CN117632702A - Model-based test system and test method suitable for spacecraft integrated electronic software - Google Patents
Model-based test system and test method suitable for spacecraft integrated electronic software Download PDFInfo
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- CN117632702A CN117632702A CN202311425049.7A CN202311425049A CN117632702A CN 117632702 A CN117632702 A CN 117632702A CN 202311425049 A CN202311425049 A CN 202311425049A CN 117632702 A CN117632702 A CN 117632702A
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Abstract
The invention provides a model-based test system suitable for spacecraft integrated electronic software, which comprises: a front-end communication model; the front-end communication model is a variable subsystem which is controlled by a variant control item to be in two modes of model in-loop test or hardware in-loop test; after the model in-loop verification, an embedded comprehensive electronic software code is automatically generated, and the embedded comprehensive electronic software code can be directly operated on comprehensive electronic hardware equipment or virtual simulation software to perform hardware in-loop verification after being compiled, so that the conventional organization assets based on a document development mode are multiplexed to the greatest extent, an interface between ground test platform software and the model is opened, and the problem of low simulation verification efficiency of the spacecraft comprehensive electronic software model is solved.
Description
Technical Field
The invention relates to a test method and a test system of a software model, in particular to a test system and a test method which are applicable to a spacecraft integrated electronic software based model.
Technical Field
In the traditional software development process, design results of all stages are presented in a form of a document and are transferred among all stages, so that a document-based software development mode is formed. However, with the continuous increase of the size and complexity of the spacecraft software, the difficulty faced by the traditional document-based software development mode is more and more obvious, and the "model-driven software development" gradually draws attention in the software development mode. The software development based on model driving needs to be verified in multiple directions and multiple levels such as model in ring, software in ring, hardware in ring and the like, and the test result can be used for verifying whether the software acts correctly. The spacecraft comprehensive electronic software takes whole data management as a main function, is a typical discrete system, is common software (such as Matlab/Simulink) in various fields, and has low efficiency when the self-contained data interaction method is applied to simulation and verification of a comprehensive electronic software model, so that the method and the system for efficiently testing the spacecraft comprehensive electronic software based on the model are necessary to be established.
The invention discloses a model-based rapid implementation platform for flight control software, which is disclosed in CN109710247A patent of China aerodynamic research and development center computing aerodynamic research institute.
The above method mainly has the following problems:
(1) The method needs a flight control computer device to perform semi-physical simulation, namely, extra hardware support is needed, and simulation and verification of the model in a virtual soft environment are not supported.
(2) A code test model needs to be developed specifically to determine whether the code passes the test, and its pure model-based test method fails to fully utilize existing tools and organization-level assets of the past document model-based development model.
(3) The method is suitable for model-based development of aviation flight control software, and because the aviation flight control software and the spacecraft integrated electronic software have great differences in functions, use scenes and the like, the method and the platform are not suitable for model-based testing of the spacecraft integrated electronic software.
Disclosure of Invention
In view of the above, the invention provides a model-based test system and a test method for spacecraft integrated electronic software, which open up an interface between ground test platform software and a model, and solve the problem of low simulation verification efficiency of the spacecraft integrated electronic software model.
The technical scheme for realizing the invention is as follows:
a model-based test system for spacecraft integrated electronic software, comprising: a front-end communication model; the front-end communication model is a variable subsystem which is controlled by a variant control item to be in model on-loop verification or hardware on-loop verification;
when the variable subsystem is in the loop verification of the model, packaging data received by the spacecraft comprehensive electronic software model, transmitting the data to the ground telemetry and remote control master control software for display after protocol conversion, receiving data uploaded by the ground telemetry and remote control master control software, analyzing a remote control instruction according to a stipulated protocol, and transmitting the data to the spacecraft comprehensive electronic software model for execution;
when the variable subsystem is in hardware-in-loop verification, a spacecraft comprehensive electronic software model is used for generating a code for hardware-in-loop test through a code automatic tool according to a software call interface reserved in advance, the code is integrated with a hardware driver and an operating system interface through a script, and the code is directly downloaded to spacecraft comprehensive electronic hardware equipment or virtual simulation software for running after compiling, so that the hardware-in-loop test of the model is performed.
Further, the spacecraft comprehensive electronic software model comprises modeling of application function layer functions, and a bottom layer hardware driving software and operating system software writing interface is reserved.
Further, the variant control item is realized by two configuration sets, namely a configuration set for simulation and a configuration set for code generation, wherein the two configuration sets and the front-end communication model are stored in the same file, and the front-end communication model can view and modify the contents of the two configuration sets.
Furthermore, the telemetry analysis configuration, the remote control instruction data and the test cases of the ground telemetry remote control master control software can multiplex the existing test cases verified by the model in a ring.
Furthermore, the spacecraft comprehensive electronic software model and the front-end communication model are constructed by adopting a Matlab/Simulink standard model-based development environment.
Furthermore, the front-end communication model is connected with the ground telemetry and remote control master control software through a TCP/IP network.
A model-based test method suitable for spacecraft integrated electronic software comprises the following specific processes:
setting a variant control item, controlling a front-end communication model to be in a model ring test mode, packaging data sent by a spacecraft comprehensive electronic software model by the front-end communication model, transmitting the data to ground telemetry and remote control master control software for display after protocol conversion, receiving and analyzing a remote control instruction uploaded by the ground telemetry and remote control master control software, transmitting the remote control instruction to the spacecraft comprehensive electronic software model for execution, and checking the correctness of the model function through model ring test;
setting a variant control item, controlling a front-end communication model to be in a hardware-in-loop test mode, automatically generating codes of a spacecraft comprehensive electronic software model according to a pre-reserved software call interface by the front-end communication model, generating codes for hardware-in-loop test, integrating the codes with a hardware driver and an operating system interface through a script, directly downloading the codes to spacecraft comprehensive electronic hardware equipment or virtual simulation software to run after compiling, and checking the correctness of hardware functions through hardware-in-loop test.
The beneficial effects are that:
firstly, modeling and simulation tool software and integrated electronic ground test platform software are connected through a front-end communication model, the model on-loop verification is realized, after the model on-loop verification is passed, the model can be indicated that the model does not have problems, then an embedded integrated electronic software code is automatically generated, after the embedded integrated electronic software code is compiled, the embedded integrated electronic software code can directly run on integrated electronic hardware equipment or virtual simulation software to carry out hardware on-loop verification, the tissue assets under the traditional document development-based mode are multiplexed to the greatest extent, an interface between the ground test platform software and the model is opened, and the problem of low simulation verification efficiency of the integrated electronic software model of the spacecraft is solved.
Secondly, the method can be based on the same set of ground remote measurement and remote control master control software when the execution model is in loop test and the hardware is in loop test, thereby realizing complete multiplexing in the aspects of remote measurement analysis configuration, remote control instruction data and test cases and greatly improving test verification efficiency.
Thirdly, the method establishes two different configuration sets in the same set of models through a variable subsystem mode, wherein the two different configuration sets are the configuration set for model ring simulation and the configuration set for model automatic code generation respectively, so that model simulation and code generation one-key switching are realized in one set of models, and the problem that the model ring and code generation do not correspond to the same set of models is avoided.
Fourth, the invention constructs the front end communication model, the front end communication model is connected with the ground remote-measuring and remote-controlling main control software through TCP/IP network, the front end communication model simulates the communication protocol of data interaction with the ground remote-measuring and remote-controlling main control software, and the upstream and downstream bidirectional data are respectively unpacked and packaged, thereby realizing the direct communication between the satellite-borne software model and the ground remote-measuring and remote-controlling main control software.
Drawings
FIG. 1 is an MBSwE environment of integrated electronic software.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
The spacecraft comprehensive electronic software model is based on Matlab/Simulink standard model development environment, an interface between the spacecraft comprehensive electronic software model and traditional ground telemetry and remote control main control software is opened by expanding a front-end communication function module, the model of the spacecraft comprehensive electronic model is verified in a ring and hardware in the ring based on the existing ground spacecraft test software, the whole development flow based on the model is seamlessly connected, and an MBSwE environment of the spacecraft comprehensive electronic software based on the method is shown in figure 1.
The embodiment of the application provides a model-based test system for spacecraft integrated electronic software, which comprises the following components: a front-end communication model; the front-end communication model is a variable subsystem which is controlled by a variant control item to be in a model on-loop test or a hardware on-loop test;
when the variable subsystem is in the loop verification of the model, packaging CADU data received by the spacecraft comprehensive electronic software model, transmitting the CADU data to a ground remote-measuring and remote-controlling main control software module for display after protocol conversion, receiving data uploaded by the ground remote-measuring and remote-controlling main control software, analyzing a remote-controlling instruction according to a stipulated protocol, and transmitting the remote-controlling instruction to the spacecraft comprehensive electronic software model for execution;
when the variable subsystem is in hardware-in-loop verification, a spacecraft comprehensive electronic software model is used for generating a code for hardware-in-loop test through a code automatic tool according to a software call interface reserved in advance, the code is integrated with a hardware driver and an operating system interface through a script, and the code is directly downloaded to spacecraft comprehensive electronic hardware equipment or virtual simulation software for running after compiling, so that the hardware-in-loop test of the model is performed.
The modeling and simulation tool software and the integrated electronic ground test platform software are connected through the front-end communication model, the model on-loop verification is realized, after the model on-loop verification is passed, the model can be indicated that the model does not have problems, then the embedded integrated electronic software code is automatically generated, after the modeling, the embedded integrated electronic software code can be directly operated on integrated electronic hardware equipment or virtual simulation software to carry out hardware on-loop verification, the tissue assets under the traditional document development-based mode are multiplexed to the greatest extent, the interface between the ground test platform software and the model is opened, and the problem of low simulation verification efficiency of the spacecraft integrated electronic software model is solved. The specific process of building the model-based test system for the spacecraft integrated electronic software is as follows:
firstly, a spacecraft comprehensive electronic software model architecture is built based on commercial modeling simulation software Matlab/Simulink, and a model external interface is built in the model architecture, wherein the model external interface comprises telemetry, remote control, satellite time and the like. The spacecraft comprehensive electronic software model only comprises modeling of application layer functions, and the bottom hardware driving software and the operating system software need to reserve interfaces in the modeling process, so that the model codes can be integrated with handwriting codes after being automatically generated. In addition, under the condition of the existing software components, general function libraries and other organization assets, the part of codes can be directly integrated into the whole model engineering without re-modeling and code generation, and can be directly called by the spacecraft comprehensive electronic software model through a function interface.
And establishing a front-end communication model in the model framework, wherein the model realizes a communication protocol between a hardware test client and ground telemetry and remote control master control software (namely ground test software) and is used for communication between the spacecraft comprehensive electronic software model and the ground telemetry and remote control master control software, and the front-end communication model receives remote control instructions uploaded by the ground telemetry and remote control master control software and transmits the remote control instructions to the spacecraft comprehensive electronic software model, receives CADU telemetry data generated by the spacecraft comprehensive electronic software model and transmits the CADU telemetry data to the ground telemetry and remote control master control software for analysis.
The method is characterized by comprising the steps of realizing a specific model in a front-end communication model, wherein communication with a ground telemetry and remote control main control software module is realized by adopting an M function, and the front-end communication model is used as a bridging model for interconnection between the ground telemetry and remote control main control software and a spacecraft comprehensive electronic software model and is only used for model simulation and is not used for generating codes.
The front-end communication model establishes TCP/IP network connection with the ground remote measurement and remote control master control software through a network library function in Matlab/Simulink, the ground remote measurement and remote control master control software is used as a Client end, the front-end communication model is used as a Server end, and the connection supports two-way operation of receiving and transmitting. The input of the front-end communication model is a CADU frame periodically generated by the spacecraft comprehensive electronic software model, after the CADU frame is received, the front-end communication model encapsulates the CADU frame source code into a communication protocol packet according to a protocol between the CADU frame source code and the ground telemetry and remote control main control software, the communication protocol packet is transmitted to the ground telemetry and remote control main control software through TCP/IP connection, and the ground telemetry and remote control main control software analyzes the original CADU frame from the communication protocol packet and displays telemetry information in the original CADU frame according to ground configuration.
The front-end communication model monitors a specific port, receives remote control instruction data sent by the ground remote control and remote control main control software through TCP/IP network connection, analyzes the received data according to a protocol between the received data and the ground remote control and remote control main control software to obtain original remote control instruction data which can be processed by the spacecraft comprehensive electronic software model, outputs the remote control instruction data and the effective data length to the spacecraft comprehensive electronic software model, changes the effective data length into 0 after the output is completed, and avoids the spacecraft comprehensive electronic software model from repeatedly processing instructions in the simulation process.
The external interface of the spacecraft integrated electronic software model establishes two different configuration sets (namely variant control items) by means of a variable subsystem, namely a configuration set for simulation and a configuration set for code generation. The variable Subsystem module contains both a Subsystem module and a Model module as variant systems, including Inport, outport and Connection Port modules. The variable subsystem is associated with variant control items created in the global workspace. The variant control determines which variant system is active. The variant control item is designed as an expression of a specified condition, and the active variant is determined by the variant control item with a calculation result of true. The two configuration sets and the model are stored in the same file, and the configuration content can be checked and modified, so that decoupling of two functions of model simulation and code generation is realized in one set of model.
The embodiment of the application provides a model-based test method for spacecraft integrated electronic software, which comprises the following specific processes:
setting a variable subsystem in the model as a simulation mode, carrying out model on-loop test on the comprehensive electronic model of the spacecraft, simulating to verify the correctness of the model, packaging the received CADU data in a front-end communication model, transmitting the packaged CADU data to ground remote-sensing remote-control main control software for display after protocol conversion, simultaneously, receiving data uploaded by the ground remote-sensing remote-control main control software by the front-end communication model, analyzing a remote-control instruction according to a stipulated protocol, transmitting the remote-control instruction to the comprehensive electronic model for execution, and checking the correctness of the model function through the model on-loop test.
And finally, setting a variable subsystem in the model as a code generation mode, generating a code for hardware-in-loop testing by the comprehensive electronic model through a code automatic tool according to a pre-reserved software call interface, integrating a script with a hardware driver and an operating system interface, directly downloading the code to comprehensive electronic hardware equipment or virtual simulation software for running after compiling, and carrying out hardware-in-loop testing of the model.
The ground telemetry remote control master control software telemetry analysis configuration, remote control instruction data and test cases can multiplex the existing test cases of the model ring test in the last step.
The ground telemetry remote control main control software used for uploading remote control instructions and analyzing telemetry frames in the implementation steps of the invention is an example software, but the invention is not limited to the software, and any ground software needing to be communicated with the spacecraft integrated electronic device can be directly communicated with the spacecraft integrated electronic software model by adopting a mode similar to a protocol conversion model of a front-end communication model based on the thought in the invention.
The TCP/IP connection mode used for establishing connection between the ground telemetry and remote control main control software and the spacecraft comprehensive electronic software model in the steps of the invention is an example connection mode, but the invention is not limited to the network communication protocol, and any connection protocol (such as UDP/IP and the like) needing to be communicated with the spacecraft comprehensive electronic equipment can be used for carrying out protocol simulation connection through a similar front-end communication model based on the thought in the invention.
What is not described in detail in the present specification is a well known technology to those skilled in the art.
In summary, the above is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A model-based test system for spacecraft integrated electronic software, comprising: a front-end communication model; the front-end communication model is a variable subsystem which is controlled by a variant control item to be in model on-loop verification or hardware on-loop verification;
when the variable subsystem is in the loop verification of the model, packaging data received by the spacecraft comprehensive electronic software model, transmitting the data to the ground telemetry and remote control master control software for display after protocol conversion, receiving data uploaded by the ground telemetry and remote control master control software, analyzing a remote control instruction according to a stipulated protocol, and transmitting the data to the spacecraft comprehensive electronic software model for execution;
when the variable subsystem is in hardware-in-loop verification, a spacecraft comprehensive electronic software model is used for generating a code for hardware-in-loop test through a code automatic tool according to a software call interface reserved in advance, the code is integrated with a hardware driver and an operating system interface through a script, and the code is directly downloaded to spacecraft comprehensive electronic hardware equipment or virtual simulation software for running after compiling, so that the hardware-in-loop test of the model is performed.
2. The model-based test system for spacecraft integrated electronic software of claim 1, wherein said spacecraft integrated electronic software model comprises modeling of application function layer functions and is reserved with underlying hardware driver software and operating system software write interfaces.
3. The model-based test system for spacecraft integrated electronic software according to claim 1, wherein the variant control item is implemented by two configuration sets, a configuration set for simulation and a configuration set for code generation, respectively, the two configuration sets being stored in the same file as the front-end communication model, the front-end communication model being capable of viewing and modifying the contents of the two configuration sets.
4. The model-based test system for spacecraft integrated electronic software according to claim 1, wherein the telemetry parsing configuration, the remote control command data and the test cases of the ground telemetry remote control master control software can multiplex the existing test cases of the model in-loop verification.
5. The model-based test system for spacecraft integrated electronic software according to any one of claims 1-4, wherein said spacecraft integrated electronic software model and said front-end communication model are built using a Matlab/Simulink standard model-based development environment.
6. The model-based test system for spacecraft integrated electronic software according to claim 5, wherein the front-end communication model is connected with the ground telemetry and remote control master control software model through a TCP/IP network.
7. A model-based test method suitable for spacecraft integrated electronic software is characterized by comprising the following specific processes:
setting a variant control item, controlling a front-end communication model to be in a model ring test mode, packaging data sent by a spacecraft comprehensive electronic software model by the front-end communication model, transmitting the data to ground telemetry and remote control master control software for display after protocol conversion, receiving and analyzing a remote control instruction uploaded by the ground telemetry and remote control master control software, transmitting the remote control instruction to the spacecraft comprehensive electronic software model for execution, and checking the correctness of the model function through model ring test;
setting a variant control item, controlling a front-end communication model to be in a hardware-in-loop test mode, automatically generating codes of a spacecraft comprehensive electronic software model according to a pre-reserved software call interface by the front-end communication model, generating codes for hardware-in-loop test, integrating the codes with a hardware driver and an operating system interface through a script, directly downloading the codes to spacecraft comprehensive electronic hardware equipment or virtual simulation software to run after compiling, and checking the correctness of hardware functions through hardware-in-loop test.
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