An airborne suspension management function automatic test method and system based on an avionics simulator

Abstract

The present application relates to the technical field of avionics system, and particularly relates to an airborne suspension management function automatic test method and system based on avionics simulator, comprising: configuring test parameters of a suspension simulator of a tested suspension management system; selecting test excitation, suspension and corresponding faults of the suspension; generating excitation commands; controlling the suspension simulated by the suspension simulator, and returning bus data; and obtaining test results. The present application uses a suspension management system test environment based on avionics simulator and suspension simulator, testers can freely input or set instruction parameters of devices on the display control machine / task machine and response behaviors of the mounted suspension, and the devices connected with the suspension management system can be simulated more completely and truly, so that the test has better freedom and authenticity, and can be a good supplement to the avionics ground integration test environment.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of avionics system, in particular to an airborne suspension management function automatic test method and system based on avionics simulator. BACKGROUND

[0002] The suspension management system (SMS in the drawings) is the control core of the airborne suspension system of the aircraft. As an intermediate link for coordinating the suspension and the on-board subsystem, the suspension management system has the most direct effect on the integration and management of the airborne suspension, and has important significance for the aircraft suspension and the control of new suspension.

[0003] The typical functions of the suspension management system include identifying, managing and reporting the suspension list, monitoring and reporting the suspension state, receiving and managing the release program, receiving the control commands and binding parameters of the on-board task equipment for the suspension, and performing power control, position selection, parameter binding, launch control management, fault handling and reporting for the suspension. In the avionics environment, the suspension management system is connected to the avionics management devices such as the display and control and the mission machine, and the connection mode is mainly various high-speed data buses and a small amount of discrete signals. According to the main / auxiliary power interface signal group and the data bus specified in GJB1188A "Interface Requirements for Aircraft / Suspension Electrical Connection System", the suspension management system is connected to various standard suspensions, and is connected to non-standard suspensions through specific electrical interfaces and buses.

[0004] The traditional avionics ground test environment can connect the situation assessment, task management, suspension control and other systems in series to form a ground test environment based on the cockpit. Since this test environment involves many devices, if only the airborne suspension control process of the suspension management system is tested, the avionics task equipment / suspension simulator can be designed around the suspension management system for testing, that is, only the simulator is used to simulate the various on-board task equipment (display and control, mission machine, power system, landing gear, etc.) connected to the suspension management system, and to simulate various suspensions managed by the suspension management system. The discrete quantities and various data buses connected to the suspension management system provide test excitation and collect measured output to complete the test of the suspension management system. Figure 2 The connection mode of this test environment is shown. However, the execution of this test environment still depends on the manual operation of the tester, and cannot be automatically tested, which limits the efficiency and completeness of the test.

[0005] Therefore, it is necessary to provide an airborne suspension management function automatic test method and system based on avionics simulator to solve the above problems. SUMMARY

[0006] The application provides an airborne suspension management function automatic test method and system based on an avionics simulator, to solve the problem that the execution of the existing test environment still relies on the manual operation of testers, and automatic testing cannot be achieved, which limits the efficiency and completeness of the test.

[0007] The airborne suspension management function automatic test method based on the avionics simulator adopts the following technical scheme, comprising:

[0008] The test parameters of the suspension simulator of the tested suspension management system are configured, which include: the suspension type simulated by the suspension simulator, the suspension type corresponding to each hanging point, the preset test excitation of various suspensions simulated by the suspension simulator, and the suspension fault simulated by the suspension simulator;

[0009] The suspension type simulated by the suspension simulator, the preset test excitation, and the simulated suspension fault are selected from the configured parameters;

[0010] The excitation command is generated according to the preset test excitation, and the excitation command is sent to the avionics simulator, wherein the excitation command includes: the discrete quantity command agreed with the avionics simulator in advance, and the bus data consistent with the communication bus interface control file of the avionics simulator and the suspension management system;

[0011] If the avionics simulator receives the discrete quantity command, the format is parsed according to the pre-agreed format, and the corresponding discrete quantity is sent to the suspension management system; if the avionics simulator receives the bus data, the bus data is forwarded to the suspension management system according to the message specified in the communication bus interface header;

[0012] The suspension management system controls the suspension simulated by the suspension simulator according to the bus data and the discrete quantity, and the suspension management system transmits the bus data back to the avionics simulator;

[0013] The bus interface data is converted into test results, and the test results of each suspension corresponding to each test excitation are displayed in the form of a master / slave table.

[0014] Preferably, each row in the master table is a test excitation row, and each test excitation row has a slave table, and the test result rows of the suspensions corresponding to the test excitation in the slave table.

[0015] Preferably, the content of the test excitation row includes: whether to execute, operation range, operation step, operation value, and total test result.

[0016] Preferably, the content of the test result row includes: response object, hanging point, operation response, expected result, timeout time, and test result.

[0017] Preferably, the test excitation comprises: start-up self-checking of the measured suspension management system, suspension power-on simulated by the suspension simulator, suspension alignment simulated by the suspension simulator, and hatch opening; and the test result is: self-checking result of the measured suspension management system is normal / failure, suspension power-on simulated by the suspension simulator is identified as success / failure, suspension alignment simulated by the suspension simulator is success / failure, and hatch opening is success / failure.

[0018] Preferably, whether the content of the bus data returned by the suspension management system changes is judged, and if the content changes, the test result is obtained according to the data meaning parsed by the built-in interface control file.

[0019] An airborne suspension management function automatic test system based on an avionics simulator, comprising:

[0020] A parameter configuration module is configured to configure test parameters of a suspension simulator of a measured suspension management system, which comprises: configuring a suspension type simulated by the suspension simulator, a suspension type corresponding to each hanging point, preset test excitation of various suspensions simulated by the suspension simulator, and suspension faults simulated by the suspension simulator.

[0021] An excitation selection module is configured to select the suspension type simulated by the suspension simulator, the preset test excitation, and the simulated suspension faults from the configured parameters.

[0022] An excitation module is configured to generate an excitation command according to the preset test excitation, and send the excitation command to the avionics simulator, wherein the excitation command comprises: a discrete quantity command agreed with the avionics simulator in advance, and bus data consistent with a communication bus interface control file of the avionics simulator and the suspension management system.

[0023] A test module is configured to, if the avionics simulator receives the discrete quantity command, parse according to a format agreed in advance, and send corresponding discrete quantities to the suspension management system; and if the avionics simulator receives the bus data, forward the bus data to the suspension management system as is according to a message specified in a communication bus interface header, and the suspension management system controls the suspension simulated by the suspension simulator according to the bus data and the discrete quantities, while the suspension management system returns bus data to the avionics simulator.

[0024] A test result module is configured to convert the bus interface data into test results, and display the test results of each suspension under each test excitation in a master / slave table form.

[0025] The present application has the following beneficial effects:

[0026] By using the suspension management system test environment based on the avionics simulator and the suspension simulator, the tester can freely input or set the instruction parameters of the device on the display and control machine / task machine and the response behavior of the mounted suspension, and the device connected with the suspension management system can be simulated more completely and truly, so that the test has better freedom and authenticity, and can be a good supplement to the avionics ground integration test environment. BRIEF DESCRIPTION OF DRAWINGS

[0027] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0028] Figure 1 A flow chart of an airborne suspension management function automatic test method based on an avionics simulator according to the present application;

[0029] Figure 2 A schematic diagram of the cross-linking relationship between the measured suspension management system and the ground laboratory test environment according to the present application;

[0030] Figure 3 A schematic diagram of the cross-linking relationship between the avionics task simulator, the measured suspension management system and the suspension simulator for automatic test according to the present application;

[0031] Figure 4 A specific execution flow chart of the automatic test management method according to the present application;

[0032] Figure 5 A software interaction interface example diagram of the test excitation and test results based on the "master / slave table" form according to the present application. DETAILED DESCRIPTION

[0033] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some embodiments of the present application, not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0034] An embodiment of an airborne suspension management function automatic test method based on an avionics simulator according to the present application, as shown in Figure 1 , comprises:

[0035] S1, configure the test parameters of the suspension simulator of the measured suspension management system:

[0036] Specifically, the embodiment stores the test parameters to be configured into a computer disk file, wherein the test parameters to be configured include: 1, a set of suspension types allowed to be simulated by the suspension simulator; 2, the suspension types set for each hanging point; 3, test excitation and test results performed on various suspensions simulated by the suspension simulator; and 4, faults set for various suspensions simulated by the suspension simulator.

[0037] Wherein, the test excitation includes (but is not limited to, which is exemplified here): start-up self-check of the suspension management system under test, power-on of the suspension simulated by the suspension simulator, alignment of the suspension simulated by the suspension simulator, and opening of the hatch; and the test results are: self-check result of the suspension management system under test is normal / failure, power-on identification of the suspension simulated by the suspension simulator is successful / failure, alignment of the suspension simulated by the suspension simulator is successful / failure, and opening of the hatch is successful / failure.

[0038] Wherein, for the test excitation and test results performed on various suspensions simulated by the suspension simulator: the implementation of the airborne suspension control function depends on a series of sequential operations, for example, operation 1 is performed on the suspension management system, then operation 2 is performed on various suspensions; operation 1 is successfully performed on a certain suspension, then operation 2 and 3 are performed.

[0039] S2, selecting test excitation, suspension, and fault corresponding to the suspension;

[0040] Specifically, the suspension type simulated by the suspension simulator of the suspension management system under test, the preset test excitation, and the simulated suspension fault are selected from the configured parameters.

[0041] S3, generating an excitation command;

[0042] Specifically, the excitation command is generated according to the preset test excitation, and the excitation command is sent to the avionics simulator, wherein after the excitation command is generated, the excitation command is sent to the avionics simulator through an Ethernet socket interface.

[0043] Wherein, the excitation command includes: discrete quantity command and bus data; the format of the discrete quantity command is automatically agreed upon by the test program and the avionics simulator, and after receiving the discrete quantity command, the avionics simulator outputs a discrete voltage command to the suspension management system; the data format of the bus data is completely consistent with the bus interface control file for communication between the avionics simulator and the suspension management system, and after receiving the bus message, the avionics simulator forwards the bus data to the suspension management system.

[0044] Wherein, the test excitation message between the avionics simulator should be agreed upon as shown in Table 1.

[0045] Table 1

[0046]

[0047] S4, control the suspension simulated by the suspension simulator, and return the bus data;

[0048] Specifically, if the avionics simulator receives a discrete command, the avionics simulator parses the discrete command according to a pre-agreed format and sends a corresponding discrete command to the suspension management system; if the avionics simulator receives bus data, the avionics simulator forwards the bus data to the suspension management system according to a message specified in a communication bus interface header; the suspension management system controls the suspension simulated by the suspension simulator according to the bus data and the discrete command, and the suspension management system returns the bus data to the avionics simulator.

[0049] The suspension management system sends the received bus data or discrete command to the suspension simulator to control the suspension simulator, i.e., to simulate the suspension in a manner specified by the data content, and the specific process is shown in Table 2.

[0050]

[0051] S5, obtain a test result;

[0052] The bus data returned by the suspension management system to the avionics simulator is converted into a test result, and the test result corresponding to each suspension under each test stimulus is displayed in the form of a master / slave table.

[0053] The test case based on the master / slave table: the steps of displaying the test result corresponding to each suspension under each test stimulus in the form of a master / slave table are as follows: in each test, each row in the master table is a test stimulus row, and each test stimulus row has a slave table, and the slave table has multiple suspension test result rows corresponding to the test stimulus (i.e., one test stimulus row operation can correspond to multiple suspension test results), and these test results are displayed as the slave table of the stimulus row and can be expanded or folded by the editor on the software interaction interface. Each stimulus row should include whether to execute, operation range, operation steps, operation value, and total test result (total operation result, which is the summary of all results in the slave table, correct or incorrect); each result row should include a response object (in this embodiment, a suspension), a hanging point, an operation response, an expected result, a timeout time, and a test result (a single test result of the suspension).

[0054] It should be noted that the test result item is filled after the automatic test execution, and other items need to be edited by the tester in advance. Specifically, when editing the excitation row, if the "operation range" element has been selected, when the "operation step" element is selected, the interface prompts which "operation step" element can be selected according to the value of the "operation range"; if the "operation step" element has been selected, when the "operation value" element is selected, the interface prompts which "operation value" element can be selected according to the value of the "test". Similarly, when the tester edits the result row, if the "response object" element has been selected, when the "operation response" and "expected result" elements are selected, the interface prompts which "test result" and "expected result" elements can be selected according to the value of the "operation step" element of the excitation row and the "response object" of the result row, and the "timeout time" value is automatically filled after the "test result" is determined.

[0055] As shown in Figure 5 the lower left corner specifies the 1 / 2 / 3 hanging point to be simulated, and the upper right corner is a test table based on a master-slave table form. In the first test excitation row of the test table, the operation range is "the measured suspension management system (SMS)", the operation step is "the measured suspension management system starts", and the operation value is "on" (signal valid). After the excitation is issued, the measured suspension management system should reply to the start of the bus message within 10 seconds, which is forwarded and judged by the avionics simulator, and "pass" is displayed in the "test result" column of the "detailed result" slave table, and "pass" is also displayed in the "total test result" column of the test excitation row. In the second test excitation row, the operation range is "the measured suspension management system", the operation step is "turn on the suspension total power supply", and the operation value is "on" (signal valid). After the excitation is issued, the measured suspension management system should report the identification results of wpn1 / 2 and the report of the suspension total power supply switch state collected by the measured suspension management system within the specified timeout time according to the different timeout times defined by each result row.

[0056] The following is based on the Extensible Markup Language (XML) form to explain the configuration of the test parameters. Specifically, an example of the test parameter configuration is as follows:

[0057] <?xml version="1.0" encoding="utf-8"?>

[0058] <testconfig name="测试配置表">

[0059] <sta_name_list>

[0060] None

[0061] demo_wpn1

[0062] demo_wpn2

[0063] < / sta_name_list>

[0064] <sta_allow_list>

[0065] <sta 挂点="1">

[0066] <type>demo_wpn1< / type>

[0067] < / sta>

[0068] <sta 挂点="2">

[0069] <type>demo_wpn2< / type>

[0070] < / sta>

[0071] <sta 挂点="3">

[0072] <type>demo_wpn1< / type>

[0073] <type>demo_wpn2< / type>

[0074] < / sta>

[0075] <sta 挂点="4">

[0076] <type>demo_wpn1< / type>

[0077] <type>demo_wpn2< / type>

[0078] < / sta>

[0079] < / sta_allow_list>

[0080] <oper_option>

[0081] <sms>

[0082] <operation name="-">< / operation>

[0083] <operation name="SMS start" overtime="10">< / operation>

[0084] <operation name="landing gear" overtime="0.5">

[0085] <result oper_val="收起">Fold< / result>

[0086] <result oper_val="放下">Drop< / result>

[0087] < / operation>

[0088] <operation name="real / training" overtime="0.5">

[0089] <result oper_val="真实">Real< / result>

[0090] <result oper_val="训练">Train< / result>

[0091] < / operation>

[0092] <operation name="suspended total power" overtime="0.5">< / operation>

[0093] <operation name="Pickle" overtime="2">< / operation>

[0094] <operation name="emergency jettison" overtime="0.5">< / operation>

[0095] <operation name="placeholder" overtime="0.5">< / operation>

[0096] <operation name="work main mode" overtime="3">

[0097] <result oper_val="正常">Normal< / result>

[0098] <result oper_val="维护">Maintenance< / result>

[0099] <result oper_val="启动自检测">Self-check OK< / result>

[0100] <result oper_val="启动自检测">Self-check failed< / result>

[0101] < / operation>

[0102] <operation name="avionics main mode" overtime="0.5">

[0103] <result oper_val="格斗">Fight< / result>

[0104] <result oper_val="拦截">Intercept< / result>

[0105] <result oper_val="空面">Empty surface< / result>

[0106] <result oper_val="导航">Navigation< / result>

[0107] < / operation>

[0108] <operation name="autoload" overtime="0.5">< / operation>

[0109] <operation name="manifest request" overtime="0.5">< / operation>

[0110] <operation name="main suspension selection" overtime="0.5">

[0111] <result oper_val="demo_wpn1">WPN1< / result>

[0112] <result oper_val="demo_wpn2">WPN2< / result>

[0113] < / operation>

[0114] <operation name="wheel load">

[0115] <result oper_val="空中">Air< / result>

[0116] <result oper_val="地面">Ground< / result>

[0117] < / operation>

[0118] < / sms>

[0119] <weapon name="demo_wpn1">

[0120] <Subtype>Real< / Subtype>

[0121] <Subtype>Training< / Subtype>

[0122] <Fault>Failure 1< / Fault>

[0123] <Fault>Failure 2< / Fault>

[0124] <Fault>Failure 3< / Fault>

[0125] <Operation name="-">

[0126] < / Operation>

[0127] <Operation name="Identification" overtime="10">

[0128] <result>Present< / result>

[0129] <result>Absent< / result>

[0130] < / Operation>

[0131] <Operation name="Operation 1" overtime="10">

[0132] <result>Result 1a< / result>

[0133] <result>Result 1b< / result>

[0134] < / Operation>

[0135] <Operation name="Operation 2" overtime="195">

[0136] <result>Result 2a< / result>

[0137] <result>Result 2b< / result>

[0138] < / Operation>

[0139] <Operation name="Operation 3" overtime="4">

[0140] <result>Result 3a< / result>

[0141] <result>Result 3b< / result>

[0142] < / Operation>

[0143] < / weapon>

[0144] <weapon name="demo_wpn2">

[0145] <Subtype>Real< / Subtype>

[0146] <Subtype>Train< / Subtype>

[0147] <Fault>None< / Fault>

[0148] <Fault>Failure 1< / Fault>

[0149] <Fault>Failure 2< / Fault>

[0150] <Operation name="-">

[0151] < / Operation>

[0152] <Operation name="Identify" overtime="10">

[0153] <result>Present< / result>

[0154] <result>Absent< / result>

[0155] < / Operation>

[0156] <Operation name="Select" overtime="0.5">

[0157] <result>Selected< / result>

[0158] <result>Not selected< / result>

[0159] < / Operation>

[0160] <Operation name="Fire" overtime="3.5">

[0161] <result>Launched< / result>

[0162] <result>Launch failed< / result>

[0163] < / Operation>

[0164] < / weapon>

[0165] < / oper_option>

[0166] < / testconfig> .

[0167] The above only describes the preferred embodiments of the present application and is not used to limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application should be included in the protection scope of the present application.

Claims

1. An automatic test method for airborne stores management function based on avionics simulator, characterized in that, The method comprises the following steps: configuring test parameters of a suspension simulator of a measured suspension management system, which comprises: configuring a suspension type simulated by the suspension simulator, a suspension type corresponding to each hanging point, preset test excitation of various suspensions simulated by the suspension simulator, and a suspension fault simulated by the suspension simulator; selecting the suspension type simulated by the suspension simulator, the preset test excitation, and the simulated suspension fault from the configured parameters; generating an excitation command according to the preset test excitation, and sending the excitation command to an avionics simulator, wherein the excitation command comprises: discrete quantity commands agreed with the avionics simulator in advance, and bus data consistent with a communication bus interface control file of the avionics simulator and the suspension management system; if the avionics simulator receives the discrete quantity commands, the avionics simulator parses the discrete quantity commands according to a format agreed in advance, and sends corresponding discrete quantities to the suspension management system; if the avionics simulator receives the bus data, the avionics simulator forwards the bus data to the suspension management system as they are according to a message specified in a communication bus interface header; the suspension management system controls the suspensions simulated by the suspension simulator according to the bus data and the discrete quantities, and the suspension management system feeds back bus data to the avionics simulator; converting the bus interface data into test results, and displaying the test results of each suspension corresponding to each test excitation in a form of a master / slave table; wherein each row in the master table is a test excitation row, each test excitation row has a slave table, the test results of the suspensions corresponding to the test excitation in the slave table, and the content of the test excitation row comprises: whether to execute, an operation range, an operation step, an operation value, and a total test result; the content of the test result row comprises: a response object, a hanging point, an operation response, an expected result, a timeout time, and a test result; the test excitation comprises: a start self-check of the measured suspension management system, power-on of the suspensions simulated by the suspension simulator, alignment of the suspensions simulated by the suspension simulator, and opening of a hatch; and the test result is: a self-check result of the measured suspension management system is normal / failure, power-on identification of the suspensions simulated by the suspension simulator is successful / failure, alignment of the suspensions simulated by the suspension simulator is successful / failure, and opening of the hatch is successful / failure.

2. The method of claim 1, wherein the method further comprises: judging whether the content of the bus data fed back by the suspension management system changes, and obtaining the test result according to the data meaning parsed according to the built-in interface control file if the content changes.

3. An automatic test system for avionics simulator based airborne suspension management function, characterized in that, The method comprises the following steps: a parameter configuration module is configured to configure test parameters of a suspension simulator of a measured suspension management system, which comprises: configuring a suspension type simulated by the suspension simulator, a suspension type corresponding to each hanging point, preset test excitation of various suspensions simulated by the suspension simulator, and a suspension fault simulated by the suspension simulator; an excitation selection module is configured to select the suspension type simulated by the suspension simulator, the preset test excitation, and the simulated suspension fault from the configured parameters; The excitation module is configured to generate excitation commands according to preset test excitations, and send the excitation commands to the avionics simulator, wherein the excitation commands include discrete quantity commands agreed with the avionics simulator in advance, and bus data consistent with a communication bus interface control file of the avionics simulator and the suspension management system; The test module is configured to, if the avionics simulator receives the discrete quantity commands, parse the discrete quantity commands according to a format agreed in advance, and send corresponding discrete quantities to the suspension management system; if the avionics simulator receives the bus data, forward the bus data to the suspension management system as is according to a message specified in a communication bus interface header, and the suspension management system controls the suspension simulated by the suspension simulator according to the bus data and the discrete quantities, while the suspension management system returns bus data to the avionics simulator; The test result module is configured to convert the bus interface data into test results, and display the test results of each suspension corresponding to each test excitation in a "master / slave table" form. Each row in the master table is a test excitation row, each test excitation row has a slave table, and the test results of the suspension corresponding to the test excitation in the slave table. The content of the test excitation row includes whether to execute, an operation range, an operation step, an operation value, and a total test result. The content of the test result row includes a response object, a hanging point, an operation response, an expected result, a timeout time, and a test result. The test excitation includes a startup self-check of the tested suspension management system, power-on of the suspension simulated by the suspension simulator, alignment of the suspension simulated by the suspension simulator, and opening of a hatch. The test result is that the self-check result of the tested suspension management system is normal / failure, power-on identification of the suspension simulated by the suspension simulator is successful / failure, alignment of the suspension simulated by the suspension simulator is successful / failure, and opening of the hatch is successful / failure.

Images