Airborne suspension management function automatic test method and system based on avionic simulator

Abstract

The invention relates to the technical field of avionics systems, in particular to an airborne suspension management function automatic test method and system based on an avionics simulator, and the method comprises the steps: configuring test parameters of a suspension simulator of a tested suspension management system; selecting a test excitation, a suspension object and a fault corresponding to the suspension object; generating an excitation command; controlling the suspender simulated by the suspender simulator, and returning bus data; and obtaining a test result. According to the invention, a suspender management system test environment based on the avionics simulator and the suspender simulator is used, so that a tester can freely input or set instruction parameters of equipment on the display control machine / task machine and response behaviors of suspender mounting, and equipment cross-linked with the suspender management system can be simulated relatively completely and truly; therefore, the test has good degree of freedom and trueness, and can be used as a good supplement for an avionics ground integrated test environment.

Description

Technical Field

[0001] The present invention relates to the technical field of avionics systems, and in particular to an automatic testing method and system for an airborne suspended object management function based on an avionics simulator. Background Art

[0002] The Store Management System (SMS in the attached figure) is the control core of the aircraft's onboard store system. As the intermediate link between store and onboard subsystems, the Store Management System has the most direct effect on the integration and management of onboard store, and is of great significance to the addition and control of new store to aircraft.

[0003] The typical functions of the suspension management system are to identify, manage and report the list of suspensions; monitor and report the status of suspensions; receive and manage the delivery program; receive the control commands and binding parameters of the suspensions from the mission equipment on the aircraft, and perform power supply control, position selection, parameter binding, control management, fault handling and reporting on the suspensions. In the avionics environment, the suspension management system is interconnected with avionics management equipment such as display and control, mission aircraft, etc., and the interconnection method is mainly various high-speed data buses and a small number of discrete signals; it is interconnected with various types of standard-compliant suspensions according to the main / auxiliary power interface signal group and data bus specified in GJB1188A "Aircraft / Suspension Electrical Connection System Interface Requirements", and is interconnected with non-standard-compliant suspensions through specific electrical interfaces and buses.

[0004] The traditional avionics ground test environment can connect various systems such as situation assessment, mission management, and suspension control in series to form a cockpit-based ground test environment. Since this test environment involves many devices, if only the onboard suspension control process of the suspension management system is tested, an avionics mission equipment / suspension simulator can be designed around the suspension management system for testing. That is, only the simulator is used to simulate the various onboard mission equipment (display control, mission machine, power system, landing gear, etc.) interconnected with the suspension management system, and at the same time simulate the various types of suspensions managed by the suspension management system. The test stimulus is provided through the discrete quantities and various data buses interconnected with the suspension management system, and the output under test is collected to complete the test of the suspension management system. Figure 2 The cross-linking mode of this test environment is shown. However, the execution of this test environment still relies on the manual operation of the tester, and automatic testing cannot be achieved, which limits the efficiency and completeness of the test.

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

[0006] The present invention provides an automatic test method and system for an airborne suspension management function based on an avionics simulator, so as to solve the problem that the execution of the existing test environment still relies on the manual operation of the tester, and automatic testing cannot be achieved, thus limiting the efficiency and completeness of the test.

[0007] The present invention discloses an automatic test method for an airborne suspended object management function based on an avionics simulator, which adopts the following technical scheme, including: Configuring the test parameters of the suspension simulator of the tested suspension management system, including: configuring the type of suspension simulated by the suspension simulator, the type of suspension corresponding to each hanging point, the preset test excitation of various suspensions simulated by the suspension simulator, and various suspension faults simulated by the suspension simulator; Select the type of suspension to be simulated by the suspension simulator, the preset test stimulus, and the simulated suspension fault from the configured parameters; Generate an excitation command according to a preset test excitation, and send the excitation command to the avionics simulator, wherein the excitation command includes: a discrete quantity command agreed in advance with the avionics simulator, and bus data consistent with a communication bus interface control file between the avionics simulator and the suspension management system; If the avionics simulator receives a discrete quantity command, it will parse it according to the pre-agreed format and send the corresponding discrete quantity to the suspension management system; if the avionics simulator receives bus data, it will forward it to the suspension management system as is according to the message specified in the communication bus interface packet header; The suspension management system controls the suspension simulated by the suspension simulator according to the bus data and discrete quantities, and at the same time, the suspension management system transmits the bus data back to the avionics simulator; The bus interface data is converted into test results, and the test results corresponding to each suspended object under each test stimulus are displayed in the form of a "master / slave table".

[0008] Preferably, each row in the main table is a test stimulus row, and each test stimulus row has a slave table, and the slave table has a test result row corresponding to the suspended object under the test stimulus.

[0009] Preferably, the content of the test stimulus line includes: whether to execute, operation range, operation steps, operation value, and total test result.

[0010] Preferably, the content of the test result row includes: response object, hanging point, operation response, expected result, timeout period, and test result.

[0011] Preferably, the test stimulus includes: startup self-test of the tested suspension management system, power-on of the suspension simulated by the suspension simulator, suspension alignment and cabin opening simulated by the suspension simulator; the test results are: self-test result of the tested suspension management system is normal / failed, power-on identification of the suspension simulated by the suspension simulator is successful / failed, suspension alignment simulated by the suspension simulator is successful / failed, and cabin opening is successful / failed.

[0012] Preferably, it is determined whether the content of the bus data returned by the hanging object management system has changed. If the content has changed, the test result is obtained according to the meaning of the data parsed by the built-in interface control file.

[0013] An automatic test system for airborne suspension management function based on an avionics simulator, comprising: A parameter configuration module is used to configure the test parameters of the suspension simulator of the tested suspension management system, including: configuring the type of suspension simulated by the suspension simulator, the type of suspension corresponding to each hanging point, the preset test excitation of various suspensions simulated by the suspension simulator, and various suspension faults simulated by the suspension simulator; An excitation selection module, used to select the type of suspension simulated by the suspension simulator, perform a preset test excitation, and simulate the suspension fault from the configured parameters; The stimulus module is used to generate a stimulus command according to a preset test stimulus and send the stimulus command to the avionics simulator, wherein the stimulus command includes: a discrete quantity command agreed in advance with the avionics simulator, and bus data consistent with a communication bus interface control file between the avionics simulator and the suspension management system; The test module is used for parsing the discrete quantity command received by the avionics simulator according to the pre-agreed format and sending the corresponding discrete quantity to the suspension management system; if the avionics simulator receives the bus data, it forwards it to the suspension management system as it is according to the message specified in the communication bus interface packet header, and the suspension management system controls the suspension simulated by the suspension simulator according to the bus data and the discrete quantity, and at the same time, the suspension management system returns the bus data to the avionics simulator; The test result module is used to convert the bus interface data into test results and display the test results corresponding to each suspended object under each test stimulus in the form of a "master / slave table".

[0014] The beneficial effects of the present invention are: By using the suspension management system test environment based on avionics simulators and suspension simulators, testers can freely input or set the command parameters of the equipment on the display and control machine / mission aircraft and the response behavior of the mounted suspensions, and can more completely and realistically simulate the equipment interconnected with the suspension management system. Therefore, the test has a good degree of freedom and authenticity, and can serve as a good supplement to the avionics ground integration test environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0016] Figure 1 It is a flow chart of an automatic testing method of an airborne suspension management function based on an avionics simulator of the present invention; Figure 2 It is a schematic diagram of the cross-linking relationship between the tested hanging object management system and the ground test laboratory test environment of the present invention; Figure 3 It is a schematic diagram of the cross-linking relationship for automated testing between the avionics mission simulator, the tested suspension management system, and the suspension simulator of the present invention; Figure 4 It is a specific execution flow chart of the automated test management method of the present invention; Figure 5 This is an example diagram of the software interaction interface of the present invention based on the test stimulus and test result in the form of a "master / slave table". DETAILED DESCRIPTION

[0017] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0018] An embodiment of an automatic test method for an airborne suspension management function based on an avionics simulator of the present invention is as follows: Figure 1 As shown, including: S1. Configure the test parameters of the suspended object simulator of the suspended object management system under test: Specifically, the present embodiment stores the test parameters to be configured in 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 types of suspensions set at each suspension point; 3. test stimuli and test results for various suspensions simulated by the suspension simulator; 4. faults of various suspensions simulated by the suspension simulator; The test stimulus includes (but is not limited to, as illustrated here): the startup self-test of the tested suspension management system, the power-on of the suspension simulated by the suspension simulator, the alignment of the suspension simulated by the suspension simulator, and the opening of the cabin; the test results are: the self-test result of the tested suspension management system is normal / failed, the power-on identification of the suspension simulated by the suspension simulator is successful / failed, the alignment of the suspension simulated by the suspension simulator is successful / failed, and the opening of the cabin is successful / failed.

[0019] Among them, for the test stimuli and test results of various suspensions simulated by the suspension simulator: the realization of the onboard suspension control function depends on a series of sequential operations. For example, after operating the suspension management system 1, various types of suspensions can be operated; after successfully operating 1 on a certain suspension, operations 2 and 3 can be performed.

[0020] S2. Select the test stimulus, the hanging object and the fault corresponding to the hanging object; Specifically, the type of suspended object simulated by the suspended object simulator of the suspended object management system under test, the preset test stimulus and the simulated suspended object fault are selected from the configured parameters.

[0021] S3, generating an incentive command; Specifically, an excitation command is generated according to a preset test excitation, and the excitation command is sent to the avionics simulator. After the excitation command is generated, the excitation command is sent to the avionics simulator through an Ethernet socket interface.

[0022] Among them, the excitation command includes: discrete quantity command and bus data; the format of the discrete quantity command is agreed in advance by the automatic test program and the avionics simulator, and the avionics simulator outputs a discrete quantity voltage command to the suspension management system after receiving the discrete quantity command; 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 the avionics simulator forwards the bus data to the suspension management system after receiving the bus message.

[0023] Among them, the test stimulus message to be agreed upon between the avionics simulator and the avionics simulator is shown in Table 1.

[0024] Table 1

[0025] S4, controlling the suspended object simulated by the suspended object simulator and returning bus data; Specifically, if the avionics simulator receives a discrete quantity command, it will parse it according to the pre-agreed format and send the corresponding discrete quantity to the suspension management system; if the avionics simulator receives bus data, it will forward it to the suspension management system as is according to the message specified in the communication bus interface packet header; the suspension management system controls the suspension simulated by the suspension simulator based on the bus data and discrete quantity, and at the same time the suspension management system returns the bus data to the avionics simulator.

[0026] Among them, the hanging object management system sends the received bus data or discrete quantity to the hanging object simulator to control the hanging object simulator, that is, to simulate the hanging object in the manner specified by the data content. The specific process is shown in Table 2.

[0027]

[0028] S5. Obtain test results; The bus data transmitted back by the suspension management system to the avionics simulator is converted into test results, and the test results corresponding to each suspension under each test stimulus are displayed in the form of a "master / slave table".

[0029] Test cases designed based on "master / slave tables": The steps of displaying the test results corresponding to each pendant under each test stimulus in the form of "master / slave tables" 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 test result rows corresponding to multiple pendants under this test stimulus (that is, the operation of a test stimulus row can correspond to the test results of multiple pendants). These test results are displayed as slave tables of the stimulus row and can be expanded or collapsed 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 (the total operation result is a summary of all results from the slave table, correct or wrong); each result row should include the response object (the pendant in this embodiment), hanging point, operation response, expected result, timeout, and test result (a single test result of the pendant).

[0030] It should be noted that the test result items are filled in after the automatic test is executed, and other items need to be edited in advance by the tester. Specifically, when editing the stimulus row, if the "operation range" element has been selected, then when selecting the "operation step" element, the interface will prompt which "operation step" elements are available based on the value of the "operation range"; if the "operation step" element has been selected, then when selecting the "operation value" element, the interface will prompt which "operation value" elements are available based on the value of "test". Similarly, when the tester is editing the result row, if the "response object" element has been selected, then when selecting the "operation response" or "expected result" elements, the interface will prompt which "test result" and "expected result" elements are available based on the value of the "operation step" element of the stimulus row and the "response object" of the result row, and automatically fill in the "timeout" value after the "test result" is determined.

[0031] like Figure 5 As shown in the figure, the lower left corner specifies the suspensions to be simulated at the 1 / 2 / 3 suspension points, and the upper right corner is a test table based on the master-slave table format. In the first test stimulus row of the test table, the operation scope is "Survey Management System (SMS) under test", the operation steps are "Survey Management System under test start", and the operation value is "Open" (signal valid). After the stimulus is issued, the Suspension Management System under test should reply to the bus message of good start within 10 seconds. After forwarding and judging by the avionics simulator, "Pass" is displayed in the "Test Result" column of the "Detailed Results" slave table, and "Pass" is also displayed in the "Total Test Result" column of the test stimulus row. In the second test stimulus row, the operation scope is "Survey Management System under Test", the operation steps are "Turn on the main power supply of the suspension", and the operation value is "Open" (signal valid). After the stimulus is issued, according to the different timeout times defined in each result row, the Suspension Management System under test should report the recognition results of wpn1 / 2 within the specified timeout time, as well as the report on the main power switch status of the suspension collected by the Suspension Management System under test.

[0032] The following is an explanation of configuring test parameters based on the Extensible Markup Language (xml). Specifically, an example of test parameter configuration is as follows: <?xml version="1.0" encoding="utf-8"?> <testconfig name="测试配置表"> <sta_name_list> <Suspension>None< / Suspension> <Suspension>demo_wpn1< / Suspension> <Suspension>demo_wpn2< / Suspension> < / sta_name_list> <sta_allow_list> <sta 挂点="1"> <Type>demo_wpn1< / Type> < / sta> <sta 挂点="2"> <Type>demo_wpn2< / Type> < / sta> <sta 挂点="3"> <Type>demo_wpn1< / Type> <Type>demo_wpn2< / Type> < / sta> <sta 挂点="4"> <Type>demo_wpn1< / Type> <Type>demo_wpn2< / Type> < / sta> < / sta_allow_list> <oper_option> <sms> <Operation name="-">< / Operation> <Operation name="SMS Start" overtime="10">< / Operation> <Operation name="Landing Gear" overtime="0.5"> <result oper_val="收起"> Close< / result> <result oper_val="放下"> lay down< / result> < / Operation> <Operation name="Real / Train" overtime="0.5"> <result oper_val="真实"> reality< / result> <result oper_val="训练"> train< / result> < / Operation> <Operation name="Total Suspension Power" overtime="0.5">< / Operation> <Operation name="Pickle" overtime="2">< / Operation> <Operation name="Emergency Jettison" overtime="0.5">< / Operation> <Operation name="Occupancy" overtime="0.5">< / Operation> <Operation name="Working Main Mode" overtime="3"> <result oper_val="正常"> normal< / result> <result oper_val="维护"> maintain< / result> <result oper_val="启动自检测"> Good self-examination< / result> <result oper_val="启动自检测"> Self-test failed< / result> < / Operation> <Operation name="Avionics Main Mode" overtime="0.5"> <result oper_val="格斗"> Fighting< / result> <result oper_val="拦截"> Interception< / result> <result oper_val="空面"> empty noodles< / result> <result oper_val="导航"> navigation< / result> < / Operation> <Operation name="Auto Load" overtime="0.5">< / Operation> <Operation name="Inventory Request" overtime="0.5">< / Operation> <Operation name="Main Suspension Selection" overtime="0.5"> <result oper_val="demo_wpn1"> WPN1< / result> <result oper_val="demo_wpn2"> WPN2< / result> < / operation> <operation name="wheel load"> <result oper_val="空中"> Aerial< / result> <result oper_val="地面"> ground< / result> < / operation> < / sms> <weapon name="demo_wpn1"> <Subtype>True< / Subtype> <Subtype>Training< / Subtype> <Fault>Fault 1< / Fault> <Fault>Fault 2< / Fault> <Fault>Fault 3< / Fault> <Operation name="-"> < / Operation> <Operation name="Recognition" overtime="10"> <result> exist< / result> <result> Does not exist< / result> < / Operation> <Operation name="Operation 1" overtime="10"> <result> Result 1a< / result> <result> Result 1b< / result> < / Operation> <Operation name="Operation 2" overtime="195"> <result> Result 2a< / result> <result> Result 2b< / result> < / Operation> <Operation name="Operation 3" overtime="4"> <result> Result 3a< / result> <result> Result 3b< / result> < / Operation> < / weapon> <weapon name="demo_wpn2"> <Subtype>Real< / Subtype> <Subtype>Training< / Subtype> <Fault>None< / Fault> <Fault>Fault 1< / Fault> <Fault>Fault 2< / Fault> <Operation name="-"> < / Operation> <Operation name="Identify" overtime="10"> <result> exist< / result> <result> Does not exist< / result> < / Operation> <Operation name="Select" overtime="0.5"> <result> Select< / result> <result> Unchecked< / result> < / Operation> <Operation name="Launch" overtime="3.5"> <result> Launched< / result> <result> Launch failure< / result> < / Operation> < / weapon> < / oper_option> < / testconfig> .

[0033] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An automatic test method for airborne suspension management function based on an avionics simulator, characterized in that: include: Configuring the test parameters of the suspension simulator of the tested suspension management system, including: configuring the type of suspension simulated by the suspension simulator, the type of suspension corresponding to each hanging point, the preset test excitation of various suspensions simulated by the suspension simulator, and various suspension faults simulated by the suspension simulator; Select the type of suspension to be simulated by the suspension simulator, the preset test stimulus, and the simulated suspension fault from the configured parameters; Generate an excitation command according to a preset test excitation, and send the excitation command to the avionics simulator, wherein the excitation command includes: a discrete quantity command agreed in advance with the avionics simulator, and bus data consistent with a communication bus interface control file between the avionics simulator and the suspension management system; If the avionics simulator receives a discrete quantity command, it will parse it according to the pre-agreed format and send the corresponding discrete quantity to the suspension management system; if the avionics simulator receives bus data, it will forward it to the suspension management system as is according to the message specified in the communication bus interface packet header; The suspension management system controls the suspension simulated by the suspension simulator according to the bus data and discrete quantities, and at the same time, the suspension management system transmits the bus data back to the avionics simulator; The bus interface data is converted into test results, and the test results corresponding to each suspended object under each test stimulus are displayed in the form of a "master / slave table".

2. The automatic test method for the airborne suspension management function based on the avionics simulator according to claim 1 is characterized in that: in, Each row in the main table is a test stimulus row, and each test stimulus row has a subordinate table, which contains the test result row corresponding to the suspended object under the test stimulus.

3. The automatic test method for the airborne suspension management function based on the avionics simulator according to claim 2 is characterized in that: The contents of the test stimulus line include: whether to execute, operation range, operation steps, operation value, and total test results.

4. The automatic test method for the airborne suspension management function based on the avionics simulator according to claim 2 is characterized in that: The contents of the test result row include: response object, hanging point, operation response, expected result, timeout period, and test result.

5. The automatic test method for the airborne suspension management function based on the avionics simulator according to claim 1 is characterized in that: The test stimulus includes: the startup self-test of the tested suspension management system, the power-on of the suspension simulated by the suspension simulator, the suspension alignment and the cabin opening simulated by the suspension simulator; the test results are: the self-test result of the tested suspension management system is normal / failed, the power-on identification of the suspension simulated by the suspension simulator is successful / failed, the suspension alignment simulated by the suspension simulator is successful / failed, and the cabin opening is successful / failed.

6. The automatic test method for the airborne suspension management function based on the avionics simulator according to claim 1 is characterized in that: Determine whether the content of the bus data returned by the hanging object management system has changed. If the content has changed, obtain the test result according to the meaning of the data parsed by the built-in interface control file.

7. An automatic test system for airborne suspension management function based on an avionics simulator, characterized in that: include: A parameter configuration module is used to configure the test parameters of the suspension simulator of the tested suspension management system, including: configuring the type of suspension simulated by the suspension simulator, the type of suspension corresponding to each hanging point, the preset test excitation of various suspensions simulated by the suspension simulator, and various suspension faults simulated by the suspension simulator; An excitation selection module, used to select the type of suspension simulated by the suspension simulator, perform a preset test excitation, and simulate the suspension fault from the configured parameters; The stimulus module is used to generate a stimulus command according to a preset test stimulus and send the stimulus command to the avionics simulator, wherein the stimulus command includes: a discrete quantity command agreed in advance with the avionics simulator, and bus data consistent with a communication bus interface control file between the avionics simulator and the suspension management system; The test module is used for parsing the discrete quantity command received by the avionics simulator according to the pre-agreed format and sending the corresponding discrete quantity to the suspension management system; if the avionics simulator receives the bus data, it forwards it to the suspension management system as it is according to the message specified in the communication bus interface packet header, and the suspension management system controls the suspension simulated by the suspension simulator according to the bus data and the discrete quantity, and at the same time, the suspension management system returns the bus data to the avionics simulator; The test result module is used to convert the bus interface data into test results and display the test results corresponding to each suspended object under each test stimulus in the form of a "master / slave table".

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