A Test Method for Complex Airborne System Configuration Items Combining Models

Abstract

The present invention belongs to the field of airborne software testing, and specifically relates to a method for testing complex airborne system configuration items in combination with a model. By using a DDS network to replace the transmission of data such as the product's RS422, 1553B, discrete signals, and analog quantities, the product is freed from the limitations of actual hardware interfaces. By stipulating the rules to be followed when establishing the model, the system model can be connected to the DDS communication network and participate in the closed-loop testing of the entire system. The test input node realizes the test input by changing the input data of the product under test in the network. The test observation node subscribes to all the data in the DDS network and displays it, observes the output of the product under test, and determines whether the test result meets the expectations. This method can realize the access of the system model, enable each product to be freed from the actual hardware interface, build a configuration item test environment on a common PC, and realize the configuration item test. At the same time, it is not limited by the quantity of actual embedded hardware products and can be repeatedly deployed on a common computer to achieve reuse.

Description

Technical Field

[0001] The present invention belongs to the field of airborne software testing, and specifically relates to a test method for complex airborne system configuration items combined with models. Background Art

[0002] With the development of weaponry and equipment, the architecture of airborne systems has undergone fundamental changes. Airborne systems are becoming increasingly important, more complex, and larger in scale. Airborne software has become a key part of aviation weaponry models. On the other hand, with the application of the MBSE method in the aviation field, more and more systems start using modeling tools at the initial stage of the project to verify the rationality of the design and logic of each system. Software testing is an important means to detect and solve airborne software problems in advance. The traditional test method for airborne software configuration items is to build a dedicated test bench and supporting equipment for the system to be tested. This test bench and equipment are tailored for different aircraft models and aircraft systems, which are expensive and lack generality. During use, it does not support parallel use. Since all relevant departments need to use it during the development process, this test bench system is extremely precious. As the iteration speed of airborne software is getting faster and faster, the drawbacks of this configuration item test method using the test bench are gradually emerging. In addition to being difficult to reuse, expensive, resource-intensive, and not supporting parallel use, it is also impossible to utilize the existing system models of each specialty.

[0003] In summary, it is very necessary to design a configuration item test method that can utilize models, can be reused, and is independent of the actual hardware environment. Summary of the Invention

[0004] Compared with the method of building a test environment for finished products of airborne systems, in this method, the data originally transmitted through RS422, 1553B, discrete signals, analog quantities, etc. between each system is converted into DDS network data for transmission, and the communication of simulation data is simplified through data subscription and publishing services. The data interaction rules of each node are formulated in the form of configuration files. By stipulating simple rules that need to be followed when establishing a model, the established model can be connected to the communication network, receive input data from the communication network, and send output data, and participate in the closed-loop test of the entire system. The product under test and the accompanying test product are also connected to the network as nodes, and the input and output data are obtained and published through the DDS network. The input data of the product under test in the network is changed by the test input node to achieve test input. The test observation node monitors the data by subscribing to all the data in the network to determine whether the test results meet the expectations. In this way, relevant system products can be separated from the actual hardware, and a configuration item test environment can be built on a common PC to achieve configuration item testing. At the same time, this environment is not limited by the number of actual embedded hardware finished products and can be repeatedly deployed on a common computer to achieve reuse.

[0005] The present invention attaches importance to the data communication content of the airborne system, uses Ethernet to replace the data transmission in each system, changes and monitors the data in the network through the publish-subscribe method, and establishes a set of operating and test environments that can be accessed by the airborne system.

[0006] Technical solution of the present invention:

[0007] A test method for complex airborne system configuration items combined with a model, characterized by comprising the following steps:

[0008] Step 1: Transform all products that need to access the test environment, transform the external interface information originally transmitted through the hardware interface of the product into transmission through the DDS network, and divide the transmitted data into two categories: input and output, to form corresponding interface control files for other products accessing the DDS network to parse when receiving / sending data;

[0009] Step 2: Transform the model that is being modeled or has been modeled, unify all external inputs of the model to be input through a single file; output data is output through a single file; the definition of the model input data and output data files should meet the data composition rules in Step 1; and provide a general call interface, through which the model can be driven to run; publish the model in the form of a dynamic link library;

[0010] Step 3: Integrate the dynamic link library formed in Step 2 through the simulation communication interface middleware to drive the model to run; send and receive the transformed model data in the communication network, send the output data of the model to the network according to the data transmission format, receive the data subscribed by the model in the network, and write the data to the input file of the model. The simulation communication interface middleware is responsible for loading the model and scheduling its operation, receiving the control information sent by the simulation master control node, including four states: start, run, pause, and accelerate; when the simulation communication interface middleware receives the start control command, it sends the local IP address, host name, model name, node description, and online information to the DDS network; when receiving the run control command, it calls the model information to start running. The model reads the input data from the input file and writes the output data to the send file. The simulation interface communication middleware is responsible for receiving data from the DDS network and sending data to the DDS network; when receiving the pause control command, it pauses calling the model; when receiving the accelerate command, it changes the model operation cycle to make the model run at an accelerated or decelerated speed;

[0011] Step 4: Monitor the current running status and information of each node connected to the DDS network through the simulation master node. The status includes four states: start, run, pause, and stop. The node information includes the node IP address, host name, model name, node description, and whether it is online. The simulation master node can send four control commands to the node: start, run, pause, and accelerate.

[0012] The specific implementation process in Step 1 is as follows:

[0013] 1) Divide the external interface information transmitted through the hardware interface of each product connected to the test environment into two parts: input and output, centered around each product.

[0014] 2) Establish a simulation parameter data structure to represent the specific values of the above-divided input and output data. The simulation parameter data structure includes two parts: type and data. The data is an 8-byte array that records the data value of a specific signal in the external interface information.

[0015] 3) Establish a simulation transmission data structure, combine the simulation parameter data structures into a whole to represent all the data of a certain external interface information, and facilitate transmission in the DDS network. The simulation data structure includes a structure name, an array of simulation parameter data structures, and the number of data. Among them, the array of simulation parameter data structures is a collection of simulation parameter data structures, used to represent all the data in a certain external interface information. The number of data represents the number of data in the array of simulation parameter data structures.

[0016] 4) Organize and form an interface control file for the external interface information in the above manner. Each product sends the output data to the DDS network according to the interface control file. On the other hand, according to the data that each product needs to subscribe to in the DDS network, the received data is parsed according to the interface control file for its own use.

[0017] One or more data types can be selected according to the actual usage to define the simulation parameter data structure. The data types to be used should be determined according to the specific signal types used in the external interface of the product.

[0018] The specific combination of the simulation parameter data structure in Step 1 is in the form of structure index + parameter index. Among them, the structure index can be represented by two bytes, numbered from 0, but the number of bytes used is not limited to two, denoted as StrucIndex; the parameter index can be represented by two bytes, but the number of bytes used is not limited to two, denoted as Index, numbered from 1. Among them, the structure index occupies the high byte, and the parameter index occupies the low byte, forming the data index value VarIndex. The simulation parameter data structures with the same StrucIndex belong to the same external interface, and Index represents the position of the simulation parameter data structure in the simulation transmission data structure.

[0019] In Step 1, the structure name of the simulated transmission data structure can be the same as the actual physical meaning represented by the simulated data.

[0020] The external interface information includes RS422, 1553B, discrete signals, analog signals, and FC.

[0021] The external interface information is not limited to the described interface types. The external interface information is determined by the interfaces actually used by the products accessing the communication network.

[0022] In Step 1, the corresponding relationship between the data types of the external interface information is shown in Table 1:

[0023] Table 1 Corresponding Relationship Table of Data Types in External Interface Information

[0024]

[0025]

[0026] The data transmission format in Step 3 is: "VarIndex VarData VarIndex VarData VarIndexVarData VarIndex VarData…", where VarIndex is the data index value and varData is the data.

[0027] It further includes Step 5: Subscribe to all data in the DDS network through the test input node and parse according to the interface control file of each node; when conducting tests, the test input node publishes the designed input data to the DDS network in the form of published information, which is received by the product under test.

[0028] It further includes Step 6: Subscribe to all data in the DDS network through the test observation node, parse the data according to the interface control protocol of each node, and display it; when the input of the software under test is changed through the test input node, observe whether the output data of the product under test is correct and meets the expectations through the data observation node, so as to judge the correctness of the function of the product under test.

[0029] Advantages of the present invention:

[0030] The present invention is applied in the field of aviation airborne software testing. The present invention replaces the test bench that was originally tailored for aircraft systems, is expensive, not universal, and cannot work in parallel, with a DDS network for the transmission of data such as RS422, 1553B, discrete signals, and analog signals of the product, and proposes a method for conducting tests in this new test environment. The following technical effects are achieved:

[0031] 1. Compared with the method of establishing a test bench for aircraft systems, this method proposes to use a DDS network to replace the transmission of data such as RS422, 1553B, discrete signals, and analog quantities, enabling the data accessed in the test environment to be freed from the limitations of hardware interfaces. It is easier to observe the input and output data of each product using a general DDS network.

[0032] 2. This invention proposes simple principles for rewriting various system models in the aviation field, enabling the input and output data of the models to be completed through a DDS network, so that they can be connected to the aviation product test environment to verify the correctness of model operation. The models can also be used as accompanying test pieces to assist in verifying the correctness of the products under test.

[0033] 3. The method proposed in this invention can make the entire test environment independent of actual hardware, virtualize the test environment and each product, and deploy multiple sets of the same environment on a computer, enabling system personnel, designers, and testers involved in research and development to deploy independent test environments with almost no additional cost, thereby assisting in the development and verification work.

[0034] 4. This invention can be extended to other fields. This method is also applicable to establishing test environments for products with the same characteristics to carry out verification, not limited to the field of aviation airborne software testing. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 is a test method for complex airborne system configuration items combined with models;

[0036] Figure 2 are the specific implementation steps of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0037] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative work shall fall within the protection scope of the present invention.

[0038] A test method for complex airborne system configuration items combined with models includes the following steps:

[0039] Step 1: Modify all products that need to be connected to the test environment, transform the external interface information originally transmitted through the hardware interface of the product into transmission through a DDS network, and divide the transmitted data into two categories: input and output, to form corresponding interface control files for other products connected to the DDS network to parse when receiving / sending data.

[0040] 1) Divide the external interface information transmitted through the hardware interface of each product accessing the test environment into two parts: input and output, centered around each product;

[0041] 2) Establish a simulation parameter data structure to represent the specific values of the input and output data divided above. The simulation parameter data structure includes two parts: type and data. The type definition is shown in the following table, and the data is an 8-byte array that records the data value of a specific signal in the external interface information.

[0042] Table 1 Correspondence Table of Data Types in External Interface Information

[0043] Data Definition Meaning Type char Character 1 octet Represents an eight-bit quantity 1 short Integer variable 2 unsigned short Unsigned integer variable 2 long Long integer data 4 unsigned long Unsigned long integer 4 long long Long long integer 8 unsigned long long Unsigned long long integer 8 float Single-precision floating-point data 4 double Double-precision floating-point 8 boolean Boolean variable 1

[0044] 3) Establish a simulation transmission data structure to combine the simulation parameter data structure into a whole to represent all the data of a certain external interface information, facilitating transmission in the DDS network. The simulation data structure includes a structure name, an array of simulation parameter data structures, and the number of data. Among them, the array of simulation parameter data structures is a collection of simulation parameter data structures, used to represent all the data in a certain external interface information; the number of data represents the number of data in the array of simulation parameter data structures;

[0045] 4) Organize and form an interface control file for the external interface information in the above manner. Each product sends the output data to the DDS network according to the interface control file; on the other hand, according to the needs of each product to subscribe to the data in the DDS network, the received data is parsed according to the interface control file for its own use.

[0046] Step 2: Modify the model that is being modeled or has been modeled. Unify all the external inputs of the model to be input through a single file; the output data is output through a single file; the definitions of the model input data and output data files should meet the data composition rules in Step 1; and provide a general call interface through which the model can be driven to run; publish the model in the form of a dynamic link library.

[0047] Step 3: Integrate the dynamic link library formed in Step 2 through the simulation communication interface middleware to drive the model to run. Send and receive the modified model data in the communication network, send the output data of the model to the network according to the data transmission format, receive the data subscribed by the model in the network, and write the data to the input file of the model. The data transmission format is specifically: "VarIndex VarData VarIndex VarData VarIndex VarData VarIndexVarData…", where VarIndex is the data index value and varData is the data. The simulation communication interface middleware is responsible for loading the model and scheduling its operation, and receiving the control information sent by the simulation master node, including four states: start, run, pause, and acceleration.

[0048] When the simulation communication interface middleware receives the start control command, it sends the local IP address, host name, model name, node description, and online information to the DDS network; when it receives the run control command, it calls the model information to start running. The model reads the input data from the input file and writes the output data to the send file. The simulation interface communication middleware is responsible for receiving data from the DDS network and sending data to the DDS network; when it receives the pause control command, it pauses calling the model; when it receives the acceleration command, it changes the running cycle of the called model to enable the model to run at an accelerated or decelerated speed.

[0049] Step 4: Monitor the current running status and information of each node connected to the DDS network through the simulation master node. The status includes four states: start, run, pause, and stop, and the node information includes the node IP address, host name, model name, node description, and whether it is online. The simulation master node can send four control commands: start, run, pause, and acceleration to the node.

[0050] Further, it also includes Step 5: Subscribe to all the data in the DDS network through the test input node and parse it according to the interface control file of each node. When conducting a test, the test input node publishes the input data designed by the tester to the DDS network in the form of publishing information, which is received by the product under test;

[0051] Further, it also includes Step 6: Subscribe to all the data in the DDS network through the test observation node, parse the data according to the interface control protocol of each node, and display it. When the tester changes the input of the software under test through the test input node, observe whether the output data of the product under test is correct and meets the expectations through the data observation node, so as to judge the correctness of the function of the product under test.

[0052] Further, in the first step, one or more data types can be selected according to the actual usage to define the simulation parameter data structure. The data types to be used should be determined based on the specific signal types used in the external interface of the product. For example, if all the input signals of a certain product are signals of 0 or 1, only boolean variables can be used.

[0053] Further, the combination of the simulation parameter data structure in the first step is specifically in the form of: structure index + parameter index, where the structure index can be represented by two bytes, numbered from 0, but the number of bytes used is not limited to two, denoted as StrucIndex; the parameter index can be represented by two bytes, but the number of bytes used is not limited to two, denoted as Index, numbered from 1. Among them, the structure index occupies the high byte, and the parameter index occupies the low byte, forming the data index value VarIndex. The simulation parameter data structures with the same StrucIndex belong to the same external interface, and Index represents the position of the simulation parameter data structure in the simulation transmission data structure. For example: StrucIndex = 0x0001, Index = 0x0002, and when combined, VarIndex is 0x00010002.

[0054] Further, the structure name of the simulation transmission data structure in the first step can be the same as the actual physical meaning represented by the simulation data. For example: "RS422 data frame", "1553B data frame", etc. This is convenient for identifying the specific interface specific meaning corresponding to the simulation data structure.

[0055] Further, the external interface information includes RS422, 1553B, discrete signals, analog quantities, FC.

[0056] In the previous step, the external interface information is not limited to the described interface types. The external interface information is determined by the interfaces actually used by the products accessing the communication network.

[0057] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0058] Embodiment:

[0059] A test method for complex airborne system configuration items combined with a model includes transforming the external interface information transmitted through the hardware interface to be transmitted through the DDS network; transforming the model; driving the model to run through the simulation communication interface middleware; the simulation master node monitoring each node; the test input node changing the input of the node under test; and the test observation node subscribing to all the data in the DDS network.

[0060] Step 1: Modify the product connected to the test environment, divide the transmitted data into two categories: input and output, and form corresponding interface control files.

[0061] Taking a simplified power system of an aircraft as an example, this article first sorts out the input signals and output signals of this power system. Among them, the input signals include:

[0062]

[0063] Then the corresponding simulation parameter data structures are {8, Data[8]}, {1, Data[8]}, and the corresponding Indexes are 0x0001 and 0x0002 respectively;

[0064] The corresponding data transmission structure is {"Power input signal", {{8, Data[8]}, {1, Data[8]}}, 2}. StrucIndex is 0x0000.

[0065] The output signals include:

[0066] Signal name Data type Meaning Electromagnetic valve control discrete quantity boolean 0 means off, 1 means on Discharge valve control discrete quantity boolean 0 means off, 1 means on

[0067] Then the corresponding simulation parameter data structures are {1, Data[8]}, {1, Data[8]}, and the corresponding Indexes are 0x0001 and 0x0002 respectively.

[0068] The corresponding data transmission structure is {"Power output signal", {{1, Data[8]}, {1, Data[8]}}, 2} StrucIndex is 0x0001.

[0069] Step 2: Modify the model. The model receives discrete signals for electromagnetic valve control and discrete signals for discharge valve control, simulates the valve actions, and feedbacks the valve positions. Form interface files for all external inputs and external outputs of the model according to the rules, and form an input interface control file and an output interface control file respectively, which is convenient for the model to obtain data from the DDS network.

[0070] Among them, for the input interface control file, the data content is:

[0071] {"Model input signal", {{1, Data[8]}, {1, Data[8]}}, and the corresponding StrucIndex is 0x0001.

[0072] Among them, for the output interface control file, the data content is:

[0073] {"Model output signal", {{1, Data[8]}}, and the corresponding StrucIndex is 0x0002.

[0074] Step 3: Integrate the dynamic link library formed in Step 2 through the simulation communication interface middleware to drive the model to run.

[0075] Assume the valve position value is 50, then the data transmission format sent by the model in the DDS network is: 0x0002000150.

[0076] Step 4: Monitor the current operating status and information of each node connected to the DDS network through the simulation master node.

[0077] Each node feeds back the IP address, host name, model name, node description, and online status information.

[0078] Step 5: Test that the input node subscribes to all data in the DDS network, and the published information is received by the product under test. For example, the test input node simulates the control computer input (set to 0) to let the power system run.

[0079] Then a piece of information is published, and the information format is 0x000000020.

[0080] Step 6: Observe through the test that the node subscribes to all data in the DDS network, and check whether the power system outputs the discrete quantity of electromagnetic valve control and the discrete quantity signal of emission valve control as required after receiving the message of the control computer input (set to 0).

[0081] The present invention attaches importance to the data content such as RS422, 1553B, discrete signals, and analog quantities transmitted between aircraft systems, ignores their specific transmission methods, transmits them through Ethernet, and establishes a simple principle for establishing or rewriting a model or system, enabling the aircraft system and the model to transmit data in the established network after simple rewriting. By monitoring the test input node and changing the data transmitted in the network, and observing the test node subscribing to and displaying all data in the DDS network to achieve the purpose of aircraft system-level testing. The specific steps of the method are as Figure 2 .

[0082] As described above, only the specific embodiments of the present invention are described in detail, and the unelaborated parts are conventional technologies. However, the protection scope of the present invention is not limited thereto, and any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered by the protection scope of the present invention. The protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A test method for complex airborne system configuration items combining models, characterized in that, It includes the following steps: Step 1: Modify all products that need to access the test environment. Transform the external interface information originally transmitted through the hardware interface of the product into transmission through the DDS network, and divide the transmitted data into two categories: input and output, to form corresponding interface control files for other products accessing the DDS network to parse when receiving / sending data; Step 2: Modify the models that are being modeled or have been modeled. Uniformly input all external inputs of the model through a single file; Output data is output through a single file; the definitions of the model input data and output data files should meet the data composition rules in Step 1; and provide a general call interface through which the model can be driven to run; release the model in the form of a dynamic link library; Step 3: Integrate the dynamic link library formed in Step 2 through the simulation communication interface middleware to drive the model to run; send and receive the modified model data in the communication network, send the output data of the model to the network according to the data transmission format, receive the data subscribed by the model in the network, and write the data to the input file of the model. The simulation communication interface middleware is responsible for loading the model and scheduling its operation, and receiving the control information sent by the simulation master control node, including four states: start, run, pause, and accelerate; when the simulation communication interface middleware receives the start control command, it sends the local IP address, host name, model name, node description, and online status information to the DDS network; When receiving the run control command, it calls the model information to start running. The model reads the input data from the input file and writes the output data to the send file. The simulation interface communication middleware is responsible for receiving data from the DDS network and sending data to the DDS network; When receiving the pause control command, it pauses calling the model; when receiving the accelerate command, it changes the running cycle of the called model to enable the model to run at an accelerated or decelerated speed; Step 4: Monitor the current running status and information of each node accessing the DDS network through the simulation master control node. The status includes four states: start, run, pause, and stop, and the node information includes the node IP address, host name, model name, node description, and online status; the simulation master control node can send four control commands: start, run, pause, and accelerate to the node; Step 5: Subscribe to all data in the DDS network through the test input node and parse it according to the interface control file of each node; when conducting tests, the test input node publishes the designed input data to the DDS network in the form of published information for the product under test to receive; Step 6: Subscribe to all data in the DDS network through the test observation node, parse the data according to the interface control protocol of each node, and display it; When changing the input of the software under test through the test input node, observe whether the output data of the product under test is correct and meets the expectations through the data observation node, so as to judge the correctness of the function of the product under test.

2. The test method for complex airborne system configuration items combined with a model according to claim 1, wherein The specific implementation process in Step 1 is as follows: 1) Divide the external interface information transmitted through the hardware interface of each product accessing the test environment into two parts: input and output, centered around each product; 2) Establish a simulation parameter data structure to represent the specific values of the input and output data divided above. The simulation parameter data structure includes two parts: type and data. The data is an 8-byte array that records the data value of a specific signal in the external interface information; 3) Establish a simulation transmission data structure, combine the simulation parameter data structures into a whole to represent all the data of a certain external interface information, facilitating transmission in the DDS network; the simulation data structure includes a structure name, an array of simulation parameter data structures, and the number of data; among them, the array of simulation parameter data structures is a collection of simulation parameter data structures, used to represent all the data in a certain external interface information; The number of data represents the number of data in the array of simulation parameter data structures; 4) Organize and form an interface control file for the external interface information in the above manner. Each product sends the output data to the DDS network according to the interface control file; on the other hand, according to the needs of each product to subscribe to the data in the DDS network, parse the received data according to the interface control file for its own use; One or more data types can be selected according to the actual usage situation to define the simulation parameter data structure; the data types to be used should be determined according to the specific signal types used in the external interface of the product.

3. The test method for complex airborne system configuration items combined with a model according to claim 2, characterized in that The combination of the simulation parameter data structures in step 1 is specifically in the form of: structure index + parameter index. Among them, the structure index is represented by two bytes, numbered from 0, but the number of bytes used is not limited to two, denoted as StrucIndex; the parameter index is represented by two bytes, but the number of bytes used is not limited to two, denoted as Index, numbered from 1; among them, the structure index occupies the high byte, and the parameter index occupies the low byte, forming the data index value VarIndex; the simulation parameter data structures with the same StrucIndex belong to the same external interface, and Index represents the position of the simulation parameter data structure in the simulation transmission data structure.

4. The test method for a complex airborne system configuration item combining a model according to claim 3, characterized in that The structure name of the simulation transmission data structure in step 1 is consistent with the actual physical meaning represented by the simulation data.

5. A test method for a complex airborne system configuration item combined with a model according to claim 4, characterized in that, The external interface information includes RS422, 1553B, discrete signals, analog quantities, and FC.

6. The test method for a complex airborne system configuration item combined with a model according to claim 5, wherein The external interface information is not limited to the described interface types, and the external interface information is determined by the interfaces actually used by the products accessing the communication network.

7. A test method for complex airborne system configuration items combined with a model according to claim 1, characterized in that In step 1, the corresponding relationship between the data types of the external interface information is shown in Table 1: Table 1 Corresponding relationship table of data types in external interface information 。 8. A test method for complex airborne system configuration items combined with a model according to claim 1, characterized in that The data transmission format in step 3 is: "VarIndex VarData VarIndex VarData VarIndex VarDataVarIndex VarData…", where VarIndex: data index value, varData: data.

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