CN108089975A - A kind of method of constructing environment Control System Software virtual testing environment - Google Patents

Abstract

The invention discloses a method for constructing a virtual testing environment for environment control system software, which belongs to the technical field of airborne system software testing. Including first constructing a comprehensive airborne electronic system network configuration including an environmental control system, and constructing an interface associated with the environmental control system, and then constructing a virtual target machine associated with the environmental control system to form an embedded operating system , and build simulation control and display modules according to the above-mentioned network configuration, and build a peripheral equipment model library, then set up the failure models of all systems, and develop a dynamic link library to form a connection with the environmental control system and the embedded operating system interface, and finally integrate auxiliary testing tools for black-box and white-box testing of environmental control system software. Through this method, in the virtual test environment or system, the test of the airborne software configuration items of the environmental control system can be independently and fully completed without being affected by the real operating environment of the flight tube system.

Description

A method for constructing a virtual testing environment for environmental control system software

technical field

The invention belongs to the technical field of airborne system software testing, in particular to a method for constructing a virtual testing environment for environment control system software.

Background technique

Integrated avionics system software and hardware integrated design technology has been widely used in various types of modern military and civilian aircraft. The environmental control system software (ECS software) realizes the centralized maintenance and management functions of each component system of the aircraft.

At present, the R&D mode of environmental control system software (ECS software) starts with the overall or outline design of the software, and then starts the hardware equipment to reach the delivery status, and then the software R&D and testing personnel carry out the software design and development and unit component testing, and the software Hardware system integration testing and validation.

Since the environmental control system software (ECS software) of the integrated avionics system has a great correlation with the hardware, the testing of software configuration items and system testing is heavily dependent on many airborne products or systems with interface cross-linking, resulting in embedded software development and The main problems in verification are as follows:

a) According to the traditional method, the environmental control system software (ECS software) configuration item test needs to wait for the development and testing of the relevant airborne system hardware equipment to be completed, and the airborne software test can only be carried out after the available hardware equipment is submitted work, resulting in prolongation of the entire project cycle;

b) During the testing phase of airborne software configuration items, due to limited hardware equipment resources or high cost of hardware equipment, the software testing project team cannot efficiently carry out relevant testing work;

c) Due to the design or prototype production problems in the early debugging stage of hardware equipment, it is impossible to effectively distinguish software or hardware failures when testing software configuration items, making software testing inefficient;

d) In the test and verification stage, based on the real hardware environment, it is difficult to fully test and verify through the hardware environment to deal with many abnormal situations (such as the failure mode of each member system or equipment) in the software design of the environmental control system;

e) In the stage of simultaneous testing and verification of multiple versions of software, since there is only one set of real hardware environment, an unfavorable situation is formed in order to test multiple versions of ECS software, and the same set of hardware test system competes for test resources at the same time;

f) Or, it often occurs that the only set of real hardware environment is developing and verifying the function of a certain version of ECS software, and the other version of ECS software cannot be tested at the same time, which delays the testing plan and software product installation plan on time;

g) Or, the only physical verification platform in the laboratory is in the state of troubleshooting airborne equipment in the field, and the ECS software test cannot be carried out at the same time, which delays the test plan and software product installation plan on time;

h) Further, in view of the status of multi-version ECS software installed in the field, fierce competition of test systems occurs at any time from all stages of development, testing, field troubleshooting, and internal and external testing.

Contents of the invention

In order to solve the above problems, the present invention provides a method for constructing a virtual test environment for environmental control system software, establishes a digital simulation environment for peripheral equipment associated with environmental control system software (ECS software), and integrates mature test analysis and management tools at the same time On this basis, the comprehensive testing method of white box testing, black box testing and static analysis of environmental control system software (ECS software) is carried out. The method mainly includes the following steps:

Step 1. Construct a comprehensive airborne electronic system network configuration including an environmental control system, the network configuration at least including:

The first part is composed of air conditioning system, hot air anti-icing system, air source system and pressure regulation system;

the second part consisting of the electronic equipment cooling system;

The third part consisting of the fault management subsystem;

The above systems are connected through the bus;

Step 2. Build the interfaces associated with the environmental control system, the interfaces include computing data interfaces, control interfaces, operating system interfaces, CPU programming interfaces, BSP board-level interfaces, and the network configuration in step one each system interface;

Step 3, build a virtual target machine associated with the environmental control system, develop CPU instructions, BSP board-level chips, I/O, interrupt, clock simulation functions, and form an embedded operating system;

Step 4, using Ethernet to simulate the distributed data bus, so that according to the test requirements, the peripheral simulation components related to the environmental control system software can dynamically join or exit the virtual test environment;

Step 5. According to step 1, build a simulation control and display module, and construct a first peripheral equipment model library including each system in the first part, a second peripheral equipment model library including each system in the second part, including a third peripheral device model library for each system in the third part;

Step 6. Establish failure models of all systems in step 5;

Step 7, developing the dynamic link libraries of all systems in step 5, and forming interfaces with the environmental control system and the embedded operating system;

Step 8: Integrate auxiliary testing tools for black-box and white-box testing of the environmental control system software.

Preferably, in the first step, the bus includes at least one of 429 bus, RS422 bus or 1553B bus.

Preferably, in the first step, the environment control system includes a first environment control system and a second environment control system for backup, and both the first environment control system and the second environment control system include dual channels.

Preferably, the dual channels in the first environmental control system are connected to each other through the HB6096 bus, the dual channels in the second environmental control system are connected to each other through the HB6096 bus, and the first environmental control system and The second environmental control system is connected through the HB6096 bus, and is connected to the avionics system through the HB6096 bus.

Preferably, the first environment control system and the second environment control system are connected to the electromechanical management system through the GJB289A bus.

Preferably, in the step seven, after forming the interface with the environmental control system and the embedded operating system, it further includes classifying or optimizing the combination of the interface, and placing several plug-ins that implement different functions into the same project , to enable simultaneous multiple peripheral emulation.

Preferably, in the eighth step, the auxiliary testing tools include coverage testing tools, static analysis tools, debuggers and development tools.

The advantages of the present invention are:

a) For the first time, a virtual test environment for airborne software with complex functions is provided to meet the needs of ECS software to complete configuration item testing (saving time, money and personnel, and flexibly arranging test plans);

b) Various test analysis and management tools are included in the virtual test environment, and at the same time, it can meet the static analysis/dynamic test, white box test/black box test methods of ECS software;

c) In the virtual test environment, not only the normal function model library of the peripheral equipment of the whole system is established, but also the fault model library is established to meet the execution test requirements of all normal, boundary and abnormal test cases in the testing process of ECS software configuration items;

d) Because of the establishment of the normal function model library of the peripheral equipment of the whole system, and the establishment of the fault model library, according to the configuration of other types of aircraft on-board electronic systems in the future, it can be effectively cut and optimized or expanded to meet the needs of other special aircraft models The environment controls the testing requirements of on-board software.

e) On this virtual test system, several new or upgraded versions of environmental control system software (ECS software) of various series of subsequent military and civilian aircraft can also be tested, which greatly saves money, time and human resources.

Description of drawings

Fig. 1 is the environmental control system network configuration schematic diagram of a preferred embodiment of the method for constructing the environment control system software virtual test environment of the present invention;

Fig. 2 is the aircraft environmental control system-level interface diagram of the embodiment shown in Fig. 1 of the present invention;

Fig. 3 is the connection relationship diagram between the aircraft environmental control system and the avionics and electromechanical of the embodiment shown in Fig. 1 of the present invention;

FIG. 4 is an external interface diagram of the environmental control system of the embodiment shown in FIG. 1 of the present invention.

Detailed ways

In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.

In describing the present invention, it is to be understood that the terms "central", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", The orientations or positional relationships indicated by "top", "bottom", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying the Means that a device or element must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting the scope of the invention.

The technical solution of the present invention is to design a virtual test environment, including a virtual target machine system, a peripheral device normal function model library system, a peripheral device failure mode model library system, a distributed bus simulation network, and a test case injection, analysis and management system Etc., providing a virtual testing environment for efficient white-box testing/black-box testing and static analysis/dynamic testing for ECS software.

The method mainly includes the following steps:

Step 1. Construct a comprehensive airborne electronic system network configuration including an environmental control system, the network configuration at least including:

The first part is composed of air conditioning system, hot air anti-icing system, air source system and pressure regulation system;

the second part consisting of the electronic equipment cooling system;

The third part consisting of the fault management subsystem;

The above-mentioned systems are connected through a bus, refer to FIG. 1 .

It can be understood that the bus of the present invention includes a 429 bus, an RS422 bus or a 1553B bus. In alternative implementations, other buses are also included, which are described in detail in step 2.

Step 2. Build the interfaces associated with the environmental control system, the interfaces include computing data interfaces, control interfaces, operating system interfaces, CPU programming interfaces, BSP board-level interfaces, and the network configuration in step one each system interface.

In this embodiment, the environment control system includes a first environment control system and a second environment control system for backup, and both the first environment control system and the second environment control system include dual channels. As shown in Figure 2, it is an aircraft environmental control system-level interface relationship diagram. The ECSC1A software is the software in the first channel of the first environmental control system in this embodiment, and it communicates with the second channel of the first environmental control system through the HB6096 bus. The software (ECSC1B) communicates with the software (ECSC2A) in the first channel of the second environmental control system through the HB6096 bus. The difference is that it communicates with the software (ECSC2B) in the first channel of the second environmental control system through the GJB289A bus. ) communication, which can be combined with Figure 3, the four channels can communicate with each other through the GJB289A bus, and carry out two-way communication with the electromechanical comprehensive management computer EMP in the electromechanical management system and the data acquisition computer DAP. Similarly, the GJB289A bus can also communicate with the power supply The power supply control management computer EPMC in the control management subsystem and the landing gear retraction and position indication control unit PDCU in the position indication subsystem perform two-way communication. Returning to Figure 2, in this embodiment, ECSC1A also passes The HB6096 bus communicates with the cockpit exhaust valve and the cargo compartment exhaust valve, communicates with the pressure sensors in the cockpit and cargo compartment through the RS422 bus, and the rest of the signals can be connected through ordinary hard wires.

Here, the hard wire is, for example, a wire for transmitting discrete analog signals.

In this embodiment, as shown in FIG. 3 , the first environment control system is connected to the second environment control system through the HB6096 bus, and is connected to the avionics system through the HB6096 bus. It is mainly connected to the flight accident record acquisition unit FDAU and the air data machine ADC of the avionics system, while other systems in the avionics system (such as the engine information warning system EICAS; the integrated warning system CAS; the multi-function display MFD; the central maintenance system CMS ) is preferentially connected to the electromechanical management system through the avionics bus, and then as mentioned above, the electromechanical management system is connected to the integrated controller of the environmental control system with dual redundancy through the GJB289A bus.

As shown in Figure 4, the environmental control system is connected to the display hardware through a display interface, connected to the control hardware through a control interface (such as an input and output interface), connected to an operating system (such as an RTOS system) through an operating system interface, and connected to an operating system (such as an RTOS system) through a CPU programming interface. Connect the processor hardware, connect the BSP board-level hardware through the BSP board-level interface (such as the BIT interface), and connect the electromechanical and avionics systems through the bus interface.

It should be noted that, in this embodiment, since the environmental control subsystem adopts discrete quantity control, it belongs to the control hardware and is connected through a control interface.

Step 3: Construct a virtual target machine associated with the environmental control system, develop CPU instructions, BSP board-level chips, I/O, interrupts, and clock simulation functions to form an embedded operating system.

The virtual core of the target processor is interconnected with various control hardware, storage hardware, and board-level hardware through a distributed data bus, and finally realizes the function of the embedded CPU on the virtual target machine.

Step 4: Use Ethernet to simulate the distributed data bus, so that the peripheral simulation components related to the environmental control system software can dynamically join or exit the virtual test environment according to the test requirements.

Step 5. According to step 1, build a simulation control and display module, and construct a first peripheral equipment model library including each system in the first part, a second peripheral equipment model library including each system in the second part, including A third peripheral device model library for each system in the third part.

It can be understood that the design simulation control and display module is the simulation control and display center of the entire virtual test environment, and can configure the entire environmental control system software (ECS software) related test system; dynamically and visually display each ECS software test case The data of the execution process can be managed and selected to record the data of each test case and saved. In the present embodiment, set up peripheral equipment model storehouse 1, and model storehouse comprises the system model (normal function) of air source system, air-conditioning system, hot air anti-icing system, cockpit pressure control system, adopts the atmospheric environment simulation tool of flight, realizes the aircraft The operation control of the atmospheric environment meets the functional requirements of ECS software and avionics and electromechanical systems, and establishes a peripheral equipment model library 2. The model library includes electronic equipment cooling system related models (normal functions), and meets the ECS software and electronic equipment cooling system related functions. Requirements, establish a peripheral equipment model library 3, the model library includes the fault management subsystem, and meets the functional requirements of the ECS software and the fault management subsystem.

Step 6. Based on the above peripheral equipment model libraries 1, 2, and 3, establish fault models of all the above systems and manage them centrally to meet the ECS software system test boundary and fault case test execution requirements.

Step 7, develop the dynamic link library of all systems in step 5, and form the interface with described environmental control system and described embedded operating system; In the present embodiment, develop above each subsystem dynamic link library (dll), and Form a standard interface with ECS software and embedded operating system, and then classify or optimize the combination, and place several plug-in dlls that implement different functions into the same project, which can realize multiple peripheral device simulations at the same time.

Step 8. Comprehensively integrate auxiliary testing tools, including coverage testing tools (testbed software), static analysis tools (COBOT Kubo software), debuggers, development tools (LabView), etc., and conduct black-box testing of combat flight software in a virtual test environment At the same time, it is also able to conduct testing processes such as white box testing, static analysis and software quality measurement.

On the basis of the above, build the ECS software testing system application platform and set up a laboratory for virtual environment testing.

The present invention builds a fully digital virtual test environment associated with the environmental control system software (ECS software), which is composed of a virtual target machine, a member system simulator, a fault injection and management simulator, and test case management and analysis equipment. The system has the following characteristics.

a) In this virtual test environment or system, it can independently and fully complete the test of the airborne software configuration items of the environmental control system, without being affected by the real operating environment of the flight tube system;

b) The tester does not need to rely on real ECS software airborne computer equipment (target machine) and real airborne member system equipment and environmental stimulus equipment;

c) The virtual test environment or system can cover the normal functions and abnormal and failure mode functions required by all member systems associated with the environmental control system. The test results are certain, the selected test principles are reasonable, and there will be no test results that cannot be judged. Case;

d) The digital or virtual test environment or system constructed by this method can fully test or verify the correctness and integrity of the functional design of the environmental control system software (ECS software).

Finally, it should be pointed out that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: they can still modify the technical solutions described in the aforementioned embodiments, or perform equivalent replacements for some of the technical features; and these The modification or replacement does not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims (7)

1. A method for constructing an environment control system software virtual testing environment, characterized in that, comprising: Step 1. Construct a comprehensive airborne electronic system network configuration including an environmental control system, the network configuration at least including: The first part is composed of air conditioning system, hot air anti-icing system, air source system and pressure regulation system; the second part consisting of the electronic equipment cooling system; The third part consisting of the fault management subsystem; The above systems are connected through the bus; Step 2. Build the interfaces associated with the environmental control system, the interfaces include computing data interfaces, control interfaces, operating system interfaces, CPU programming interfaces, BSP board-level interfaces, and the network configuration in step one each system interface; Step 3, build a virtual target machine associated with the environmental control system, develop CPU instructions, BSP board-level chips, I/O, interrupt, clock simulation functions, and form an embedded operating system; Step 4, using Ethernet to simulate the distributed data bus, so that according to the test requirements, the peripheral simulation components related to the environmental control system software can dynamically join or exit the virtual test environment; Step 5. According to step 1, build a simulation control and display module, and construct a first peripheral equipment model library including each system in the first part, a second peripheral equipment model library including each system in the second part, including a third peripheral device model library for each system in the third part; Step 6. Establish the failure models of all systems in step 5; Step 7, developing the dynamic link libraries of all systems in step 5, and forming interfaces with the environmental control system and the embedded operating system; Step 8: Integrate auxiliary testing tools for black-box and white-box testing of the environmental control system software. 2. The method for constructing a virtual test environment for environmental control system software according to claim 1, wherein in said step one, said bus includes at least one of 429 bus, RS422 bus or 1553B bus. 3. the method for building environment control system software virtual test environment as claimed in claim 1, is characterized in that, in described step 1, environment control system comprises the first environment control system and the second environment control system for backup, Both the first environment control system and the second environment control system include dual channels. 4. the method for constructing the environment control system software virtual test environment as claimed in claim 3, is characterized in that, the dual channels in the first environment control system are connected to each other by the HB6096 bus, and the second environment control system The dual channels inside are connected to each other through the HB6096 bus, the first environment control system and the second environment control system are connected through the HB6096 bus, and are connected to the avionics system through the HB6096 bus. 5. The method for constructing a virtual testing environment for environmental control system software according to claim 3, wherein the first environmental control system and the second environmental control system are connected to the electromechanical management system through the GJB289A bus. 6. the method for building environment control system software virtual test environment as claimed in claim 1, is characterized in that, in described step 7, after forming the interface with described environment control system and described embedded operating system, further comprise to Classify or optimize the combination of interfaces, and place several plug-ins that implement different functions into the same project to realize multiple peripheral device simulations at the same time. 7. the method for building environment control system software virtual test environment as claimed in claim 1, is characterized in that, in described step 8, described auxiliary test tool comprises coverage test tool, static analysis tool, debugger and development tool .