receiving a program control command from the automatic test computer, converting the program control command into an execution sequence according to the anchor point structure tree, converting the execution sequence into an input simulation command, transmitting the input simulation command to the avionic bus test equipment, obtaining a display image of the avionic bus test equipment, analyzing the image to obtain avionic bus parameters, coding the avionic bus parameters into a return command, and sending the return command to the automatic test computer. The device adopted by the remote control method comprises an image acquisition module, a parameter analysis module, a main control module, a control conversion module, an input control module and a program control interface module, and can realize remote control of avionic bus test equipment. The invention can enable the avionics bus test equipment to have a program control function, so that the avionics bus test equipment can be integrated into an avionics component automatic test system, the test efficiency is improved, and the maintenance cost is reduced.
Description
Technical Field
The invention belongs to the field of automatic testing, and particularly relates to a remote control method and device for avionics bus testing equipment.
Background
When testing and repairing an LRU (line replaceable unit) such as a VOR receiver in an interior maintenance shop of a civil aviation maintenance enterprise, an engineer usually manually tests the LRU according to a troubleshooting procedure of a CMM (parts maintenance manual).
Because the manual testing efficiency is low, in order to improve the testing efficiency of the avionic component, an avionic component automatic testing system needs to be developed to automatically test the avionic component.
An automatic Test System (Automated Test System) is a System capable of realizing Automated testing, and can automatically complete excitation, measurement, data processing and display or output a Test result.
General test equipment such as a digital multimeter, an arbitrary function generator and the like generally has a remote control function, and an automatic test computer can send and receive instructions according to a specified protocol through a remote control interface of the equipment to realize control over the test equipment; take a FLUKE8808A digital multimeter as an example, which provides an RS232 interface through which an automatic test computer sends SCPI Commands (Standard Commands for Programmable Instruments) to realize switching of measurement gears such as voltage and current, and receives SCPI response Commands sent by the Instruments to obtain actual measurement values such as voltage and current.
Different from a common tested object, the avionic component has the input and output of analog quantity, discrete quantity and the like of the common tested object and also has the input and output of an avionic bus, and when an avionic component automatic test system is developed, an automatic test computer needs to control general test equipment such as a universal meter, a signal source, a voltage source and the like and also needs to control the avionic bus test equipment at the same time. The existing avionics bus test equipment such as T1200B and the like generally does not have a remote control function, which brings difficulty to the development of an avionics component automatic test system.
In order to solve the problem, one solution is to specially develop avionics bus test equipment with a program control function and integrate the avionics bus test equipment into an avionics component automatic test system, and the problems of the solution are as follows: (1) the cost is high, the test equipment can only be used for a specific avionic component in general, (2) the resource waste of existing avionic bus test equipment in a workshop is caused, and (3) because new test equipment is replaced for avionic component testing, a replacement evaluation flow must be executed on the equivalence of the test equipment, so that the flow complexity is improved.
Another solution is that channels such as discrete quantity, analog quantity and the like of the avionic component are automatically tested by automatic testing computer program-controlled general-purpose equipment, and when relevant operations of avionic bus testing are met, the operations are still completed by manual operation, and the problem of the scheme is that: (1) automatic testing in the true sense is not realized, and only semi-automatic testing can be realized, and (2) most of testing steps of channels such as discrete quantity, analog quantity and the like of the avionic component can be completed only by controlling and matching the avionic bus channel, so that the testing efficiency is low.
The above description and solutions to the problems and their discovery are only intended to aid understanding of the technical solutions of the present invention, and do not represent that all of the above are prior art.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a remote control method and a remote control device for avionics bus test equipment.
The technical scheme adopted by the invention is as follows: a method of remotely controlling avionics bus test equipment, the method comprising:
firstly, receiving a program control command from an automatic test computer.
Secondly, converting the program control instruction into an execution sequence;
the execution sequence is the operational steps required to complete the programmed instruction.
Thirdly, converting the execution sequence into an input simulation instruction of avionic bus test equipment;
and inputting a simulation instruction, namely, when the operation steps given in the execution sequence are completed, the required specific operation of the input equipment of the avionic bus test equipment.
Fourthly, transmitting the input simulation instruction to avionic bus test equipment;
and converting the input simulation command into a data command form supported by the interface driving equipment, and transmitting the data command form to the aviation bus testing equipment through the interface driving equipment.
And fifthly, acquiring a display image of the avionic bus test equipment.
And sixthly, analyzing the image to obtain an avionic bus parameter.
And seventhly, encoding the avionic bus parameters into a return instruction.
And eighthly, sending the return instruction to an automatic test computer.
Optionally, the step two of converting the program-controlled instruction into an execution sequence in the present invention includes:
and (I) confirming whether an anchor point structure tree of the avionic bus test equipment is constructed, if so, entering the step (III), and otherwise, entering the step (II).
Secondly, constructing an anchor point structure tree of the avionic bus test equipment;
the anchor point structure tree stores the page organization structure of the avionic bus test equipment, and the position coordinates and the input and output attributes of the effective information area of each page.
And (III) constructing an execution sequence according to the anchor point structure tree.
Optionally, the anchor point structure tree is organized in a tree structure, a root node is an initial page of the avionic bus test equipment, and child nodes are different child pages which are entered after clicking different buttons, and so on; each page comprises position coordinates of a plurality of effective information areas and input and output attributes of the position coordinates; the position coordinates of the effective information area comprise a left upper corner coordinate and a right lower corner coordinate; the input and output attribute comprises three states of input, output and input and output.
Optionally, the analyzing the image in the sixth step to obtain the avionics bus parameters includes:
the method comprises the following steps of (I) segmenting an acquired image to obtain a segmented image set containing avionic bus parameter information;
and secondly, performing character recognition on the images in the segmented image set to obtain the avionic bus parameters.
The invention adopts another technical scheme that: a remote control apparatus for an avionics bus test device, the apparatus comprising: the system comprises a program control interface module, a main control module, a parameter analysis module, a control conversion module, an image acquisition module and an input control module; the main control module is connected with the program control interface module and used for converting the received program control instruction into a verification execution sequence, encoding avionic bus parameter information into a data packet and sending the data packet to the automatic test computer; the main control module is connected with the parameter analysis module; the parameter analysis module is connected with the image acquisition module and is used for receiving the image acquired by the image acquisition module and analyzing and identifying the image; the main control module is connected with the control conversion module; the control conversion module is connected with the input control module and used for converting the verification execution sequence into an input simulation instruction and transmitting the input simulation instruction to the avionic bus test equipment; the program control interface module is connected to an automatic test computer; the image acquisition module and the input control module are respectively connected to a man-machine interaction image output interface and an input control interface of the avionic bus test equipment.
The invention has the beneficial effects that:
(1) the remote control method and the remote control device for the avionic bus test equipment replace interaction between test personnel and the avionic bus test equipment, can be communicated with an automatic test computer, can enable the avionic bus test equipment without a program control function to have the program control function, can be integrated into an avionic component automatic test system, improve the test efficiency and reduce the maintenance cost.
(2) The remote control method and the remote control device for the avionic bus test equipment have the advantages that the avionic bus test equipment has a remote control function under the condition that the original avionic bus test equipment does not need to be replaced, changed or modified, the structural integrity of the original avionic bus test equipment is maintained, and a required replacement evaluation flow of the equivalence of the test equipment is avoided when the test equipment for avionic component testing is better, changed or modified.
(3) The avionic component automatic test system constructed by the avionic bus test equipment constructed by the method has the advantages of low cost, high speed and short time, and avoids resource waste caused by idle existing avionic bus test equipment.
(4) Compared with a semi-automatic avionics component automatic test system, the invention can construct a full-automatic avionics component automatic test system, improve the test efficiency and reduce the maintenance cost.
Drawings
FIG. 1 is a schematic diagram of an automatic test system according to the prior art;
FIG. 2 is a schematic diagram of an interface structure of a test device with program control function and communication between the test device and an automatic test computer in the prior art;
FIG. 3 is a schematic diagram of an interface structure of a avionics bus test device without a program control function and a relationship between the avionics bus test device and a tester in the prior art;
FIG. 4 is a schematic diagram of a semi-automatic avionics component testing system;
FIG. 5 is a schematic diagram of an avionics component automatic test system in which the present invention is used;
FIG. 6 is a flow chart of a remote control method of the avionics bus test equipment provided by the invention;
FIG. 7 is a schematic diagram of an anchor point structure tree provided by the present invention;
FIG. 8 is a connection block diagram of a remote control device of an avionics bus test equipment provided by the invention;
FIG. 9 is a connection block diagram of a second embodiment of the remote control device shown in FIG. 8 according to the present invention;
FIG. 10 is a connection block diagram of a third embodiment of the remote control device shown in FIG. 8 according to the present invention;
fig. 11 is a connection block diagram of a remote control device shown in fig. 8 according to another embodiment of the present invention.
Detailed Description
The invention is further illustrated by the following examples in conjunction with the accompanying drawings:
the avionics bus can be an ARINC429 bus, an ARINC664 bus, an ARINC629 bus, a 1553B bus or other avionics bus.
The avionics bus test equipment involved in the invention can be T1200A, T1200B, WFDX100 or other avionics bus test equipment.
Fig. 1 is a schematic structural diagram of an automatic test system in the prior art, and as shown in fig. 1, the automatic test system generally includes an automatic test computer, a test device, a switching system, a test program set, and the like, and implements automatic testing of a tested object. The switch system is used for switching the connecting line between the wiring end of each test device and the test point of the tested object; the test equipment provides excitation signals such as analog quantity, discrete quantity and the like for the tested object through a switch system, and measures response signals such as the analog quantity, the discrete quantity and the like of the tested object; the automatic test computer controls each test device and the switch system to work cooperatively, and tests the tested object according to the test program set.
Fig. 2 is a schematic diagram of an interface structure of a test device with a program control function and communication between the test device and an automatic test computer in the prior art, as shown in fig. 2, the interface of the test device with the program control function generally includes a remote control terminal, a test terminal, a power terminal, and the like; the automatic test computer is connected to the remote control terminal through a signal line, sends a control instruction to the test equipment and receives a response instruction of the test equipment; the test point of the avionics component is connected with the test terminal of the test equipment.
Fig. 3 is a schematic diagram of an interface structure of an avionics bus test device without a program control function and a relationship between the avionics bus test device and a tester in the prior art, and as shown in fig. 3, the avionics bus test device without the program control function interacts with the tester through a display screen and a keyboard and a mouse. The display screen is connected with the avionics bus test equipment through the image output interface, and the keyboard and the mouse are connected with the avionics bus test equipment through the keyboard and mouse input interface.
Fig. 4 is a schematic structural diagram of a semi-automatic avionics component test system, and as shown in fig. 4, common avionics components, such as a VOR receiver (VOR-700/900), a DME transceiver (DME-700/900), an ADF receiver (ADF-700/900), an ILS receiver (ILS-700/900), a VHF transceiver (VHF-700/900), etc., generally have analog input/output channels, discrete input/output channels, power input/output channels, radio frequency input/output channels, and an avionics bus input channel and an avionics bus output channel. When testing input/output channels of analog quantity, discrete quantity, power supply and radio frequency, universal equipment such as a signal source, a universal meter, an oscilloscope, a voltage source, a power meter, a frequency spectrograph and the like is generally used; when the avionics bus input channel and the avionics bus output channel are tested, avionics bus test equipment such as special equipment T1200B is needed. The avionic bus test equipment can provide an avionic bus excitation signal for the avionic component, encode parameters required by the avionic component into avionic bus data and excite the avionic component; the avionics bus data sent by the avionics component can be received and decoded. That is, when testing the avionics component, the required test equipment needs avionics bus test equipment, such as T1200B, in addition to common test equipment such as a digital multimeter. In a semi-automatic avionics component testing system, an automatic testing computer controls all general-purpose devices to work in coordination according to a testing program set so as to perform automatic testing, and when relevant operations of avionics bus testing are met, corresponding testing is still completed by operating the avionics bus testing devices by testers (a switching system is not shown in fig. 4).
Fig. 5 is a schematic diagram of an avionics component automatic test system using the present invention, and as shown in fig. 5, after the avionics component automatic test system is constructed by using the remote control device provided by the present invention, an automatic test computer can program general-purpose devices and avionics bus test devices simultaneously, so as to realize full-automatic test of an avionics component (a switching system is not shown in fig. 5).
The invention provides a remote control method of avionics bus test equipment, which comprises the following steps:
firstly, receiving a program control command from an automatic test computer;
the program control command may be a command set conforming to the SCPI standard, or a control protocol command set agreed in advance.
Secondly, converting the program control instruction into an execution sequence;
and according to the received program control command, constructing an execution sequence corresponding to the program control command, namely an execution sequence required for completing the program control command, for example, firstly clicking a specific button of the avionic bus test equipment, entering a specific page, inputting a specific value into a specific edit box and the like.
The second step comprises the following steps:
confirming whether an anchor point structure tree of the avionic bus test equipment is constructed or not, if so, entering a step (three), and otherwise, entering a step (two);
secondly, constructing an anchor point structure tree of the avionic bus test equipment;
the anchor point structure tree stores a page organization structure of the avionic bus test equipment, and the position coordinates and the input and output attributes of the effective information area of each page; the method is characterized in that a tree structure organization is adopted, a root node is an initial page of the avionic bus test equipment, and child nodes are different child pages which are entered after different buttons are clicked, and the process is analogized. Each page contains the position coordinates of a plurality of effective information areas and the input and output attributes thereof. The position coordinates of the effective information area comprise a left upper corner coordinate and a right lower corner coordinate; the input and output attribute comprises three states of input, output and input and output.
And constructing an anchor point structure tree corresponding to the avionic bus test equipment according to the page organization structure of the avionic bus test equipment, and the position coordinates and the input and output attributes of the effective information area of each page.
(III) constructing an execution sequence according to the anchor point structure tree;
and confirming a final page which needs to be entered by the avionic bus test equipment and an effective information area which needs to be written or read when the received program control command is executed. And traversing the anchor point structure tree to obtain the page and the effective information area, and obtaining an execution sequence entering the page and the required operation according to the traversing process and the result.
Converting the execution sequence into an input simulation instruction of the avionic bus test equipment;
and inputting a simulation instruction, namely completing the specific operation of the input device of the avionics bus test equipment required when the operation steps given in the sequence are executed. If the input equipment of the avionics bus test equipment is a keyboard mouse, the input simulation instruction is as follows: moving the mouse to a certain coordinate, clicking the left button of the mouse, releasing the left button of the mouse, pressing a specific key and the like.
Fourthly, transmitting the input simulation instruction to avionic bus test equipment;
and converting the input simulation instruction into a data instruction form supported by the interface driving equipment, and transmitting the data instruction form to the aviation bus testing equipment through the interface driving equipment so as to realize input control on the aviation bus testing equipment.
Fifthly, acquiring a display image of the avionic bus test equipment;
and acquiring an image of the aviation bus test equipment to obtain a display image containing avionic bus parameter information.
Analyzing the image to obtain an avionic bus parameter;
the avionic bus parameters comprise original values, decoded values and performance values of avionic bus data, the decoded values comprise parameter names and parameter values, and the performance values comprise data such as periods, check values and count values.
The sixth step comprises:
the method comprises the following steps of (I) segmenting an acquired image to obtain a segmented image set containing avionic bus parameter information;
and secondly, performing character recognition on the images in the segmented image set to obtain the avionic bus parameters.
Seventhly, encoding the avionic bus parameters into a return instruction;
the return instruction may be an instruction set conforming to the SCPI standard, or may be a control protocol instruction set agreed in advance.
And eighthly, sending the return instruction to the automatic test computer.
And sending a return instruction containing avionic bus parameter information to an automatic test computer for calling of a test program set so as to test and analyze the avionic component.
One or more of steps one through eight may be performed multiple times.
The first embodiment is as follows:
as shown in fig. 6, an embodiment of a remote control method of an avionics bus test device is given below, in this embodiment, the avionics bus is an ARINC429 avionics bus, and the avionics bus test device is T1200B.
Step S1: receiving a program control command from an automatic test computer;
the programmed instructions may be in the form of:
Enter ADF Test Mode；
Set Value：Fre，577.0；
Set Value：Pad，000；
Get Para；
the programmed instructions represent the need for the automated test computer to set the avionics bus test equipment to the ADF test mode, set the tuning frequency of the ADF avionics component to 577.0KHz, set Pad to 000, and acquire the measured parameters.
Step S2: converting the program control instruction into an execution sequence;
step S2 includes:
step S21: confirming whether an anchor point structure tree of the avionic bus test equipment is constructed, if so, entering S23, otherwise, entering S22;
step S22: constructing an anchor point structure tree of the avionic bus test equipment;
as shown in fig. 7, fig. 7 is a schematic diagram of an anchor point structure tree provided by the present invention. The root node is a main page of the avionic bus test equipment, N effective information areas are arranged under the main page, namely a first effective information area, a second effective information area and a third effective information area, and the effective information areas reach the Nth effective information area, and each effective information area comprises area coordinates and input/output/input/output attributes; for the first effective information area, the attribute is input, the form is button, after clicking the button, the next level first page is entered, the first page has a plurality of effective information areas, which are respectively the 11 th effective information area and the 12 th effective information area, the button of the 12 th effective information area is clicked to enter the 121 th page, the 1211 th effective information area and the 1212 nd effective information area are included under the 121 th page, and so on.
The anchor point structure tree stores the page organization structure of the avionic bus test equipment, the position coordinates and the input and output attributes of the effective information area of each page, and the program control instructions can be converted into execution sequences according to the anchor point structure tree.
Step S23: an execution sequence is constructed from the anchor point structure tree.
Generating the following execution sequence by traversing the anchor point structure tree:
PushButton：Reset；
WaitPage：MainPage；
PushButton：LRU Mode；
PushButton：ADF；
EditValue：Fre/577.0；
EditValue：Pad/000；
the above execution sequence represents: click the Reset button on the page, wait to enter the MainPage page, click the LRU Mode button, click the ADF button, enter 577.0 in the Fre edit box, and enter 000 in the Pad edit box. Because the system Reset needs a certain time, after the Reset button is clicked, the main page needs to be waited for entering, and other secondary pages can enter after being clicked, so that the pages do not need to be waited for.
Step S3: converting the execution sequence into an input simulation instruction of avionic bus test equipment;
and converting each operation in the execution sequence into the input simulation instruction.
For PushButton: the input emulation commands generated by Reset are as follows:
(1) acquiring region coordinates (x 1, y1, x2, y 2) of the Reset button through the anchor point structure tree;
(2) moving the mouse to the coordinates (| x1-x2|/2, | y1-y2 |/2);
(3) pressing a left mouse button;
(4) and releasing the left mouse button.
For the WaitPage: the MainPage can generate an input simulation instruction in an open-loop or closed-loop mode;
for an open-loop implementation:
(1) delaying for a period of time;
(2) proceed to the next step.
For closed loop implementation:
(1) acquiring a current display image;
(2) judging whether the current page is a MainPage, if so, entering the step (3), and if not, returning to the step (1);
(3) proceed to the next step.
For PushButton: LRU Model, PushButton: input simulation instructions generated by execution sequences such as ADF and the like and PushButton: the Reset execution sequence is similar except that the coordinates of the buttons are different and will not be described in detail herein.
For EditValue: the input simulation instruction generated by Fre/577.0 is as follows:
(1) acquiring Fre edit box coordinates (x 3, y3, x4, y 4) through the anchor point structure tree;
(2) moving the mouse to the coordinates (| x3-x4|/2, | y3-y4 |/2);
(3) pressing a left mouse button;
(4) releasing the left mouse button;
(5) sending a keyboard key instruction 5;
(6) sending a keyboard key instruction 7;
(7) sending a keyboard key instruction 7;
(8) sending a keyboard key instruction;
(9) sending a keyboard key instruction 0;
(10) and sending a keyboard key instruction Enter.
For step (10), the method can also be implemented by clicking an Enter button on the page, namely, step (10) is replaced by the following steps:
(10) obtaining Enter button coordinates (x 5, y5, x6, y 6) through the anchor point structure tree;
(11) moving the mouse to the coordinates (| x5-x6|/2, | y5-y6 |/2);
(12) pressing a left mouse button;
(13) and releasing the left mouse button.
For EditValue: pad/000 generated input simulation instruction with EditValue: fre/577.0 execution sequences are similar, except that the entered values and edit box coordinates are different and will not be described in detail herein.
Step S4: and transmitting the input simulation command to the avionics bus test equipment.
Taking an HID analog chip adopting a UART interface as an interface driving device, for example, converting an input analog instruction into a data instruction form supported by the HID analog chip, taking operations such as pressing a left mouse button and the like as examples:
pressing a left mouse button: 57 AB 0004070201000000000010;
releasing the left mouse button: 57 AB 000407020000000000000F;
move mouse to coordinates (100 ): 57 AB 0004070200400115020067;
pressing a key A: 57 AB 000208000004000000000010;
releasing the key A: 57 AB 00020800000000000000000C.
And transmitting the data instruction to the avionic bus test equipment through the HID analog chip by the UART interface so as to realize input control of the avionic bus test equipment.
Step S5: and acquiring a display image of the avionics bus test equipment.
Step S6: and analyzing the image to obtain the avionics bus parameters.
Step S6 includes:
step S61: and acquiring coordinates of all effective information areas through the anchor point structure tree, and segmenting the acquired display image according to the coordinates to obtain a segmented image set containing avionic bus parameter information.
Step S62: performing character recognition on the images in the segmented image set to obtain avionics bus parameter information such as parameter names, parameter values and the like as follows:
parameter name: bearing;
parameter values: 35;
and (3) period: 200 ms.
Step S7: encoding avionic bus parameters into a return instruction;
the return instruction may be of the form:
Para Name：Bearing；
Para Value：35；
Para Cyc：200。
step S8: and sending the return instruction to the automatic test computer.
In the above step, the parameter information of Bearing is acquired, and in order to acquire more parameter information, some steps may be repeated multiple times, for example, the steps after step S6 may be:
1. Another execution sequence is constructed from the anchor point structure tree as follows:
PushButton：Slot；
clicking the button causes the output display image of the avionics bus test equipment to be transformed so that other parameters appear in the display image.
2. And converting the new execution sequence into an input simulation instruction of the avionics bus test equipment.
The generated input simulation instruction is as follows:
(1) acquiring region coordinates (x 7, y7, x8, y 8) of the Slot button through the anchor point structure tree;
(2) moving the mouse to the coordinates (| x7-x8|/2, | y7-y8 |/2);
(3) pressing a left mouse button;
(4) and releasing the left mouse button.
3. And transmitting the new input simulation command to the avionics bus test equipment.
And repeating the steps S5-S6 to obtain new avionics bus parameter information as follows:
parameter name: CurrentFre;
parameter values: 577.0, respectively;
and (3) period: 350 ms.
4. Encoding all the obtained parameter information into a return instruction is as follows:
Para Name：Bearing；
Para Value：35；
Para Cyc：200；
Para Name：CurrentFre；
Para Value：577.0；
Para Cyc：350。
it can also be coded as follows to save communication bandwidth:
Para Name：Bearing，CurrentFre；
Para Value：35，577.0；
Para Cyc：200，350。
5. and sending the return instruction to the automatic test computer.
Fig. 8 shows a remote control device of an avionics bus test device, which includes an image acquisition module, an input control module, a parameter analysis module, a control conversion module, a main control module, and a program control interface module.
An image acquisition module: the method is used for acquiring the output image of the avionics bus test equipment.
A parameter analysis module: the image acquisition module is used for acquiring an image of the avionics bus, and analyzing and identifying the image to obtain parameter information of the avionics bus.
The main control module: the system is used for coding the avionic bus parameter information obtained by the parameter analysis module into a return instruction and analyzing the program control instruction into an execution sequence, and the execution sequence comprises an anchor point structure tree inside.
The control conversion module: for converting the execution sequence into the input simulation instruction.
An input control module: the aviation bus test device comprises an interface drive device and a controller thereof, converts an input simulation instruction into a data instruction form supported by the interface drive device, and transmits the data instruction form to the aviation bus test device through the interface drive device so as to realize input control of the aviation bus test device.
The program control interface module: for receiving programming instructions from the automatic test computer and for sending return instructions to the automatic test computer.
The image acquisition module is connected with the parameter analysis module, the input control module is connected with the control conversion module, the parameter analysis module is connected with the main control module, the control conversion module is connected with the main control module, and the program control interface module is connected with the main control module.
The program control interface module is connected to the automatic test computer; the image acquisition module and the input control module are respectively connected to a man-machine interaction image output interface and an input control interface of the avionic bus test equipment.
The working principle of the remote control device of the avionics bus test equipment shown in fig. 8 is as follows:
the automatic test computer sends a program control command to the remote control device; receiving by the program control interface module, and analyzing by the main control module according to the anchor point structure tree to obtain a verification execution sequence; the control conversion module converts the verification execution sequence into an input simulation instruction, and then the input simulation instruction is converted by the input control module and transmitted to a human-computer interaction input interface of the avionic bus test equipment, so that the input control of the avionic bus test equipment is realized; the image acquisition module acquires an output image of standard avionic bus test equipment, the parameter analysis module receives the image acquired by the image acquisition module and analyzes the image to obtain avionic bus parameters, the main control module encodes the avionic bus parameters into data packets according to a preset protocol and then sends the data packets to the automatic test computer, and the test program set processes the avionic bus parameters according to test requirements. The main control module can also control all the modules to work cooperatively so as to complete the test instruction of the test program set, and the main control module internally contains an anchor point structure tree corresponding to the avionic bus test equipment.
It can be understood that the specific forms of the output interface and the input interface of the avionic bus test equipment needing program control for human-computer interaction are different according to different models of the avionic bus test equipment; the output interface is usually an image input interface, such as VGA, HDMI, DVI, etc. for connecting with the display, and the input interface is usually an input control interface, such as PS/2, USB, etc. for connecting with the keyboard and mouse. The input control module and the image acquisition module can be realized according to a specific interface form, and the invention is not limited.
When the output display device of the avionics bus test equipment is independent of the host or is connected with the host through an external interface, the image acquisition module can be realized in a video acquisition card, an image acquisition device and the like to acquire a display image.
The display image output by the avionic bus test equipment host can be simultaneously output to the display device and the image acquisition module of the avionic bus test equipment host through devices such as a video distribution/switcher, and the like, so that the original output image of the avionic bus test equipment can be simultaneously seen by a tester while remote control is realized.
When the output display device of the avionics bus test equipment is integrated in the host or is connected with the host through an internal interface, the image acquisition module can be realized through a camera, an image sensor or other similar modes so as to acquire a display image.
When the input control device of the avionic bus test equipment is independent of the host computer or is connected with the host computer through an external interface, the input control module can realize the input control of the avionic bus test equipment through an HID converter, a PS/2 converter or other similar modes.
The device such as accessible concentrator, HUB inserts avionics bus test equipment's input control equipment and input control module simultaneously to avionics bus test equipment, when realizing remote control, still can make the tester also can control avionics bus test equipment's input simultaneously.
When the input control device of the avionic bus test equipment is integrated in the host or is connected with the host through an internal interface, the input control module can realize the input control of the avionic bus test equipment through a manipulator or other mechanical mechanisms.
The program control interface module can receive the program control instruction and send the return instruction in the form of a network interface, a UART serial port, a GPIB interface, a USB interface, other standard interfaces or custom interfaces, and can also receive the program control instruction and send the return instruction in the form of API call, message response, a signal slot and the like.
The image acquisition module, the parameter analysis module, the main control module, the control conversion module, the input control module and the program control interface module can be realized in a hardware, software or software and hardware combination mode. For a hardware implementation, the implementation may be in one or more Application Specific Integrated Circuits (ASICs), Digital Signal Processors (DSPs), Digital Signal Processing Devices (DSPDs), Programmable Logic Devices (PLDs), Field Programmable Gate Arrays (FPGAs), general purpose processors, controllers, micro-controllers, and the like; the hardware thereof can be arbitrarily selected. For a software implementation, software code may be developed in any programming language and may be stored in memory and executed by a processor. The memory may be implemented within the processor or external to the processor.
Hardware and software or combined software and hardware for realizing the image acquisition module, the parameter analysis module, the main control module, the control conversion module, the input control module and the program control interface module can be independent of avionic bus test equipment and an automatic test computer, can also be combined with the avionic bus test equipment, and can also be combined with the automatic test computer.
It is understood that the image acquisition module, the parameter analysis module, the main control module, the control conversion module, the input control module and the program control interface module are implemented in hardware, software or a combination of hardware and software, and are independent from or combined with the avionics bus test equipment and/or the automatic test computer, depending on the specific application and design constraints of the technical solution.
Example two:
fig. 9 is a view showing an embodiment of the present invention providing a remote control apparatus shown in fig. 8.
In this embodiment, the image output interface of the avionics bus test equipment is an HDMI interface, and the input control interface is a PS/2 interface.
In this embodiment, the HDMI capture card is used to implement the function of the image processing module, the PS/2 converter is used to implement the function of the input control module, and the GPIB interface is used to implement the function of the program control interface module; the PS/2 converter comprises a PS/2 analog chip and a controller thereof, converts the input analog instruction into a data instruction form supported by the PS/2 analog chip, and transmits the data instruction form to a PS/2 input interface of the avionic bus test equipment through the PS/2 analog chip.
In this embodiment, the parameter analysis module, the control conversion module, and the main control module are implemented based on the same controller in a form of combining software and hardware, and the controller is implemented by using an embedded development platform based on an FPGA chip. It will be appreciated that such a controller may also be an Application Specific Integrated Circuit (ASIC), a Digital Signal Processor (DSP), a Digital Signal Processing Device (DSPD), a Programmable Logic Device (PLD), a general purpose processor, a controller, a microcontroller, or the like.
In this embodiment, each functional module of the remote control device is implemented independently of the avionics bus test equipment and the automatic test computer.
Example three:
fig. 10 is yet another embodiment of the present invention providing a remote control device as shown in fig. 8.
In this embodiment, the image output interface of the avionics bus test equipment is a VGA interface, and the input control interface is a USB interface.
In this embodiment, a VGA acquisition card is used to implement the function of the image processing module, and an HID converter is used to implement the function of the input control module; the HID converter comprises an HID analog chip and a controller thereof, converts an input analog instruction into a data instruction form supported by the HID analog chip, and transmits the data instruction form to a USB input interface of the avionic bus test equipment through the HID analog chip.
In this embodiment, the parameter analyzing module, the control converting module, the main control module, and the interface API module together form a control program, which is implemented in a software form by combining with the automatic test computer. The interface API module communicates with a test suite in the automatic test computer in a software call manner.
In this embodiment, the control program composed of the parameter parsing module, the control conversion module, the main control module, and the interface API module is implemented by using C language, and it can be understood that the control program can also be implemented by using other languages such as C + +, Python, and the like.
Example four:
fig. 11 is yet another embodiment of the present invention providing a remote control device as shown in fig. 8.
When the avionics bus test equipment can deploy a third-party application module, each module of the remote control device can be realized on the basis of a hardware platform of the avionics bus test equipment. As shown in fig. 11, the avionics bus test device has a man-machine interface on a display screen, and the interface has a plurality of display controls and input controls.
The remote control device comprises a control acquisition module, a keyboard and mouse signal simulation module, a control parameter identification module, a keyboard and mouse signal conversion module, a main control module and a network port module. Different from the second embodiment, in this embodiment, the control acquisition module is used to implement the function of the image acquisition module, the key mouse signal simulation module is used to implement the function of the input control module, the control parameter identification module is used to implement the function of the parameter analysis module, the key mouse signal conversion module is used to implement the function of the control conversion module, and the network interface module is used to implement the function of the program control interface module.
The control acquisition module can acquire display control information on the human-computer interaction interface, and the control parameter identification module identifies parameters on the display control to obtain avionic bus parameter information. The main control module packs the analyzed data into a data packet according to a preset protocol, and transmits the data packet to the automatic test computer through the network port module for calling of the test program set. The test program set transmits the program control instruction data to the main control module through the network port module, and the execution sequence is obtained after the program control instruction data are analyzed by the main control module; the keyboard and mouse signal conversion module converts the execution sequence into an input simulation instruction of a keyboard and a mouse; converting an input simulation instruction of a keyboard and a mouse into a keyboard and mouse signal which can be recognized by a hardware platform of the avionic bus test equipment through a key and mouse signal simulation module, and transmitting the keyboard and mouse signal to an input control of a human-computer interaction interface so as to control the input of the avionic bus test equipment; the main control module can also control all the modules to work cooperatively so as to complete the test instruction of the test program set, and the main control module internally contains an anchor point structure tree corresponding to the avionic bus test equipment.
It can be understood that the keyboard and mouse signals are different according to different operating systems adopted on a hardware platform of the avionic bus test equipment, for example, in a Windows system, the keyboard and mouse operations are implemented by using a message mechanism, and then the keyboard and mouse signals are corresponding keyboard and mouse messages.
In this embodiment, each functional module of the remote control device is implemented in combination with the avionics bus test equipment.
Claims (5)
1. A method of remotely controlling avionics bus test equipment, the method comprising:
firstly, receiving a program control command from an automatic test computer;
secondly, converting the program control instruction into an execution sequence;
the execution sequence is the operation steps required for completing the program control command;
thirdly, converting the execution sequence into an input simulation instruction of avionic bus test equipment;
inputting a simulation instruction, namely, when the operation steps given in the execution sequence are completed, the specific operation of the input equipment of the avionic bus test equipment is required;
fourthly, transmitting the input simulation instruction to avionic bus test equipment;
converting the input simulation instruction into a data instruction form supported by interface driving equipment, and transmitting the data instruction form to aviation bus testing equipment through the interface driving equipment;
fifthly, acquiring a display image of the avionic bus test equipment;
analyzing the image to obtain an avionic bus parameter;
seventhly, encoding the avionic bus parameters into a return instruction;
and eighthly, sending the return instruction to an automatic test computer.
2. The remote control method of an avionics bus test equipment according to claim 1,
the step two of converting the program control command into an execution sequence comprises the following steps:
confirming whether an anchor point structure tree of the avionic bus test equipment is constructed or not, if so, entering a step (three), and otherwise, entering a step (two);
secondly, constructing an anchor point structure tree of the avionic bus test equipment;
the anchor point structure tree stores a page organization structure of the avionic bus test equipment, and the position coordinates and the input and output attributes of the effective information area of each page;
and (III) constructing an execution sequence according to the anchor point structure tree.
3. The remote control method of an avionics bus test equipment according to claim 2,
the anchor point structure tree is organized by adopting a tree structure, a root node is an initial page of the avionic bus test equipment, and child nodes are different child pages which are entered after different buttons are clicked, and the rest is done in the same way; each page comprises position coordinates of a plurality of effective information areas and input and output attributes of the position coordinates; the position coordinates of the effective information area comprise a left upper corner coordinate and a right lower corner coordinate; the input and output attribute comprises three states of input, output and input and output.
4. The remote control method of an avionics bus test equipment according to claim 1,
analyzing the image in the sixth step to obtain the avionics bus parameters comprises the following steps:
the method comprises the following steps of (I) segmenting an acquired image to obtain a segmented image set containing avionic bus parameter information;
and secondly, performing character recognition on the images in the segmented image set to obtain the avionic bus parameters.
5. A remote control apparatus for an avionics bus test device, the apparatus comprising: the system comprises a program control interface module, a main control module, a parameter analysis module, a control conversion module, an image acquisition module and an input control module;
the main control module is connected with the program control interface module and used for converting the received program control instruction into a verification execution sequence, encoding avionic bus parameter information into a data packet and sending the data packet to the automatic test computer; the main control module is connected with the parameter analysis module; the parameter analysis module is connected with the image acquisition module and is used for receiving the image acquired by the image acquisition module and analyzing and identifying the image; the main control module is connected with the control conversion module; the control conversion module is connected with the input control module and used for converting the verification execution sequence into an input simulation instruction and transmitting the input simulation instruction to the avionic bus test equipment;
the program control interface module is connected to an automatic test computer; the image acquisition module and the input control module are respectively connected to a man-machine interaction image output interface and an input control interface of the avionic bus test equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110111207.6A CN112540891B (en) | 2021-01-27 | 2021-01-27 | Remote control method and device for avionic bus test equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110111207.6A CN112540891B (en) | 2021-01-27 | 2021-01-27 | Remote control method and device for avionic bus test equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112540891A true CN112540891A (en) | 2021-03-23 |
| CN112540891B CN112540891B (en) | 2021-08-17 |
Family
ID=75017259
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110111207.6A Active CN112540891B (en) | 2021-01-27 | 2021-01-27 | Remote control method and device for avionic bus test equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112540891B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113468003A (en) * | 2021-06-18 | 2021-10-01 | 上海芷锐电子科技有限公司 | Tree-shaped display and operation system and method for chip test data |
| CN113514716A (en) * | 2021-04-20 | 2021-10-19 | 北京航空航天大学 | Digital bus electromagnetic environment effect simulation device and method |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090268878A1 (en) * | 2008-04-28 | 2009-10-29 | Embarq Holdings Company, Llc | System and Method for Remote Testing Of A Subscriber Loop |
| CN101915877A (en) * | 2010-07-02 | 2010-12-15 | 北京航空航天大学 | Bus technology-based universal electromagnetic susceptibility testing device and method |
| CN102353865A (en) * | 2011-09-05 | 2012-02-15 | 西安石油大学 | Automatic testing device and method universally used for multiple bus processor modules |
| CN103616560A (en) * | 2013-11-29 | 2014-03-05 | 中国航空无线电电子研究所 | Automatic power consumption parameter testing device and method applied to avionics device |
| CN104536858A (en) * | 2015-01-04 | 2015-04-22 | 中国科学院光电技术研究所 | Method for automatically testing remote terminal in 1553B bus communication |
| CN107885661A (en) * | 2017-11-08 | 2018-04-06 | 百度在线网络技术（北京）有限公司 | The terminal transparency method of testing and system of Mobile solution, equipment, medium |
| CN108803568A (en) * | 2018-06-08 | 2018-11-13 | 西安应用光学研究所 | One kind is based on ARINC429 bus avionics manipulation simulation system and method |
| CN108804302A (en) * | 2017-05-04 | 2018-11-13 | 腾讯科技（深圳）有限公司 | A kind of remote test method, system and relevant device |
| CN111044939A (en) * | 2019-12-27 | 2020-04-21 | 成都天奥测控技术有限公司 | Intelligent test system and test method for avionics HMI interface |
-
2021
- 2021-01-27 CN CN202110111207.6A patent/CN112540891B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090268878A1 (en) * | 2008-04-28 | 2009-10-29 | Embarq Holdings Company, Llc | System and Method for Remote Testing Of A Subscriber Loop |
| CN101915877A (en) * | 2010-07-02 | 2010-12-15 | 北京航空航天大学 | Bus technology-based universal electromagnetic susceptibility testing device and method |
| CN102353865A (en) * | 2011-09-05 | 2012-02-15 | 西安石油大学 | Automatic testing device and method universally used for multiple bus processor modules |
| CN103616560A (en) * | 2013-11-29 | 2014-03-05 | 中国航空无线电电子研究所 | Automatic power consumption parameter testing device and method applied to avionics device |
| CN104536858A (en) * | 2015-01-04 | 2015-04-22 | 中国科学院光电技术研究所 | Method for automatically testing remote terminal in 1553B bus communication |
| CN108804302A (en) * | 2017-05-04 | 2018-11-13 | 腾讯科技（深圳）有限公司 | A kind of remote test method, system and relevant device |
| CN107885661A (en) * | 2017-11-08 | 2018-04-06 | 百度在线网络技术（北京）有限公司 | The terminal transparency method of testing and system of Mobile solution, equipment, medium |
| CN108803568A (en) * | 2018-06-08 | 2018-11-13 | 西安应用光学研究所 | One kind is based on ARINC429 bus avionics manipulation simulation system and method |
| CN111044939A (en) * | 2019-12-27 | 2020-04-21 | 成都天奥测控技术有限公司 | Intelligent test system and test method for avionics HMI interface |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113514716A (en) * | 2021-04-20 | 2021-10-19 | 北京航空航天大学 | Digital bus electromagnetic environment effect simulation device and method |
| CN113514716B (en) * | 2021-04-20 | 2023-03-03 | 北京航空航天大学 | Digital bus electromagnetic environment effect simulation device and method |
| CN113468003A (en) * | 2021-06-18 | 2021-10-01 | 上海芷锐电子科技有限公司 | Tree-shaped display and operation system and method for chip test data |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112540891B (en) | 2021-08-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201757767U (en) | General comprehensive automatic test system of airplane electronic part | |
| CN112540891B (en) | Remote control method and device for avionic bus test equipment | |
| CN109873497B (en) | Power distribution main station and terminal automatic joint debugging acceptance method based on intelligent acceptance device | |
| CN112783794B (en) | Aviation communication radio station software testing system | |
| CN205786884U (en) | A kind of Testing System for Electronic Equipment | |
| CN104794258A (en) | Automobile hardware-in-loop simulation system | |
| CN109298317A (en) | A kind of Intelligent test device and its test method of middle low-frequency channel | |
| CN103913728B (en) | A kind of method of testing based on portable radar comprehensive tester | |
| CN109254214B (en) | Automatic test system and method for valve-based electronic equipment | |
| CN110749814A (en) | Automatic testing system and method for chip IC sample | |
| CN117763825A (en) | Substation auxiliary equipment sensor simulation method, system and device | |
| CN112505529A (en) | Board-level automatic test system | |
| CN108375708A (en) | A kind of flexible direct current power transmission system power module functional test board | |
| CN115391174A (en) | Automatic software testing platform | |
| Velihorskyi et al. | Remote Debugging of Embedded Systems in STM32CubeMonitor | |
| CN212112224U (en) | Thing networking intelligent household equipment testing arrangement | |
| CN111596203B (en) | Chip testing device, platform and method | |
| CN211121263U (en) | Signal conversion device and signal conversion board card | |
| CN112540890B (en) | Application layer verification method and device of avionic bus test equipment | |
| CN112104526A (en) | Test system and test method | |
| CN110412382B (en) | S-VDU response time automatic measuring device based on image processing | |
| CN212675512U (en) | Embedded system development platform | |
| Xuewu et al. | Design and implementation of data acquisition system based on Agilent 3458A | |
| CN220691052U (en) | Device for rapidly detecting RTC function | |
| CN220171123U (en) | Electric interference generating device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Application publication date: 20210323 Assignee: TIANJIN JIUYUE TECHNOLOGY Co.,Ltd. Assignor: CIVIL AVIATION University OF CHINA Contract record no.: X2024980002388 Denomination of invention: A remote control method and device for avionics bus testing equipment Granted publication date: 20210817 License type: Common License Record date: 20240301 |
|
| EE01 | Entry into force of recordation of patent licensing contract | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Application publication date: 20210323 Assignee: Tianjin water transport engineering survey and Design Institute Co.,Ltd. Assignor: CIVIL AVIATION University OF CHINA Contract record no.: X2024980004278 Denomination of invention: A remote control method and device for avionics bus testing equipment Granted publication date: 20210817 License type: Common License Record date: 20240412 |
|
| EE01 | Entry into force of recordation of patent licensing contract | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Application publication date: 20210323 Assignee: TIANJIN HANGXIN AVIATION TECHNOLOGY CO.,LTD. Assignor: CIVIL AVIATION University OF CHINA Contract record no.: X2024980006413 Denomination of invention: A remote control method and device for avionics bus testing equipment Granted publication date: 20210817 License type: Common License Record date: 20240529 |