CN112540890B

CN112540890B - Application layer verification method and device of avionic bus test equipment

Info

Publication number: CN112540890B
Application number: CN202110111198.0A
Authority: CN
Inventors: 马腾达; 刘哲旭; 樊智勇; 王凯; 刘岱; 赵珍; 吴晓东
Original assignee: Civil Aviation University of China
Current assignee: Civil Aviation University of China
Priority date: 2021-01-27
Filing date: 2021-01-27
Publication date: 2021-08-17
Anticipated expiration: 2041-01-27
Also published as: CN112540890A

Abstract

The invention discloses an application layer verification method and device of avionic bus test equipment. The application layer verification method of the avionic bus test equipment realizes the automatic verification of the application layer function of the avionic bus test equipment to be verified by controlling standard avionic bus test equipment; and an avionic bus verification parameter database can be constructed by controlling standard avionic bus test equipment, and automatic verification is realized by the avionic bus verification parameter database. The application layer verification device comprises a computing platform, a first remote control module and a second remote control module. The method and the device for verifying the application layer of the avionic bus test equipment can automatically verify the application layer function of the developed avionic bus test equipment, have high verification efficiency and strong accuracy, and avoid human errors.

Description

Application layer verification method and device of avionic bus test equipment

Technical Field

The invention belongs to the field of avionics bus testing, and particularly relates to an application layer verification method and device of avionics bus testing equipment.

Background

The avionics bus test equipment is one of necessary test instruments when an interior maintenance workshop of a civil aviation maintenance enterprise tests and maintains LRU (line replaceable assembly) such as a VOR receiver and the like.

The avionic bus test equipment can provide an avionic bus excitation signal to the LRU, encode parameters required by the LRU into avionic bus data and excite the LRU; the avionics bus data sent by the LRU can be received and decoded, such as ARINC429 avionics bus tester T1200B, ARINC664 avionics bus tester WFDX100 and the like.

When the avionic bus test equipment is developed, besides the bottom layer capability of receiving and transmitting avionic bus data, the avionic bus test equipment also has application layer capability, namely the avionic bus test equipment has encoding and decoding capability on the avionic bus data.

Generally, when an avionics bus test device is developed, the encoding and decoding functions of avionics bus data are developed according to an ICD (interface control document), avionics bus specifications, or an avionics component manual; for example, patent CN102523129A discloses a general aviation bus test analysis method and device thereof, which implements encoding and decoding of avionics bus data through ICD documents. When the ICD document, the avionic bus specification and the avionic component manual are wrongly compiled or the compiled code cannot accurately reflect the ICD document, the avionic bus specification and the avionic component manual, errors in coding and decoding of avionic bus data may occur, and correct communication with an avionic component cannot be achieved.

Therefore, a reliable verification method is needed to verify the application layer function of the developed avionics bus test equipment. A study on an ARINC429 bus analyzer calibration system (study on an ARINC429 bus analyzer calibration system [ J ] measurement technique, 2016,36(S1): 224-. In addition, the avionic bus test equipment does not usually have a remote control function, so efficient and automatic verification cannot be realized, only partial data can be checked manually, the verification efficiency is low, and the avionic bus test equipment is also easily influenced by human factors.

Disclosure of Invention

In order to solve the problems in the prior art, the invention provides an application layer verification method and device of avionics bus test equipment.

The first technical scheme adopted by the invention is as follows: the method for verifying the application layer of the avionic bus test equipment is characterized by realizing the automatic verification of the application layer function of the avionic bus test equipment to be verified by controlling standard avionic bus test equipment, and comprises the following specific steps of:

firstly, connecting an avionic bus input channel and an avionic bus output channel of standard avionic bus test equipment with an avionic bus output channel and an avionic bus input channel of avionic bus test equipment to be verified.

Verifying the avionics bus decoding function of the avionics bus test equipment to be verified, wherein the verification comprises the following steps:

controlling standard avionic bus test equipment to send verification avionic bus data to avionic bus test equipment to be verified;

acquiring avionic bus verification parameters of standard avionic bus test equipment, wherein the avionic bus verification parameters comprise original values and corresponding decoded values;

acquiring avionic bus to-be-verified parameters of the avionic bus test equipment to be verified, wherein the avionic bus to-be-verified parameters comprise original values and corresponding decoded values;

and fourthly, comparing the verification parameters with the parameters to be verified to obtain a verification result.

Thirdly, verifying the avionics bus coding function of the avionics bus test equipment to be verified, comprising the following steps:

controlling avionic bus test equipment to be verified to send verification avionic bus data to standard avionic bus test equipment;

And fourthly, recording a verification result.

And fifthly, changing the avionics bus data for verification, and repeating the second step to the fourth step until all verification is completed.

Optionally, the method for controlling the standard avionics bus test equipment to send the verification avionics bus data to the avionics bus test equipment to be verified includes the following steps:

(1) sending a program control verification instruction;

the program control verification instruction comprises an original value of avionics bus data for verification;

(2) converting the program-controlled verification instruction into a verification execution sequence;

the verification execution sequence is the operation steps required for completing the program-controlled verification instruction;

(3) converting the verification execution sequence into an input simulation instruction of standard avionic bus test equipment;

the input simulation instruction is the concrete operation of the input equipment of the standard avionic bus test equipment required when the operation steps given in the verification execution sequence are completed;

(4) transmitting the input simulation instruction to standard 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 standard aviation bus testing equipment through the interface driving equipment.

Optionally, the controlling the avionics bus test equipment to be verified to send verification avionics bus data to the standard avionics bus test equipment according to the invention includes the following steps:

(1) sending a program control verification instruction;

(3) converting the verification execution sequence into an input simulation instruction of the avionic bus test equipment to be verified;

the input simulation instruction is the specific operation of the input equipment of the avionic bus test equipment to be verified, which is required when the operation steps given in the verification execution sequence are completed;

(4) transmitting the input simulation instruction to avionics bus test equipment to be verified;

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 test equipment to be verified through the interface driving equipment.

Optionally, the acquiring an avionics bus verification parameter of the standard avionics bus test equipment, which includes an original value and a corresponding decoded value, according to the present invention includes the following steps: (1) acquiring a display image of standard avionic bus test equipment; (2) and analyzing the image to obtain an avionic bus verification parameter.

Optionally, the obtaining of the avionics bus to-be-verified parameter of the avionics bus test equipment to-be-verified includes an original value and a corresponding decoded value, and includes the following steps: (1) acquiring a display image of the avionic bus test equipment to be verified; (2) and analyzing the image to obtain the parameter to be verified of the avionic bus.

Optionally, the converting the program-controlled verification instruction into the verification execution sequence according to the present invention includes the following steps:

A. confirming whether an anchor point structure tree of the avionic bus test equipment is constructed or not, if so, entering a step C, otherwise, entering a step B;

B. 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 comprises the following steps that a tree structure organization is adopted, a root node is an initial page of 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 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;

C. and constructing a verification execution sequence according to the anchor point structure tree.

The second technical scheme adopted by the invention is as follows: an application layer verification method of avionic bus test equipment is characterized in that an avionic bus verification parameter database is constructed by controlling standard avionic bus test equipment, and automatic verification of application layer functions of the avionic bus test equipment to be verified is realized through the avionic bus verification parameter database, and the method specifically comprises the following steps:

the method comprises the following steps of constructing an avionics bus verification parameter database based on standard avionics bus test equipment, wherein the method comprises the following steps:

controlling standard avionic bus test equipment to externally output verification avionic bus data;

recording the obtained avionic bus verification parameters, including original values and corresponding decoded values;

and (IV) changing the verification avionics bus data, repeating the step (I), the step (II) and the step (III), and constructing an avionics bus verification parameter database.

Verifying the avionic bus decoding function of the avionic bus test equipment to be verified; the method comprises the following steps:

acquiring avionic bus verification parameters from the avionic bus verification parameter database, wherein the avionic bus verification parameters comprise original values and corresponding decoded values;

acquiring avionic bus to-be-verified parameters of the avionic bus test equipment to be verified, wherein the avionic bus to-be-verified parameters comprise original values and corresponding decoded values; acquiring an original value which is the same as the original value in the step (one);

and thirdly, comparing the verification parameters with the parameters to be verified to obtain a verification result.

Thirdly, verifying the avionic bus coding function of the avionic bus test equipment to be verified; the method comprises the following steps:

And fourthly, recording a verification result.

And fifthly, acquiring other avionic bus verification parameters, and repeating the second step to the fourth step until all verification is finished.

Optionally, the decoded value of the present invention includes a parameter name of the decoded value and a parameter value of the decoded value.

Optionally, the avionic bus verification parameter database stores original values of the avionic bus data and corresponding decoded values, and is implemented by adopting a tree structure, a plurality of original value nodes are arranged below a root node, a plurality of parameter information nodes are arranged below each original value node, and each parameter information node comprises a parameter name of a decoded value and a parameter value of the decoded value.

The third technical scheme adopted by the invention is as follows: an application layer verification device of avionics bus test equipment, the device comprising: the system comprises a computing platform, a first remote control module and a second remote control module, wherein the computing platform is used for finishing functions of scheduling control, parameter data comparison verification and data storage; the first remote control module consists of a first program control interface module, a first main control module, a first parameter analysis module, a first control conversion module, a first image acquisition module and a first input control module; the system is used for realizing control input of standard avionic bus test equipment and acquiring output information of the standard avionic bus test equipment; the second remote control module consists of a second program control interface module, a second main control module, a second parameter analysis module, a second control conversion module, a second image acquisition module and a second input control module; the device is used for realizing control input of avionics bus test equipment to be verified and acquiring output information of the avionics bus test equipment to be verified; the first main control module and the second main control module are respectively connected with the computing platform through the first program control interface module and the second program control interface module and are used for converting received program control verification instructions into verification execution sequences, encoding avionic bus parameter information into data packets and sending the data packets to the computing platform; the first main control module and the second main control module are respectively connected with the first parameter analysis module and the second parameter analysis module; the first parameter analysis module and the second parameter analysis module are respectively connected with the first image acquisition module and the second image acquisition module and are used for receiving the images acquired by the image acquisition modules and analyzing and identifying the images; the first main control module and the second main control module are respectively connected with the first control conversion module and the second control conversion module; the first control conversion module and the second control conversion module are respectively connected with the first input control module and the second input control module and are used for converting the verification execution sequence into an input simulation instruction and transmitting the input simulation instruction to the standard avionic bus test equipment; the first image acquisition module and the first input control module are respectively connected to a man-machine interaction output interface and an input interface of the standard avionic bus test equipment; the second image acquisition module and the second input control module are respectively connected to a human-computer interaction output interface and an input interface of the avionic bus test equipment to be verified.

Optionally, the device of the present invention further comprises an avionics bus verification parameter database; the avionics bus verification parameter database is stored in a memory, and the memory is connected with the computing platform.

The fourth technical scheme adopted by the invention is as follows: an application layer verification device of avionics bus test equipment, the device comprising: the system comprises a computing platform, a first remote control module, a second remote control module, a verification program set and an avionic bus verification parameter database, wherein the computing platform is used for finishing functions of scheduling control, verification parameter data comparison and data storage; the second remote control module, the verification program set and the avionic bus verification parameter database which are connected in sequence are installed in the avionic bus test equipment to be verified; the main program is connected to the avionics bus test equipment to be verified through a second remote control module; the computing platform is connected with a first remote control module, and the first remote control module is connected with an output interface and an input interface of standard avionic bus test equipment; the computing platform is connected to an avionics bus verification parameter database in the avionics bus test equipment to be verified.

The invention has the beneficial effects that:

(1) according to the application layer verification method and device of the avionic bus test equipment, the avionic bus test equipment to be verified is verified through standard avionic bus test equipment, so that the application layer function of the developed avionic bus test equipment is verified, and the communication correctness between the avionic bus test equipment and an avionic component is ensured.

(2) The application layer verification method and device of the avionic bus test equipment can automatically verify the application layer function of the developed avionic bus test equipment, is high in verification efficiency and high in accuracy, and avoids human errors.

(3) The application layer verification method and the application layer verification device of the avionic bus test equipment can also carry out verification by constructing an avionic bus verification parameter database; therefore, standard avionic bus test equipment is only needed during construction, and during subsequent verification, the standard avionic bus test equipment is not needed any more, so that the dependence on the standard avionic bus test equipment is reduced.

(4) The avionic bus verification parameter database constructed by the application layer verification method and the application layer verification device of the avionic bus test equipment can be applied to verification of the avionic bus test equipment, and can also be used in research and development of avionic bus data coding and decoding equipment needed, such as a remote data concentrator or avionic system integrated verification equipment, and the like, and used as a coding and decoding database of the avionic bus data coding and decoding equipment.

(5) According to the application layer verification method and device of the avionic bus test equipment, when the program-controlled verification instruction is sent, the original value of the avionic data is sent instead of the coded value, verification is carried out in such a way, verification can be carried out under the condition that the avionic bus coding and decoding rules are unknown, and the adaptability and the universality of verification are improved.

The method and the device provided by the invention can be applied to the application layer function verification of avionic bus test equipment, and also can be applied to the application layer function verification of other avionic bus coding and decoding functional equipment, such as a remote data concentrator, an avionic system exciter, an avionic component simulator and the like.

Drawings

FIG. 1 is a flowchart of an application layer verification method of a avionics bus test device according to a first embodiment of the present invention;

FIG. 2 is a flowchart of an application layer verification method of a second avionics bus test device provided by the invention;

FIG. 3 is a connection block diagram of an application layer verification apparatus of an avionics bus test device applied to a first method of the present invention;

fig. 4 is a connection block diagram of an application layer authentication apparatus according to a third embodiment of the present invention, which is applied to the apparatus shown in fig. 3;

FIG. 5 is a connection block diagram of an application layer authentication apparatus according to a second embodiment of the present invention;

FIG. 6 is a connection block diagram of an application layer authentication apparatus applied to a second method, embodiment five, in accordance with the present invention;

FIG. 7 is a schematic diagram of an anchor point structure tree provided by the present invention;

FIG. 8 is a schematic diagram of an avionics bus validation parameter database architecture provided by the present invention;

FIG. 9 is a flow chart of sub-steps of step S112 in FIG. 1;

FIG. 10 is a flowchart of the substeps of step S122 of FIG. 1;

FIG. 11 is a flow chart of sub-steps of step S2 in FIG. 1;

FIG. 12 is a flow diagram of sub-steps of step SN01 of FIG. 2;

FIG. 13 is a flow diagram of sub-steps of step SN02 of FIG. 2;

fig. 14 is a flow diagram of sub-steps of step SN2 of fig. 2.

In the figure: 1. a first avionic bus connection cable; 2. the second avionics bus is connected to the cable.

Detailed Description

The invention is further illustrated by the following examples in conjunction with the accompanying drawings:

the avionics bus involved in the invention may be an ARINC429 bus, an ARINC664 bus, an ARINC629 bus, a 1553B bus or other avionics bus. The standard avionics bus test equipment may be T1200A, T1200B, WFDX100 or other standard avionics bus test equipment.

According to the application layer verification method of the avionic bus test equipment, provided by the invention, the automatic verification of the application layer function of the avionic bus test equipment to be verified is realized by controlling the standard avionic bus test equipment.

Step (2) in step (one) in step two, convert the program-controlled verification order into verifying the execution sequence: and (3) according to the received program-controlled verification instruction, constructing a verification execution sequence corresponding to the program-controlled verification instruction, namely, the verification execution sequence required for completing the program-controlled verification instruction, for example, firstly clicking a specific button of standard avionic bus test equipment, entering a specific page, inputting a specific value into a specific editing frame and the like. The method comprises the following steps:

A. confirming whether an anchor point structure tree of standard avionic bus test equipment is constructed or not, if so, entering the step C, otherwise, entering the step B;

B. constructing an anchor point structure tree of standard avionic bus test equipment;

and constructing an anchor point structure tree corresponding to the standard avionic bus test equipment according to the page organization structure of the standard avionic bus test equipment, and the position coordinates and the input and output attributes of the effective information area of each page.

The anchor point structure tree stores a page organization structure of standard avionic bus test equipment, and the position coordinates and input and output attributes of an 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 standard 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.

C. Constructing a verification execution sequence according to the anchor point structure tree;

and when the received program control verification instruction is confirmed to be executed, the standard avionic bus test equipment needs to enter a final page and an effective information area which needs to be subjected to writing operation or reading operation. And traversing the anchor point structure tree to obtain the page and the effective information area, and obtaining a verification execution sequence entering the page and required operation according to the traversal process and the result.

Step (3) in step (one) in the step two, the verification execution sequence is converted into an input simulation instruction of the standard avionic bus test equipment: and inputting a simulation instruction, namely completing the specific operation of the input equipment of the standard avionic bus test equipment required when the operation steps given in the verification execution sequence are finished. If the input equipment of the standard 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.

Step (4) in step (one) in the step two, the input simulation instruction is transmitted to the standard avionic bus test equipment: and converting the input simulation instruction into a data instruction form supported by the interface driving equipment, transmitting the data instruction form to the standard aviation bus testing equipment through the interface driving equipment so as to realize the input control of the standard aviation bus testing equipment, and transmitting the avionic bus data of the standard avionic bus testing equipment to the avionic bus testing equipment to be verified.

In the second step, acquiring avionic bus verification parameters of the standard avionic bus test equipment, including an original value and a corresponding decoded value, including:

(1) acquiring a display image of standard avionic bus test equipment;

and acquiring an image of standard aviation bus test equipment to obtain a display image containing avionics bus parameter information.

(2) Analyzing the image to obtain avionic bus verification parameters including an original value and a corresponding decoded value;

and analyzing and identifying the image to obtain an avionic bus verification parameter, wherein the avionic bus verification parameter comprises an original value before decoding of the data bus, a corresponding decoded value, a parameter name comprising the decoded value, a parameter value comprising the decoded value and other data.

The step (2) comprises the following steps:

A. segmenting the acquired image to obtain a segmented image set containing avionic bus verification parameter information;

B. and performing character recognition on the images in the segmented image set to obtain an original value and a corresponding decoded value.

The content of the step (three) in the step (two) is similar to that of the step (two), and the difference is that the operation object is the avionics bus test equipment to be verified, and the details are not described herein.

Step (IV) in the step (II), comparing the verification parameters with the parameters to be verified to obtain a verification result: the output channel of the standard avionic bus test equipment is connected with the input channel of the avionic bus test equipment to be verified, so that the original value of avionic bus data received by the avionic bus test equipment to be verified is consistent with the original value of the avionic bus data sent by the standard avionic bus test equipment. Firstly, comparing the original values of the avionic bus data, and if the original values of the avionic bus data are inconsistent, showing that the problem possibly exists in the bottom layer function of the avionic bus test equipment to be verified. And if the values are consistent, comparing the information such as the name and the parameter value of each parameter of the decoded value, if the information is consistent, proving that the avionic bus test equipment to be verified has correct decoding function on the original value of the avionic data, and if the information is inconsistent, indicating that the decoding function is incorrect.

The content of step (one) in step three is similar to that of step (one) in step two, except that the operation object is an avionics bus test device to be verified, and the details are not described herein. The contents of the steps (two), (three) and (four) in the step three are similar to those of the steps (two), (three) and (four) in the step two, and are not described in detail herein.

The first embodiment is as follows:

in the embodiment, the automatic verification of the application layer function of the avionic bus test equipment to be verified is realized by controlling the standard avionic bus test equipment; the avionics bus is an ARINC429 avionics bus, and the standard avionics bus test equipment is T1200B; referring to fig. 1, 9, 10 and 11, the specific steps are as follows:

step S0: connecting an avionic bus input channel and an avionic bus output channel of standard avionic bus test equipment with an avionic bus output channel and an avionic bus input channel of avionic bus test equipment to be verified;

step S1: verifying the avionic bus decoding function of the avionic bus test equipment to be verified; step S1 includes the following steps:

step S11: controlling standard avionic bus test equipment to send verification avionic bus data to avionic bus test equipment to be verified; step S11 includes the following steps:

step S111: sending a program control verification instruction;

the programmed validation instruction may be in the form of:

Enter Standard Mode；

Set Value：Tx，89D41080；

the above program-controlled verification instruction represents setting the standard avionics bus test equipment to the standard transceiving mode and setting the original value of the transmitted avionics bus data to 89D 41080.

Step S112: converting the program control verification instruction into a verification execution sequence; step S112 includes:

step S1121: confirming whether an anchor point structure tree of the standard avionic bus test equipment is constructed, if so, entering S1123, otherwise, entering S1122;

step S1122: constructing an anchor point structure tree of standard 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 below the main page, namely a 1 st effective information area, a 2 nd effective information area and a 3 rd 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 1 st effective information area, the attribute is input, the form is a button, after the button is clicked, the 1 st page of the next level is entered, a plurality of effective information areas are arranged under the 1 st page, the effective information areas 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, the page is entered into 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 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 the program control instruction can be converted into a verification execution sequence according to the anchor point structure tree.

Step S1123: constructing a verification execution sequence according to the anchor point structure tree;

by traversing the anchor point structure tree, the following verification execution sequence is generated:

PushButton：Reset；

WaitPage：MainPage；

PushButton：Standard Mode；

PushButton：HEX；

EditValue：Value/89D41080。

the above verification execution sequence represents: click the Reset button on the page, wait to enter the MainPage page, click the Standard Mode button, click the HEX button, enter 89D41080 in the Value 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 S113: converting the verification execution sequence into an input simulation instruction of standard avionic bus test equipment;

and converting each operation in the verification execution sequence into an input simulation instruction.

For PushButton: reset, the input emulation instructions generated 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: MainPage can adopt an open loop mode or a closed loop mode to generate an input simulation instruction.

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: standard Model, PushButton: HEX and the like verify the execution sequence, and the generated input simulation instruction is compared with PushButton: reset authentication execution sequences are similar except that the coordinates of the buttons are different and will not be described in detail herein.

For EditValue: Value/89D41080, the generated input simulation instruction is as follows: (1) obtaining Value 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 8; (6) sending a keyboard key instruction 9; (7) sending a keyboard key instruction D; (8) sending a keyboard key instruction 4; (9) sending a keyboard key instruction 1; (10) sending a keyboard key instruction 0; (11) sending a keyboard key instruction 8; (12) sending a keyboard key instruction 0; (13) and sending a keyboard key instruction Enter.

For step (13), the method can also be implemented by clicking an Enter button on the page, namely, step (13) is replaced by the following steps: (13) obtaining Enter button coordinates (x 5, y5, x6, y 6) through the anchor point structure tree; (14) moving the mouse to the coordinates (| x5-x6|/2, | y5-y6 |/2); (15) pressing a left mouse button; (16) and releasing the left mouse button.

Step S114: and transmitting the input simulation instruction to standard avionic bus test equipment.

Taking an HID analog chip adopting a UART interface as an interface driving device, for example, the input analog instruction is converted into a data instruction form supported by the HID analog chip, and operations such as pressing a left mouse button are taken 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 standard 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 S12: acquiring avionic bus verification parameters of standard avionic bus test equipment, wherein the avionic bus verification parameters comprise original values and corresponding decoded values; step S12 includes the following steps:

step S121: acquiring a display image of standard avionic bus test equipment;

step S122: analyzing the image to obtain avionic bus verification parameters, wherein the avionic bus verification parameters comprise original values and corresponding decoded values; step S122 includes the steps of:

step S1221: acquiring coordinates of all effective information areas through an anchor point structure tree, and segmenting the acquired display image according to the coordinates to obtain a segmented image set containing avionic bus verification parameter information;

step S1222: performing character recognition on the images in the segmented image set to obtain an original value and a corresponding decoded value as follows:

original value: 89D 41080;

parameter 1: parameter name: label, parameter values: 001;

parameter 2: parameter name: SDI, parameter value: 00;

parameter 3: parameter name: distance To Go, parameter value: +2750.4 NM;

parameter 4: parameter name: SSM, parameter values: POS;

parameter 5: parameter name: parity, parameter value: and (4) ODD.

Step S13: acquiring avionic bus to-be-verified parameters of the avionic bus test equipment to be verified, wherein the avionic bus to-be-verified parameters comprise original values and corresponding decoded values; the content of step S13 is similar to that of step S12, except that the operation target is the avionics bus test equipment to be verified, and details are not described here, and the original value and the corresponding decoded value are obtained as follows:

original value: 89D 41080;

parameter 1: parameter name: label, parameter values: 001;

parameter 2: parameter name: SDI, parameter value: 00;

parameter 3: parameter name: distance To Go, parameter value: +2750.4 NM;

parameter 4: parameter name: SSM, parameter values: POS;

parameter 5: parameter name: parity, parameter value: and (4) ODD.

Step S14: comparing the verification parameters with the parameters to be verified to obtain verification results;

and comparing, wherein the original value is consistent with the corresponding decoded value, and the verification is passed.

Step S2: verifying the avionic bus coding function of the avionic bus test equipment to be verified;

step S2 includes the following steps:

step S21: controlling the avionic bus test equipment to be verified to send verification avionic bus data to standard avionic bus test equipment; the transmitted avionics bus data is 89D41080, and this step is similar to the step included in step S11, except that the operation object is an avionics bus test device to be verified, and is not described in detail here.

Step S22: acquiring avionic bus verification parameters of standard avionic bus test equipment, wherein the avionic bus verification parameters comprise original values and corresponding decoded values; the content of this step is similar to that of step S12, and will not be described in detail here, and the original value and the corresponding decoded value are obtained as follows:

original value: 89D 41080;

parameter 1: parameter name: label, parameter values: 001;

parameter 2: parameter name: SDI, parameter value: 00;

parameter 3: parameter name: distance To Go, parameter value: +2750.4 NM;

parameter 4: parameter name: SSM, parameter values: POS;

parameter 5: parameter name: parity, parameter value: and (4) ODD.

Step S23: acquiring avionic bus to-be-verified parameters of the avionic bus test equipment to be verified, wherein the avionic bus to-be-verified parameters comprise original values and corresponding decoded values; the content of step S23 is similar to step S13 and will not be described in detail here. The original values and corresponding decoded values are obtained as follows:

original value: 89D 41080;

parameter 1: parameter name: label, parameter values: 001;

parameter 2: parameter name: SDI, parameter value: 00;

parameter 3: parameter name: distance To Go, parameter value: +2750.4 NM;

parameter 4: parameter name: SSM, parameter values: POS;

parameter 5: parameter name: parity, parameter value: and (4) ODD.

Step S24: comparing the verification parameters with the parameters to be verified to obtain verification results;

Step S3: recording a verification result;

the results are reported in the following table:

step S4: steps S1 through S3 are repeated until all verifications are completed.

And changing the verification avionics bus data into other values, and repeating the steps from S1 to S3 until all the avionics bus data are verified.

According to the second application layer verification method for the avionic bus test equipment, the standard avionic bus test equipment is controlled, the avionic bus verification parameter database is constructed, and the avionic bus verification parameter database is used for realizing automatic verification of the application layer function of the avionic bus test equipment to be verified.

The content of step (a) in step one is similar to that of step (a) in step two in the first method, except that the standard avionic bus output channel does not need to be connected to the avionic bus test equipment to be verified, but no equipment reception does not affect the data transmission thereof, and therefore, the details are not described herein. The content of step (ii) in step one is similar to that of step (ii) in step two in the first method, and will not be described in detail here. The content of step (two) in step two is similar to that of step (three) in step two in the first method, and is not described in detail herein, except that the avionics bus test equipment to be verified is remotely controlled so that the original value obtained is the same as the original value in step (one). The content of step (three) in step two is similar to that of step (four) in step two in the first method, and is not described in detail here. The contents of steps (a), (b), and (c) in step three are similar to those of steps (a), (b), and (c) in step two, and will not be described in detail here.

One or more of the first to fifth steps and the sub-steps thereof in the first method or the second method may be implemented in one or more hardware modules, may be implemented in one or more software modules, and may be implemented in a form of combination of one or more hardware modules and software modules. To verify a particular parameter, one or more of steps one through five and their sub-steps in the first or second method may be performed multiple times.

The avionic bus equipment has the advantages that the encoding and decoding rules of the avionic bus data are consistent, the encoding function is verified when the decoding function is verified, and the decoding function is verified similarly; therefore, the application layer verification method of the avionics bus test equipment can also comprise the following steps: step one, step two, step four, step five in the first method; or step one, step three, step four and step five in the first method; or step one, step two, step four and step five in the second method; or step one, step three, step four and step five in the second method.

Example two:

in the embodiment, an avionic bus verification parameter database is constructed by controlling standard avionic bus test equipment, and the avionic bus verification parameter database is used for realizing the automatic verification of the application layer function of the avionic bus test equipment to be verified; the avionics bus is an ARINC429 avionics bus, and the standard avionics bus test equipment is T1200B; referring to fig. 2, 12, 13 and 14, the specific steps are as follows:

step SN 0: constructing an avionic bus verification parameter database based on standard avionic bus test equipment; step SN0 includes the following steps:

step SN 01: controlling standard avionic bus test equipment to externally output verification avionic bus data; step SN01 includes the following steps:

step SN 011: sending a program control verification instruction;

the programmed validation instruction may be in the form of:

Enter Standard Mode；

Set Value：Tx，89D41080。

the above program-controlled verification instruction represents setting the standard avionics bus test equipment to the standard transceiving mode and setting the original value of the transmitted avionics bus data to 89D 41080. Although the standard avionics bus test equipment is not connected to the avionics bus test equipment to be verified, this does not affect its data transmission.

Step SN 012: converting the program control verification instruction into a verification execution sequence; step SN012 includes:

step SN 0121: confirming whether an anchor point structure tree of standard avionic bus test equipment is constructed or not, if so, entering SN0123, otherwise, entering SN 0122;

step SN 0122: constructing an anchor point structure tree of standard avionic bus test equipment; the anchor point structure tree is described in step S1122 and will not be described in detail.

Step SN 0123: constructing a verification execution sequence according to the anchor point structure tree;

by traversing the anchor point structure tree, generating a verification execution sequence as follows:

PushButton：Reset；

WaitPage：MainPage；

PushButton：Standard Mode；

PushButton：HEX；

EditValue：Value/89D41080。

the above verification execution sequence, meaning of which is described in step S1123, is not described in detail here.

Step SN 013: converting the verification execution sequence into an input simulation instruction of standard avionic bus test equipment;

and converting each operation in the verification execution sequence into the input simulation instruction. The converted input analog command has already been described in step S113 and will not be described in detail here.

Step SN 014: transmitting the input simulation instruction to standard avionic bus test equipment; the execution process of this step is already described in step S114 and will not be described in detail here.

Step SN 02: acquiring avionic bus verification parameters of standard avionic bus test equipment, wherein the avionic bus verification parameters comprise original values and corresponding decoded values; step SN02 includes the following steps:

step SN 021: acquiring a display image of standard avionic bus test equipment;

step SN 022: analyzing the image to obtain avionic bus verification parameters, wherein the avionic bus verification parameters comprise original values and corresponding decoded values; step SN022 comprises the following steps:

step SN 0221: acquiring coordinates of all effective information areas through an anchor point structure tree, and segmenting the acquired display image according to the coordinates to obtain a segmented image set containing avionic bus verification parameter information;

step SN 0222: performing character recognition on the images in the segmented image set to obtain an original value and a corresponding decoded value as follows:

original value: 89D 41080;

parameter 1: parameter name: label, parameter values: 001;

parameter 2: parameter name: SDI, parameter value: 00;

parameter 3: parameter name: distance To Go, parameter value: +2750.4 NM;

parameter 4: parameter name: SSM, parameter values: POS;

parameter 5: parameter name: parity, parameter value: and (4) ODD.

Step SN 03: recording the obtained avionics bus verification parameters, including an original value and a corresponding decoded value;

step SN 04: and repeating the steps SN01, SN02 and SN03 to construct the avionics bus verification parameter database.

Referring to fig. 8, an example of the built avionics bus validation parameter database is as follows, where there are a plurality of original values under the root node, and there are a plurality of parameters under each original value, including parameter names and parameter values:

-a root node:

-1 st original value: 89D 41080;

parameter 1: parameter name: label, parameter values: 001;

parameter 2: parameter name: SDI, parameter value: 00;

parameter 3: parameter name: distance To Go, parameter value: +2750.4 NM;

parameter 4: parameter name: SSM, parameter values: POS;

parameter 5: parameter name: parity, parameter value: ODD;

......

-mth original value: 89D 40088;

parameter 1: parameter name: label, parameter values: 021 (b);

parameter 2: parameter name: SDI, parameter value: 00;

parameter 3: parameter name: selected N1, parameter values: 2750 RPM;

parameter 4: parameter name: PAD, parameter value: 0000;

parameter 5: parameter name: SSM, parameter values: NML;

parameter 6: parameter name: parity, parameter value: and (4) ODD.

Step SN 1: verifying the avionic bus decoding function of the avionic bus test equipment to be verified; step SN1 includes the following steps:

step SN 11: acquiring avionic bus verification parameters from an avionic bus verification parameter database, wherein the avionic bus verification parameters comprise original values and corresponding decoded values;

the 1 st avionics bus verification parameters are obtained as follows:

original value: 89D 41080;

parameter 1: parameter name: label, parameter values: 001;

parameter 2: parameter name: SDI, parameter value: 00;

parameter 3: parameter name: distance To Go, parameter value: +2750.4 NM;

parameter 4: parameter name: SSM, parameter values: POS;

parameter 5: parameter name: parity, parameter value: and (4) ODD.

Step SN 12: acquiring avionic bus to-be-verified parameters of the avionic bus test equipment to be verified, wherein the avionic bus to-be-verified parameters comprise original values and corresponding decoded values; the content of step SN12 is similar to that of step S13 and will not be described in detail herein, except that the avionics bus test equipment machine to be verified is remotely controlled so that the original value obtained is the same as that in step SN 11.

Step SN 13: comparing the verification parameters with the parameters to be verified to obtain verification results; the content of step SN13 is similar to step S14 and will not be described in detail here.

Step SN 2: verifying the avionic bus coding function of the avionic bus test equipment to be verified; step SN2 includes the following steps:

step SN 21: acquiring avionic bus verification parameters from an avionic bus verification parameter database, wherein the avionic bus verification parameters comprise original values and corresponding decoded values; the contents of step SN21 are similar to step SN11 and will not be described in detail herein.

Step SN 22: acquiring avionic bus to-be-verified parameters of the avionic bus test equipment to be verified, wherein the avionic bus to-be-verified parameters comprise original values and corresponding decoded values; wherein, when the original value is acquired, the original value is made the same as that in step SN 21. Step SN22 is similar to the step included in step S23 and will not be described in detail herein.

Step SN 23: comparing the verification parameters with the parameters to be verified to obtain verification results; the content of step SN23 is similar to step S24 and will not be described in detail here.

Step SN 3: recording a verification result; the content of step SN3 is similar to step S3 and will not be described in detail here.

Step SN 4: step SN1 through step SN3 are repeated until all verifications are completed.

And acquiring other avionic bus verification parameters through the avionic bus verification parameter database, and repeating the steps SN1 to SN3 until all verification is completed.

FIG. 3 is an application layer verification apparatus of an avionics bus test device provided by the invention, which is applied to a first method provided by the invention; as shown in fig. 3, the apparatus includes a computing platform, a first remote control module, and a second remote control module. A computing platform: the method is used for finishing the overall control and realization of the application layer verification function, and comprises scheduling control, verification parameter data comparison, data storage and the like. A first remote control module: the system comprises a first program control interface module, a first main control module, a first parameter analysis module, a first control conversion module, a first image acquisition module and a first input control module; the system is used for enabling the non-programmable standard avionic bus test equipment to be remotely controlled by the computing platform, and realizing control input and acquisition of output information of the standard avionic bus test equipment. A second remote control module: the system comprises a second program control interface module, a second main control module, a second parameter analysis module, a second control conversion module, a second image acquisition module and a second input control module; the method is used for enabling the non-programmable avionics bus test equipment to be verified to be remotely controlled by the computing platform, and realizing control input and acquisition of output information of the avionics bus test equipment to be verified.

The first image acquisition module and the first image acquisition module: and the method is used for respectively obtaining the output images of the standard avionic bus test equipment and the avionic bus test equipment to be verified. The first parameter analysis module and the second parameter analysis module: the image acquisition module is used for acquiring an image, analyzing and identifying the image and acquiring avionic bus parameter information including an original value and a corresponding decoded value. The first control conversion module and the second control conversion module: for converting the verified execution sequence into input emulation instructions. The first input control module and the second input control module: the interface driving device converts an input analog instruction into a data instruction form supported by the interface driving device, and transmits the data instruction form to the standard avionic bus test device and the avionic bus test device to be verified through the interface driving device so as to realize input control of the standard avionic bus test device and the avionic bus test device to be verified. The first program control interface module and the second program control interface module: the system is used for receiving a program-controlled verification instruction from the computing platform and sending a data packet encoded with avionics bus parameter information to the computing platform. The first main control module and the second main control module: the system comprises a first parameter analysis module, a second parameter analysis module, a program control verification instruction and a data packet processing module, wherein the first parameter analysis module and the second parameter analysis module are used for coding avionic bus parameter information obtained by the first parameter analysis module and the second parameter analysis module into data packets which can be processed by a computing platform, and the program control verification instruction is analyzed into a verification execution sequence, and an anchor point structure tree is contained in the program control verification instruction.

Standard avionics bus test equipment: the device is used for providing avionics bus verification parameters, comprises original values and corresponding decoded values, and comprises an output interface and an input interface with human-computer interaction and an avionics bus input and output channel. The avionics bus test equipment to be verified: the avionics bus test equipment is required to perform application layer function verification and is provided with a man-machine interaction output interface, an input interface and an avionics bus input and output channel. It can be understood that the specific forms of the output interface and the input interface for the avionic bus test equipment to perform human-computer interaction are different according to different models of the avionic bus test equipment; the output interface is usually an interface such as VGA, HDMI, DVI, etc. for connecting with a display, etc., and the input interface is usually an interface such as PS/2, USB, etc. for connecting with a keyboard, a mouse, etc.

As shown in fig. 3, a computing platform is connected to a first program-controlled interface module in a first remote control module, the computing platform is connected to a second program-controlled interface module in a second remote control module, a first image acquisition module and a first input control module in the first remote control module are respectively connected to a human-computer interaction output interface and an input interface of a standard avionic bus test device, and a second image acquisition module and a second input control module in the second remote control module are respectively connected to a human-computer interaction output interface and an input interface of an avionic bus test device to be verified. The first main control module and the second main control module are respectively connected with the first program control interface module and the second program control interface module; the first main control module and the second main control module are respectively connected with the first parameter analysis module and the second parameter analysis module; the first parameter analysis module and the second parameter analysis module are respectively connected with the first image acquisition module and the second image acquisition module, and the first main control module and the second main control module are respectively connected with the first control conversion module and the second control conversion module; the first control conversion module and the second control conversion module are respectively connected with the first input control module and the second input control module. An avionic bus input channel Rx of the standard avionic bus test equipment is connected with an avionic bus output channel Tx of the avionic bus test equipment to be verified through a first avionic bus connecting cable 1, and the avionic bus output channel Tx of the standard avionic bus test equipment is connected with the avionic bus input channel Rx of the avionic bus test equipment to be verified through a second avionic bus connecting cable 2.

The application layer verification device of the avionics bus test equipment shown in fig. 3 works according to the following principle:

because the avionic bus output channel Tx/input channel Rx of the standard avionic bus test equipment is connected with the avionic bus input channel Rx/output channel Tx of the avionic bus test equipment to be verified, the standard avionic bus test equipment and the avionic bus test equipment to be verified can mutually receive and transmit avionic bus data. The avionics bus decoding function of the avionics bus test equipment to be verified is realized: the computing platform sends a program-controlled verification instruction to the first remote control module, the program-controlled verification instruction is received by a first program-controlled interface module in the first remote control module and then is transmitted to a first main control module, a verification execution sequence is obtained after the verification execution sequence is analyzed by the first main control module according to the anchor point structure tree, and the verification execution sequence is converted into an input simulation instruction by the first control conversion module, is converted by the first input control module and is transmitted to an input interface of standard avionic bus test equipment, so that the input control of the standard avionic bus test equipment is realized; the first image acquisition module acquires an output image of the standard avionic bus test equipment, the first parameter analysis module receives the image acquired by the first image acquisition module and analyzes the image to obtain avionic bus verification parameters, the avionic bus verification parameters are coded into data packets by the first main control module and then sent to the computing platform, and the computing platform obtains the avionic bus verification parameters of the standard avionic bus test equipment, including original values and corresponding decoded values. Secondly, the computing platform is used for programming the avionic bus test equipment to be verified through the second remote control module and obtaining avionic bus to-be-verified parameters of the avionic bus test equipment to be verified; and then, the computing platform compares the verification parameters with the parameters to be verified to obtain a verification result. The process of verifying the avionics bus coding function of the avionics bus test equipment to be verified is similar to the verification decoding process and is not described in detail herein. And finally, recording a verification result by the computing platform, and continuously repeating the steps to finish the verification work of all avionics bus data.

When the output display device of the standard avionic bus test equipment or the avionic bus test equipment to be verified is independent of the host or is connected with the host through an external interface, the first image acquisition module or the second image acquisition module can be realized through a video acquisition card, an image collector and the like so as to acquire a display image. The display image output by the standard avionic bus test equipment host can be simultaneously output to the display device and the first image acquisition module of the standard avionic bus test equipment host through devices such as a video distribution/switcher, and the display image output by the avionic bus test equipment host to be verified can be simultaneously output to the display device and the second image acquisition module of the standard avionic bus test equipment host. When the output display device of the standard avionic bus test equipment or the avionic bus test equipment to be verified is integrated in the host or is connected with the host through an internal interface, the first image acquisition module or the second 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 standard avionic bus test equipment or the avionic bus test equipment to be verified is independent of the host computer or is connected with the host computer through an external interface, the first input control module or the second input control module can realize the input control of the avionic bus test equipment or the avionic bus test equipment to be verified through an HID (high intensity discharge) converter, a PS/2 converter or other similar modes. The input control device and the first input control module of the standard avionic bus test device can be simultaneously accessed to the standard avionic bus test device host through the HUB, the HUB and other devices, the input control device and the second input control module of the avionic bus test device to be verified can be simultaneously accessed to the avionic bus test device host to be verified, and when remote control is achieved, a tester can also simultaneously control the input of the avionic bus test device or the avionic bus test device to be verified. When the input control device of the standard avionic bus test equipment or the avionic bus test equipment to be verified is integrated in the host or is connected with the host through an internal interface, the first input control module or the second input control module can realize the input control of the standard avionic bus test equipment or the avionic bus test equipment to be verified 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 computing platform, the first remote control module and each module therein, and the second remote control module and each module therein may be implemented by hardware, software, or a combination of hardware and software. 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; 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.

The computing platform may be a commercial shelf product such as a computer, server, embedded development system, or the like.

Hardware and software or combined software and hardware for realizing the computing platform, the first remote control module and each module therein, the second remote control module and each module therein can be independent of standard avionic bus test equipment and avionic bus test equipment to be verified, and can also be combined with the standard avionic bus test equipment or the avionic bus test equipment to be verified.

It can be understood that the hardware, software, or combined software and hardware for implementing the first remote control module and each module therein may be the same as or different from the hardware, software, or combined software and hardware for implementing the second remote control module and each module therein, depending on the specific form of the input/output interface of the standard avionic bus test equipment and the avionic bus test equipment to be verified. It is understood that the implementation of the computing platform, the first remote control module and its internal modules, the second remote control module and its internal modules are implemented in hardware, software or a combination of hardware and software, and are independent of or combined with the standard avionics bus test equipment and/or the avionics bus test equipment to be verified, depending on the specific application of the technical solution and design constraints.

Example three:

FIG. 4 is a block diagram of an application layer authentication apparatus according to the present invention as provided in more detail in FIG. 3; as shown in fig. 4, the apparatus includes: the remote control system comprises a microcomputer, a first remote control module and a second remote control module. The device is applied to the application layer verification method of the avionic bus test equipment.

In this embodiment, a microcomputer is used as a computing platform to perform functions such as scheduling control, parameter data comparison verification, and data storage. Standard avionics bus test equipment, using T1200B, is used to provide avionics bus validation parameters, including raw values and corresponding decoded values, an output interface in VGA form with human-computer interaction and an input interface in PS/2 form, and an avionics bus input-output channel. The avionics bus test equipment to be verified is avionics bus test equipment needing application layer function verification, and comprises an output interface in a human-computer interaction HDMI form, an input interface in a USB form and an avionics bus input and output channel. The first remote control module consists of a VGA acquisition card, a PS/2 simulator, a first controller and a first Ethernet port, and the first controller comprises a first main control module, a first parameter analysis module and a first control conversion module. The system is used for enabling the non-programmable standard avionics bus test equipment T1200B to be remotely controlled by a microcomputer, and realizing control input and acquisition of output information of the standard avionics bus test equipment T1200B. The VGA acquisition card is used for acquiring an output image of the standard avionics bus test equipment T1200B. The first parameter analysis module is used for receiving the image acquired by the VGA acquisition card and analyzing and identifying the image to obtain avionic bus parameter information, including an original value and a corresponding decoded value. The first control conversion module is used for converting the verification execution sequence into an input simulation instruction. The PS/2 simulator comprises a PS/2 simulation chip and a controller thereof, and is used for converting an input simulation instruction into a data instruction form supported by the PS/2 simulation chip and transmitting the data instruction form to a PS/2 input interface of the standard avionic bus test equipment T1200B through the PS/2 simulation chip so as to realize input control on the standard avionic bus test equipment T1200B. The first Ethernet port is used for receiving the program-controlled verification instruction from the microcomputer and sending a data packet encoded with avionics bus parameter information to the microcomputer. The first main control module is used for coding the avionic bus parameter information obtained by the first parameter analysis module into a data packet which can be processed by the microcomputer and analyzing the program-controlled verification instruction into a verification execution sequence, and the verification execution sequence internally comprises an anchor point structure tree corresponding to the standard avionic bus test equipment T1200B. The first controller is an embedded development platform based on an ARM framework, and is connected with the VGA acquisition card, the PS/2 simulator and the first Ethernet port. The second remote control module consists of an HDMI acquisition card, an HID simulator, a second controller and a second Ethernet port, and the second controller comprises a second main control module, a second parameter analysis module and a second control conversion module. The method is used for enabling the non-programmable avionics bus test equipment to be verified to be remotely controlled by the microcomputer, and realizing control input and acquisition of output information of the avionics bus test equipment to be verified. The HDMI acquisition card is used for acquiring an output image of the avionics bus test equipment to be verified. The second parameter analysis module is used for receiving the image acquired by the HDMI acquisition card and analyzing and identifying the image to obtain avionic bus parameter information, wherein the avionic bus parameter information comprises an original value and a corresponding decoded value. The second control conversion module is used for converting the verification execution sequence into the input simulation instruction. The HID simulator comprises an HID simulation chip and a controller thereof, and is used for converting an input simulation instruction into a data instruction form supported by the HID simulation chip and transmitting the data instruction form to a USB input interface of the avionic bus test equipment to be verified through the HID simulation chip so as to realize input control of the avionic bus test equipment to be verified. The second Ethernet interface is used for receiving the program-controlled verification instruction from the microcomputer and sending a data packet encoded with avionics bus parameter information to the microcomputer. The second main control module is used for coding the avionic bus parameter information obtained by the second parameter analysis module into a data packet which can be processed by the microcomputer and analyzing the program-controlled verification instruction into a verification execution sequence, and the verification execution sequence comprises an anchor point structure tree corresponding to the avionic bus test equipment to be verified. The second controller is a development platform based on an FPGA framework and is connected with the HDMI acquisition card, the HID simulator and the second Ethernet port.

The microcomputer is connected with a first Ethernet port in the first remote control module, the microcomputer is connected with a second Ethernet port in the second remote control module, the VGA acquisition card and the PS/2 simulator in the first remote control module are respectively connected with a human-computer interaction VGA output interface and a PS/2 input interface of standard avionic bus test equipment T1200, and the HDMI acquisition card and the HID simulator in the second remote control module are respectively connected with a human-computer interaction HDMI output interface and a USB input interface of the avionic bus test equipment to be verified. The first main control module and the second main control module are respectively connected with the first Ethernet port and the second Ethernet port; the first main control module and the second main control module are respectively connected with the first parameter analysis module and the second parameter analysis module; the first parameter analysis module and the second parameter analysis module are respectively connected with the VGA acquisition card and the HDMI acquisition card, and the first main control module and the second main control module are respectively connected with the first control conversion module and the second control conversion module; the first control conversion module and the second control conversion module are respectively connected with the PS/2 simulator and the HID simulator. The avionics bus input channel Rx of the standard avionics bus test equipment T1200B is connected with the avionics bus output channel Tx of the avionics bus test equipment to be verified through a first avionics bus connecting cable 1, and the avionics bus output channel Tx of the standard avionics bus test equipment T1200B is connected with the avionics bus input channel Rx of the avionics bus test equipment to be verified through a second avionics bus connecting cable 2.

Example four:

referring to fig. 5, in this embodiment, the application layer verification apparatus shown in fig. 5 further includes an avionics bus verification parameter database; the avionics bus verification parameter database is stored in a memory, and the memory is connected with the computing platform. The device is applied to the application layer verification method of the second avionic bus test equipment provided by the invention. The avionics bus verification parameter database can be constructed by a computing platform, a first remote control module and standard avionics bus test equipment. The avionics bus verification parameter database can be used as an object for acquiring avionics bus verification parameters, so as to replace acquiring avionics bus verification parameters through standard avionics bus test equipment. The computing platform controls the standard avionic bus test equipment through the first remote control module and obtains output parameters of the standard avionic bus test equipment, so that an avionic bus verification parameter database is constructed. And the computing platform is combined with the avionic bus verification parameter database, and the application layer function verification of the avionic bus test equipment to be verified is realized through the second remote control module. In this embodiment, except that the standard avionics bus test equipment is required when the avionics bus verification parameter database is constructed for the first time, the standard avionics bus test equipment is not relied on any more in the subsequent verification. The avionics bus verification parameter database can be stored in the computing platform or can be independently stored in an external memory.

Example five:

referring to fig. 6, fig. 6 is an application layer verification apparatus of yet another avionics bus test device provided by the invention. When the avionic bus test equipment to be verified can deploy the third-party application module, the application layer function verification of the avionic bus test equipment to be verified can be realized on the basis of the hardware platform of the avionic bus test equipment to be verified. The application layer verification device of the avionics bus test equipment shown in fig. 6 comprises a computing platform, a first remote control module, an avionics bus verification parameter database, a verification program set and a second remote control module. The device is applied to the application layer verification method of the second avionic bus test equipment provided by the invention.

The second remote control module, the verification program set and the avionic bus verification parameter database which are sequentially connected are installed in the avionic bus test equipment to be verified, and the second remote control module is connected to a main program of the avionic bus test equipment to be verified; the computing platform is connected with a first remote control module, and the first remote control module is connected with an output interface and an input interface of the standard avionic bus test equipment; the computing platform is connected to an avionics bus verification parameter database in the avionics bus test equipment to be verified. A computing platform of the device controls standard avionic bus test equipment and obtains output parameters of the standard avionic bus test equipment through a first remote control module, so that an avionic bus verification parameter database is constructed. The avionics bus verification parameter database is stored on avionics bus test equipment to be verified. A main program of the avionics bus test equipment to be verified is provided with a human-computer interaction interface, and the interface is provided with a plurality of display controls and input controls. The second remote control module realizes the collection of a display control on a human-computer interaction interface, identifies parameters on the display control and obtains avionic bus parameter information; and keyboard and mouse instructions which can be recognized by a hardware platform of the avionic bus test equipment can be sent to simulate the operation of a keyboard and a mouse, so that the control of an input control on a human-computer interaction interface is realized. The verification program set can read avionic bus verification parameters in the avionic bus verification parameter database, control input of the avionic bus test equipment to be verified and acquisition of the avionic bus parameters to be verified are realized through the second remote control module, scheduling control, verification parameter data comparison and data storage are completed, and then the application layer functions of the avionic bus test equipment are verified. In this embodiment, the verification program set, the second remote control module, and the avionics bus verification parameter database are implemented in combination with the avionics bus test equipment to be verified.

Claims

1. The method for verifying the application layer of the avionic bus test equipment is characterized by realizing the automatic verification of the application layer function of the avionic bus test equipment to be verified by controlling standard avionic bus test equipment, and comprises the following specific steps of:

firstly, connecting an avionic bus input channel and an avionic bus output channel of standard avionic bus test equipment with an avionic bus output channel and an avionic bus input channel of avionic bus test equipment to be verified;

comparing the verification parameters with the parameters to be verified to obtain verification results;

fourthly, recording a verification result;

2. The method for verifying the application layer of the avionic bus test equipment according to claim 1, wherein the standard avionic bus test equipment is controlled to send verification avionic bus data to the avionic bus test equipment to be verified, and the method comprises the following steps:

(1) sending a program control verification instruction;

converting the input simulation instruction into a data instruction form supported by interface driving equipment, and transmitting the data instruction form to standard aviation bus testing equipment through the interface driving equipment;

the method for controlling the avionics bus test equipment to be verified to send verification avionics bus data to the standard avionics bus test equipment comprises the following steps:

(1) sending a program control verification instruction;

converting the input simulation instruction into a data instruction form supported by interface driving equipment, and transmitting the data instruction form to the aviation bus test equipment to be verified through the interface driving equipment;

the method for acquiring the avionics bus verification parameters of the standard avionics bus test equipment comprises the following steps of: (1) acquiring a display image of standard avionic bus test equipment; (2) analyzing the image to obtain an avionic bus verification parameter;

the method for acquiring the avionics bus to-be-verified parameters of the avionics bus test equipment to be verified comprises an original value and a corresponding decoded value, and comprises the following steps of: (1) acquiring a display image of the avionic bus test equipment to be verified; (2) and analyzing the image to obtain the parameter to be verified of the avionic bus.

3. The method for verifying the application layer of the avionic bus test equipment according to claim 2, wherein the step of converting the programmed verification instruction into a verification execution sequence comprises the following steps:

4. An application layer verification method of avionic bus test equipment is characterized in that an avionic bus verification parameter database is constructed by controlling standard avionic bus test equipment, and automatic verification of application layer functions of the avionic bus test equipment to be verified is realized through the avionic bus verification parameter database, and the method specifically comprises the following steps:

changing verification avionic bus data, repeating the step (I), the step (II) and the step (III), and constructing an avionic bus verification parameter database;

thirdly, comparing the verification parameters with the parameters to be verified to obtain a verification result;

fourthly, recording a verification result;

5. The application layer verification method of an avionics bus test equipment according to claim 4, characterized in that the decoded values comprise parameter names of the decoded values and parameter values of the decoded values;

the avionic bus verification parameter database stores original values of avionic bus data and corresponding decoded values, and is realized by adopting a tree structure, a plurality of original value nodes are arranged below a root node, a plurality of parameter information nodes are arranged below each original value node, and each parameter information node comprises a parameter name of a decoded value and a parameter value of the decoded value.

6. An application layer verification device of avionics bus test equipment, the device comprising: the system comprises a computing platform, a first remote control module and a second remote control module, wherein the computing platform is used for finishing functions of scheduling control, parameter data comparison verification and data storage; the first remote control module consists of a first program control interface module, a first main control module, a first parameter analysis module, a first control conversion module, a first image acquisition module and a first input control module; the system is used for realizing control input of standard avionic bus test equipment and acquiring output information of the standard avionic bus test equipment; the second remote control module consists of a second program control interface module, a second main control module, a second parameter analysis module, a second control conversion module, a second image acquisition module and a second input control module; the device is used for realizing control input of avionics bus test equipment to be verified and acquiring output information of the avionics bus test equipment to be verified;

the first main control module and the second main control module are respectively connected with the computing platform through the first program control interface module and the second program control interface module and are used for converting received program control verification instructions into verification execution sequences, encoding avionic bus parameter information into data packets and sending the data packets to the computing platform; the first main control module and the second main control module are respectively connected with the first parameter analysis module and the second parameter analysis module; the first parameter analysis module and the second parameter analysis module are respectively connected with the first image acquisition module and the second image acquisition module and are used for receiving the images acquired by the image acquisition modules and analyzing and identifying the images; the first main control module and the second main control module are respectively connected with the first control conversion module and the second control conversion module; the first control conversion module and the second control conversion module are respectively connected with the first input control module and the second input control module and are used for converting the verification execution sequence into an input simulation instruction and transmitting the input simulation instruction to the standard avionic bus test equipment;

the first image acquisition module and the first input control module are respectively connected to a man-machine interaction output interface and an input interface of the standard avionic bus test equipment; the second image acquisition module and the second input control module are respectively connected to a human-computer interaction output interface and an input interface of the avionic bus test equipment to be verified.

7. The application layer verification apparatus of an avionics bus test device of claim 6, further comprising an avionics bus verification parameter database; the avionics bus verification parameter database is stored in a memory, and the memory is connected with the computing platform.

8. An application layer verification device of avionics bus test equipment, the device comprising: the system comprises a computing platform, a first remote control module, a second remote control module, a verification program set and an avionic bus verification parameter database, wherein the computing platform is used for finishing functions of scheduling control, verification parameter data comparison and data storage; the second remote control module, the verification program set and the avionic bus verification parameter database which are sequentially connected are installed in the avionic bus test equipment to be verified and are connected to a main program of the avionic bus test equipment to be verified through the second remote control module; the computing platform is connected with a first remote control module, and the first remote control module is connected with an output interface and an input interface of standard avionic bus test equipment; the computing platform is connected to an avionic bus verification parameter database in the avionic bus test equipment to be verified; the computing platform controls the standard avionic bus test equipment through the first remote control module and obtains output parameters of the standard avionic bus test equipment, so that an avionic bus verification parameter database is constructed; the verification program set can read avionic bus verification parameters in the avionic bus verification parameter database, control input of the avionic bus test equipment to be verified and acquisition of the avionic bus parameters to be verified are realized through the second remote control module, scheduling control, verification parameter data comparison and data storage are completed, and then application layer functions of the avionic bus test equipment are verified.