General electric test platform and method based on mbse

Abstract

This invention discloses a general-purpose electrical test platform and method based on MBSE (Medium-Range Execution System), including a real-time simulator, a bus interface, a data acquisition and control interface module, a boundary testing and fault injection module, a test power supply module, a test load module, and an interface adapter. The real-time simulator is equipped with a real-time operating system for solving test program sets and test stimulus models, and for real-time resource scheduling based on the solution results. The bus interface is connected to the real-time simulator at one end and to the interface of the airborne system under test at the other end. The data acquisition and control interface module is also connected to the real-time simulator at one end and to the interface of the airborne system under test at the other end. The test power supply module is connected to the power input interface of the airborne system under test. The test load module is connected to the output interface of the airborne system under test. This invention reduces the manpower, time, and capital investment required for building test models, improves asset utilization, and reduces the maintenance and management costs of the electrical test platform.

Description

Technical Field

[0001] This invention relates to the field of aviation electrical testing technology, and more specifically, to a general electrical testing platform and method based on MBSE. Background Technology

[0002] Generally speaking, aircraft systems mainly include flight control systems, avionics systems, and electromechanical systems. Among them, electromechanical systems include electromechanical control and management, power, hydraulics, landing gear, fuel, fire protection, environmental control, life-saving, power supply, and external lighting systems, involving disciplines such as mechanics, hydraulics, heat, fluid dynamics, electrical engineering, and lighting.

[0003] Electrical engineering is a common discipline. The aircraft power supply system provides power supply and distribution for the entire aircraft system. Systems such as power, hydraulics, landing gear, fuel, fire protection, environmental control, and lighting all contain corresponding electrical subsystems, performing electrical signal acquisition and electrical control management functions. Electromechanical control management collects information from various electromechanical subsystems, performs integrated control and information fusion, and interconnects with avionics and flight control systems. It can be seen that in aircraft system design, electrical design involves highly complex interconnections at the component, system, functional, and information levels, with a high degree of coupling between systems. As aircraft develop towards more electric / fully electric directions, including with the development of electric aircraft (Evtol), the importance of electrical engineering has further increased. The functions, performance, reliability, and safety of electrical systems are directly related to aircraft safety; therefore, the testing and evaluation of airborne systems and systems under test related to electrical design are crucial.

[0004] The current status of electrical testing and inspection at aircraft mainframe manufacturers and the research and development units of the airborne systems under test is as follows:

[0005] (1) The research and development unit of the airborne system under test shall, in accordance with the equipment technical agreement and design scheme, invest human, time and financial resources to develop the corresponding equipment testing device and test the product samples (including digital models and physical objects) of the airborne system under test at each stage. Since the requirements and design schemes of the airborne system under test vary for different aircraft, the corresponding equipment testing device is often also dedicated.

[0006] (2) At the system level, the aircraft main unit, in accordance with the overall development requirements and system design scheme, proposes technical modification and infrastructure construction plans and applies for funding from higher authorities. After funding is approved, a system-level test model is built to conduct system integration tests during the design phase, prototype system integration tests, and formal prototype system integration tests. The application, approval, and investment in technical modification plans all require significant human, time, and financial resources. Different aircraft models often have different system design technologies; therefore, the system-level test model is tightly coupled with the model and exhibits specialized characteristics.

[0007] The aforementioned airborne system-level equipment testing devices and system-level test models are all included in the scope of fixed asset management. If they are dedicated and not general-purpose, the asset utilization rate is low, and long-term maintenance and management costs are required. In summary, both the main and auxiliary units have invested a lot of human, time, and financial resources to conduct system-level and equipment-level electrical tests, resulting in low asset utilization and high maintenance and management costs. Therefore, this is a technical problem that urgently needs to be solved in this field.

[0008] Prior art (application date: 2021102137704, application date: 2021.02.25) discloses an aircraft 1394B bus communication simulation test platform. Figure 1 This is a general diagram of the 1394b bus 3CC network topology in an aircraft 1394b bus communication simulation test platform provided by existing technology; see [link / reference]. Figure 1 As shown, the aircraft 1394B bus communication simulation test platform includes a simulation computer as the system operating platform, peripheral devices connected to the simulation computer for auxiliary testing, and a communication platform connected to the simulation computer and peripheral devices via a 1394 bus network for collecting and sending bidirectional communication messages. An extension section, connected to the communication platform via a 1394 bus network, is an auxiliary module added to meet testability and improve test coverage. This solution only involves the 1394 bus network and does not involve other resources; therefore, it does not solve the aforementioned technical problems. Summary of the Invention

[0009] In view of this, the present invention provides a general electrical test platform based on MBSE to solve the problems in the prior art where both main and auxiliary units invest a lot of manpower, time and financial resources to carry out system-level and equipment-level electrical tests, resulting in low asset utilization and high maintenance and management costs.

[0010] In a first aspect, the present invention provides a general electrical test platform based on MBSE, including a real-time simulator, a bus interface, an acquisition and control interface module, a boundary test and fault injection module, a test power supply module, a test load module, and an interface adapter;

[0011] The real-time simulator is equipped with a real-time operating system, which is used to solve the test program set and test stimulus model, and to schedule resources in real time according to the solution results to complete the test tasks of the airborne system under test. The resources include the bus interface, the acquisition and control interface module, signal injection, the test power supply module and the test load module. The test tasks of the airborne system under test include power allocation, command control, signal acquisition, boundary signal injection and fault signal injection.

[0012] The bus interface is connected at one end to the real-time simulator and at the other end to the interface of the airborne system under test, in order to meet the bus communication test requirements of the airborne system under test.

[0013] The acquisition and control interface module is connected at one end to the real-time simulator and at the other end to the interface of the airborne system under test (SUT), used to meet the command control and signal testing requirements of the SUT during testing. The acquisition and control interface module includes a discrete quantity interface, a voltage analog quantity interface, a current analog quantity interface, a resistance analog quantity interface, an open quantity interface, and a signal conditioning resource interface. Specifically, the discrete quantity interface processes discrete digital signals from the SUT; the voltage analog quantity interface acquires and controls the voltage signals of the SUT; the current analog quantity interface acquires and controls the current signals of the SUT; the resistance analog quantity interface acquires changes in the resistance value of the SUT; the open quantity interface receives and sends the switching status signals of the SUT; and the signal conditioning resource interface conditions the analog signals input to the SUT.

[0014] The boundary testing and fault injection module is used to test the working capability of the airborne system under test under boundary extreme conditions and to detect the environmental adaptability and fault detection of the airborne system under test.

[0015] The test power module is connected to the power input interface of the airborne system under test and is used to simulate a power generation system to provide power to the airborne system under test.

[0016] The test load module is connected to the output interface of the airborne system under test and is used to simulate electrical equipment as a simulated load for the airborne system under test, and to detect the load and overload protection of the airborne system under test.

[0017] The interface adapter is used to organize the corresponding interfaces of the real-time simulator, the bus interface, the acquisition and control interface module, the boundary test and fault injection module, the test power supply module, and the test load module, and connect them to the interface adapter box.

[0018] Optionally, the discrete quantity interface includes a discrete quantity input interface and a discrete quantity output interface, wherein the discrete quantity input interface is used to receive discrete signals from the airborne system under test, and the discrete quantity output interface is used to send discrete signals to the airborne system under test.

[0019] The voltage analog quantity interface includes a voltage analog quantity input interface and a voltage analog quantity output interface. The voltage analog quantity input interface is used to acquire voltage signals from the airborne system under test, and the voltage analog quantity output interface is used to output control signals or excitation signals to the airborne system under test.

[0020] The signal conditioning resource interface includes a voltage signal conditioning resource interface and a current signal conditioning resource interface, wherein the voltage signal conditioning resource interface is used to process voltage signals and the current signal conditioning resource interface is used to process current signals.

[0021] Optionally, the interface adapter includes a bus communication interface adapter, a data acquisition and control interface adapter, and a power supply interface adapter;

[0022] The real-time simulator and the bus interface are respectively adapted to be connected to the airborne system under test through the bus communication interface;

[0023] The acquisition and control interface module is connected to the airborne system under test through a portion of the acquisition and control interface adapter; the boundary test and fault injection module, test load module and test power supply module are connected to the test interface through another portion of the acquisition and control interface adapter.

[0024] The acquisition and control interface module is connected to the airborne system under test through a portion of the power supply interface adapter, and the boundary test and fault injection module, the test load module and the test power supply module are connected to the test interface through another portion of the power supply interface adapter.

[0025] Secondly, a general electrical testing method based on MBSE is applied to a general electrical testing platform based on MBSE, wherein the general electrical testing platform based on MBSE is the aforementioned general electrical testing platform based on MBSE. The interface resources are determined according to the interface type, quantity, function and performance parameters of the airborne system under test, and the interface resources of the general electrical testing platform are allocated.

[0026] A test program set and a test stimulus model are developed on a host computer, the test program set and the test stimulus model including an interface driver;

[0027] Test cables are fabricated according to the interface type and quantity of the airborne system under test, wherein the test cables include bus cables, signal cables and power cables;

[0028] The host computer downloads and deploys the test program set and the test stimulus model to the real-time operating system in the real-time simulator via Ethernet. The real-time simulator, the bus interface, the acquisition and control interface module, the boundary test and fault injection module, the test power supply module, and the test load module are respectively connected to the airborne system under test via the test cable.

[0029] Based on the test program set and the test stimulus model, the real-time simulator, the bus interface, the acquisition and control interface module, the boundary test and fault injection module, the test power supply module and the test load module are driven to test the airborne system under test.

[0030] Compared with the prior art, the MBSE-based general electrical test platform and method provided by the present invention achieves at least the following beneficial effects:

[0031] First, by using a general electrical test platform based on MBSE, real-time and universal electrical test resources are used to build the platform. This general electrical test platform is decoupled from and not directly related to the specific airborne system under test. Different airborne systems under test can reuse these test resources, reducing the manpower, time and capital investment required to build test models, improving asset utilization and reducing the maintenance and management costs of the electrical test platform.

[0032] Second, during the research and development and testing of the airborne system under test, the hardware is physically "fixed and immovable"; the only parts that "change and move" are the test stimulus model (such as the simulation model), the test program set, and the physical connection cables between the airborne system under test and the interface adapter box. When the design of the airborne system under test is changed, the "change and move" parts, namely the test program set, the test stimulus model, and the test cables, can be quickly modified and adjusted, thereby improving the efficiency of testing.

[0033] Third, when different airborne systems under test are being developed and tested, the corresponding test stimulus model (such as simulation model) and test program set can be downloaded to the real-time simulator, and the corresponding test cable can be used to connect the airborne system under test. This enables the switching of R&D and testing for different airborne systems under test, and realizes the staggered and parallel R&D and testing of multiple models of airborne systems under test.

[0034] Fourth, this fault injection resource can be combined with boundary test excitation software to perform electrical boundary tests, such as voltage disturbances, signal disturbances, level boundary tests, and software boundary tests; and combined with fault injection excitation software to perform fault injection tests, such as open circuit faults, short circuit faults, error signals, phase sequence reversal, spike injection, and surge injection, thereby expanding the scope of testing and increasing the depth of testing.

[0035] Fifth, through the mutual coordination of discrete quantity interfaces, voltage analog quantity interfaces, current analog quantity interfaces, resistance analog quantity interfaces, open quantity interfaces, and signal conditioning resource interfaces, the acquisition and control interfaces of the GE test platform are jointly constituted. This enables the GE test platform to flexibly adapt to different types of airborne systems under test and to realize the measurement and control of various electrical parameters. When designing the GE test platform, it is necessary to select appropriate interfaces according to the test requirements and ensure their compatibility and coordination to achieve an efficient and accurate testing process.

[0036] Of course, any product implementing this invention does not necessarily need to achieve all of the technical effects described above at the same time.

[0037] Other features and advantages of the invention will become clear from the following detailed description of exemplary embodiments of the invention with reference to the accompanying drawings. Attached Figure Description

[0038] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments of the invention and, together with their description, serve to explain the principles of the invention.

[0039] Figure 1 This is a general diagram of the 1394b bus 3CC network topology in an aircraft 1394b bus communication simulation test platform provided by existing technology;

[0040] Figure 2 This is an architecture diagram of the MBSE-based general electrical test platform provided by the present invention;

[0041] Figure 3 This is a flowchart of the MBSE-based general electrical test method provided by the present invention;

[0042] Figure 4 This is a schematic diagram of the electrical principle of an aircraft power supply system provided by the present invention;

[0043] Figure 5 This is a schematic diagram of the data simulation model of an aircraft power supply system provided by the present invention;

[0044] Figure 6 This is a test case diagram of a power supply processing device under test provided by the present invention;

[0045] Figure 7 This is a test case diagram of a power distribution device under test provided by the present invention. Detailed Implementation

[0046] Various exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be noted that, unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention.

[0047] The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the invention or its application or use.

[0048] Techniques, methods, and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and equipment should be considered part of the specification.

[0049] In all the examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values.

[0050] It should be noted that similar labels and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be discussed further in subsequent figures.

[0051] Example 1

[0052] Figure 2 This is an architecture diagram of the MBSE-based general electrical test platform provided by this invention; see also Figure 2 As shown, this embodiment provides a general electrical test platform based on MBSE, including a real-time simulator, a bus interface, an acquisition and control interface module, a boundary test and fault injection module, a test power supply module, a test load module, and an interface adapter;

[0053] The real-time simulator is equipped with a real-time operating system, which is used to solve the test program set and test stimulus model, and to schedule resources in real time according to the solution results to complete the test tasks of the airborne system under test. The resources include bus interface, acquisition and control interface module, signal injection, test power supply module and test load module. The test tasks of the airborne system under test include power distribution, command control, signal acquisition, boundary signal injection and fault signal injection.

[0054] The bus interface, with one end connected to the real-time simulator and the other end connected to the interface of the airborne system under test, is used to meet the bus communication test requirements of the airborne system under test.

[0055] The acquisition and control interface module connects to the real-time simulator on one end and to the interface of the airborne system under test (SUT) on the other. It is used to meet the command control and signal testing requirements of the SUT during testing. The acquisition and control interface module includes discrete quantity interfaces, voltage analog quantity interfaces, current analog quantity interfaces, resistance analog quantity interfaces, open quantity interfaces, and signal conditioning resource interfaces. The discrete quantity interfaces process discrete digital signals from the SUT; the voltage analog quantity interfaces acquire and control voltage signals from the SUT, such as voltage signals output by sensors or voltage signals requiring control; the current analog quantity interfaces acquire and control current signals from the SUT; the resistance analog quantity interfaces acquire changes in resistance values ​​from the SUT; the open quantity interfaces receive and send switching status signals from the SUT; and the signal conditioning resource interfaces condition the analog signals input to the SUT.

[0056] The boundary testing and fault injection module is used to test the working ability of the airborne system under test under boundary extreme conditions, as well as to detect the environmental adaptability and fault detection of the airborne system under test.

[0057] The test power module is connected to the power input interface of the airborne system under test and is used to simulate the power generation system to provide power to the airborne system under test.

[0058] The test load module is connected to the output interface of the airborne system under test. It is used to simulate electrical equipment and serve as a simulated load for the airborne system under test to detect the load and overload protection of the airborne system under test.

[0059] The interface adapter is used to organize the corresponding interfaces in the real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power supply module and test load module, and connect them to the interface adapter box.

[0060] Specifically, continue to refer to Figure 2 As shown, the MBSE-based general electrical test platform described above can be an MBSE-based general electrical test platform, which includes a real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power supply module, test load module, and interface adapter. Using the MBSE (Model-Based Systems Engineering)-driven general electrical hardware-in-the-loop test platform can significantly improve test efficiency, accuracy, and flexibility, providing strong support for the research and development and testing of electrical systems.

[0061] The aforementioned real-time simulator is the core of this GE test platform. Its main function is to solve the test program set and test stimulus model, and based on the solution results, to perform real-time scheduling of resources such as the bus interface, acquisition and control interface modules, signal injection, test power supply module, and test load module. This completes test tasks such as power allocation, command control, signal acquisition, boundary signal injection, and fault signal injection for the airborne system under test. Currently, there are many types of commercially available real-time simulators. When selecting a real-time simulator, based on the technical requirements of the airborne system under test, the core selection indicators include real-time performance, model solution scale, simulation data accuracy, internal bus interface type, supported modeling software and languages, and scalability. In this embodiment, the NIPXIe-8881 high-performance 8-core controller module, equipped with a real-time operating system, can be selected as the control core. It should be noted that the aforementioned airborne system under test includes the airborne equipment under test.

[0062] The aforementioned test program set is a general-purpose test program set designed for the GE test platform. This test program set integrates software such as real-time operating system and hardware drivers, and uses this software to configure and manage the interface resources of each component of the GE test platform. The aforementioned test stimulus model is constructed using Matlab / Simulink and C language, and uses software to drive each hardware module in the GE test platform to provide the signal stimulus required by the airborne system under test, simulate the operating environment of the airborne system under test, and simulate the interconnection equipment and system environment of the airborne system under test.

[0063] Matlab / Simulink, mentioned above, is an integrated development environment (IDE) launched by MathWorks, primarily used for mathematical computation, algorithm development, data visualization, and modeling and simulation of dynamic systems. Matlab is a high-level technical computing language and interactive environment, while Simulink is a visualization and simulation tool within Matlab, used for multi-domain simulation and model-based design.

[0064] The C language mentioned above is a general-purpose programming language. In the construction of test stimulus models, C language can be used to implement the stimulus signal generation algorithm designed in Matlab / Simulink.

[0065] The aforementioned bus interface is a key component connecting the GE test platform and the airborne system under test (SUT). It is used to meet the bus communication testing requirements of the SUT. Specifically, this bus interface is responsible for data transmission and communication between the GE test platform and the SUT, ensuring the accurate transmission and reception of test signals. Through the bus interface, the GE test platform can obtain various parameters and status information of the SUT, thereby enabling comprehensive and accurate testing and analysis of the SUT.

[0066] Currently, commonly used bus types for airborne systems under test include 1553 bus, 1394 bus, AFDX (Avionics Full-Duplex Switched Ethernet) bus, CAN (Controller Area Network) bus, 429 bus, and 629 bus. These buses generally have commercially available boards to choose from, and bus boards can be selected, configured, and subsequently expanded based on the airborne system under test.

[0067] The aforementioned 1553 bus is widely used as an airborne bus standard in the aviation field, characterized by high reliability, real-time performance, and flexibility. The 1394 bus, also known as FireWire, is a high-speed serial bus standard primarily used for data transmission and multimedia applications, and is also used in some airborne equipment. The AFDX bus is an avionics full-duplex switching network based on Ethernet technology, featuring high bandwidth, low latency, and strong real-time performance, and is an important component of modern avionics systems. The CAN bus is a widely used fieldbus standard, renowned for its high reliability and flexibility. The 429 bus is a digital data bus standard widely used in civil aviation for transmitting flight parameters and status information. The 629 bus is an airborne bus type used in specific fields or applications. These buses are suitable for different airborne equipment and application scenarios. In the GE test platform, it is necessary to select the appropriate bus interface and bus type according to specific test requirements and airborne equipment types to ensure the smooth progress of testing.

[0068] The data acquisition and control interface module includes data acquisition and control interface resources to meet the command control and signal testing requirements of the airborne system under test (SUT). Specifically, this module enables precise control and effective signal acquisition of the SUT. It sends various control commands, such as start, stop, and parameter adjustment, to the SUT. These commands ensure the SUT operates according to predetermined procedures and requirements during testing, enabling a comprehensive performance evaluation. The module also receives and processes various signals generated by the SUT during testing, such as voltage, current, frequency, and temperature. Through real-time acquisition and analysis of these signals, the GE test platform can obtain the SUT's operating status, performance parameters, and potential fault information, providing strong support for subsequent fault diagnosis and performance optimization.

[0069] Continue to refer to Figure 2As shown, the discrete signal interface converts discrete digital signals (such as dry contact, wet contact, and voltage signals) into a digital format that can be recognized and processed by a general-purpose electrical test platform for subsequent analysis and testing. The discrete signal interface also features electrical isolation to prevent electrical interference from affecting the airborne system under test (SUT), and overvoltage and overcurrent protection to ensure the SUT is protected from damage under abnormal conditions. It not only processes discrete digital signals from the SUT but also provides electrical isolation and protection, while being easy to configure and integrate, greatly enhancing the convenience and reliability of electrical testing.

[0070] This discrete signal interface can be either a ground / open discrete signal interface or a 28V / open discrete signal interface. The ground / open discrete signal interface refers to two signal states: grounded and open. Grounding can refer to the aircraft's fuselage. This type of interface is used to acquire and control discrete signals with two states (such as on / off, present / absent). The 28V / open discrete signal interface indicates many operating states of the tested airborne system through 28V voltage and open-circuit states. The 28V voltage is not a stable value but a variable voltage ranging from 18 to 32V.

[0071] The aforementioned analog voltage interface can receive voltage signals transmitted by the airborne system under test. These signals are usually analog quantities. Through a real-time simulator, the received voltage signals are acquired and converted in real time, and then converted into digital signals for subsequent processing and analysis. It can not only accurately acquire the voltage signals of the airborne system under test, but also output corresponding control signals according to the test requirements, providing strong support for the testing and control of electrical systems.

[0072] The voltage analog interface can be a 0V to 10V voltage analog interface, another common analog signal transmission interface, used to transmit continuous voltage signals, with a signal range between 0V and 10V.

[0073] The aforementioned analog current interface can acquire current data from the airborne system under test in real time, providing a basis for subsequent monitoring, analysis and control. It can also output control signals to adjust the current magnitude or state in the airborne system under test according to test requirements.

[0074] The analog current interface can be a 4mA to 20mA analog current interface. The 4mA to 20mA analog current interface is a common analog signal transmission interface used to transmit continuous current signals with a signal range of 4mA to 20mA.

[0075] The aforementioned analog resistance interface can acquire the resistance value changes of the airborne system under test in real time, providing data support for subsequent testing and analysis. This analog resistance interface has the characteristics of high precision, stability and compatibility. For example, it can accurately reflect the small changes in resistance value, ensuring the accuracy of test results. It can maintain consistent acquisition effect during long-term testing, improving the reliability of testing. It is compatible with multiple resistance types and meets the testing needs of different airborne systems.

[0076] This analog resistance interface can be used for PT1000 resistors to acquire temperature signals from PT1000 RTDs and convert them into processable analog signals.

[0077] The analog resistance interface can also be a 900 to 3kΩ analog resistance interface, used to connect resistance sensors with resistance values ​​between 900 ohms and 3kΩ to acquire various analog signals, such as pressure and displacement.

[0078] The aforementioned open-type interface can receive switch status signals from the airborne system under test. These switch status signals typically include signals from passive switches (such as pushbuttons, contactor contacts, and limit switches) and active switches (such as proximity switches and transistor switching circuits). It can also send switch control signals to the airborne system under test to achieve remote control and monitoring of the switch status of the airborne system under test.

[0079] The aforementioned signal conditioning resource interface precisely conditions analog signals, eliminating noise and interference, improving the accuracy and reliability of testing, and supporting various types of analog signal inputs. This allows the test platform to adapt to the needs of different airborne systems under test, enhancing the flexibility of testing.

[0080] It should be noted that the acquisition and control interface module also includes other standard interfaces and expansion slots. These other standard interfaces and expansion slots enable the GE test platform to connect to various airborne systems under test, meet different testing needs, and improve the flexibility and applicability of the GE test platform.

[0081] The boundary testing and fault injection module includes boundary testing and fault injection resources. It is used to test the working capability of the airborne system under test under extreme boundary conditions, and to detect the environmental adaptability and fault detection of the airborne system under test by artificially injecting fault signals, so as to discover potential errors or instabilities. Specifically, by applying test stimuli such as voltage disturbances, signal disturbances, tolerance boundaries, level boundaries, open circuit faults, and short circuit faults, the operating boundaries, disturbance rejection capabilities, and fault-tolerant reconfiguration of the airborne system under test are tested.

[0082] Commonly used boundary testing and fault injection modules include commercially available boards such as signal generators and power amplifiers. These signal generators and power amplifiers are used to inject fault signals and monitor signals. They can be found on general-purpose electrical test platforms. The power and signal range of the power amplifier vary depending on the airborne system under test (SUT), and selection should be based on the requirements of the SUT. In other words, the specific selection of the aforementioned signal generators and power amplifiers must be based on the SUT and configured accordingly, with subsequent expansion configurations possible.

[0083] Boundary tests include voltage boundary tests, current boundary tests, and time boundary tests. Voltage boundary tests refer to the performance of the airborne system under test when the voltage approaches or exceeds the rated value, such as overvoltage protection and undervoltage protection. Current boundary tests refer to the response of the airborne system under test when the current reaches or exceeds the maximum allowable value, such as overcurrent protection and short-circuit protection. Time boundary tests refer to the stability of the airborne system under test during long-term operation or very short-term operation, such as long-term operation tests and fast switching tests.

[0084] Fault injection refers to the artificial introduction of faults into an airborne system under test (SUT) to assess its fault tolerance and recovery capabilities. In electrical testing, fault injection includes voltage disturbance injection, signal disturbance injection, tolerance boundary injection, level boundary injection, and open-circuit fault injection.

[0085] Voltage disturbance injection: Applying instantaneous voltage changes to the airborne system under test to simulate external disturbances such as power grid fluctuations or lightning strikes.

[0086] Signal disturbance injection: Abnormal signals, such as noise and interference signals, are input into the airborne system under test to test the signal processing capability and anti-interference capability of the airborne system under test.

[0087] Tolerance boundary injection: The performance of the airborne system under test under parameter tolerance boundary conditions, such as component parameter drift and temperature changes, to evaluate the stability and reliability of the airborne system under test.

[0088] Level boundary injection: The behavior of the airborne system under test when the level is close to or exceeds the logic threshold, such as high-low level transitions and logic judgments.

[0089] Open-circuit fault injection: Simulates an open-circuit fault in a circuit to test the response and fault location capabilities of the airborne system under test in the event of an open circuit.

[0090] Short-circuit fault injection: Simulates short-circuit faults in the circuit to test the protection mechanism and fault isolation capability of the airborne system under test under short-circuit conditions.

[0091] The aforementioned test power supply module includes a test power supply used to simulate a power generation system. It accurately simulates the power characteristics of an actual power generation system, providing the airborne system under test with power conditions close to the real operating environment. It also offers multiple power systems, such as 28VDC, 270VDC, 540VDC, and 115VAC, to meet the power requirements of different devices under test. Technically, the test power supply is programmable (supporting remote control and programming via computer to automate the testing process) and adjustable (parameters such as voltage and current can be finely adjusted according to testing needs to meet the requirements of different testing scenarios). The test power supply technology is mature and commercially available.

[0092] This test power supply module provides power to the airborne system under test, thus providing a stable and adjustable power supply. It is a key component in this system. The test power supply module is connected to the power input interface of the airborne system under test.

[0093] The test load module includes a test load that connects to the output interface of the airborne system under test. It is used to simulate electrical equipment and serve as a simulated load for the airborne system under test. It tests the load-bearing and overload protection performance of the airborne system under test. It can establish various power loads such as 28VDC, 270VDC, 540VDC and 115VAC that are matched with the test power supply. Typically, the above test loads are electronic loads or resistive loads, which are technically mature and commercially available.

[0094] The aforementioned interface adapter organizes the corresponding interfaces from the real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power supply module, and test load module, and connects them to one side of the interface adapter box. Using the "three-way" principle, these interfaces are "divided into two groups from one group." One group of interfaces is used to connect to the airborne system under test, and the other group of interfaces is used to connect to multimeters and oscilloscopes to achieve online testing.

[0095] The aforementioned real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power supply module, and test load module are connected to the interface adapter and the airborne system under test via test cables, providing a stable and reliable signal transmission channel to ensure accurate signal transmission and real-time data exchange.

[0096] The aforementioned real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power supply module, test load module and interface adapter are all market-standardized test resources, providing general test resources for electrical airborne systems. However, they are not customized or dedicated test resources strongly related to a certain type of airborne system under test, and therefore are general electrical test platforms.

[0097] Compared with existing technologies, the MBSE-based general electrical test platform provided in this embodiment achieves at least the following beneficial effects:

[0098] First, by using a general electrical test platform based on MBSE, real-time and universal electrical test resources are used to build the platform. This general electrical test platform is decoupled from and not directly related to the specific airborne system under test. Different airborne systems under test can reuse these test resources, reducing the manpower, time and capital investment required to build test models, improving asset utilization and reducing the maintenance and management costs of the electrical test platform.

[0099] Second, during the research and development and testing of the airborne system under test, the hardware is physically "fixed and immovable"; the only parts that "change and move" are the test stimulus model (such as the simulation model), the test program set, and the physical connection cables between the airborne system under test and the interface adapter box. When the design of the airborne system under test is changed, the "change and move" parts, namely the test program set, the test stimulus model, and the test cables, can be quickly modified and adjusted, thereby improving the efficiency of testing.

[0100] Third, when different airborne systems under test are being developed and tested, the corresponding test stimulus model (such as simulation model) and test program set can be downloaded to the real-time simulator, and the corresponding test cable can be used to connect the airborne system under test. This enables the switching of R&D and testing for different airborne systems under test, and realizes the staggered and parallel R&D and testing of multiple models of airborne systems under test.

[0101] Fourth, this fault injection resource can be combined with boundary test excitation software to perform electrical boundary tests, such as voltage disturbances, signal disturbances, level boundary tests, and software boundary tests; and combined with fault injection excitation software to perform fault injection tests, such as open circuit faults, short circuit faults, error signals, phase sequence reversal, spike injection, and surge injection, thereby expanding the scope of testing and increasing the depth of testing.

[0102] Fifth, through the mutual coordination of discrete quantity interfaces, voltage analog quantity interfaces, current analog quantity interfaces, resistance analog quantity interfaces, open quantity interfaces, and signal conditioning resource interfaces, the acquisition and control interfaces of the GE test platform are jointly constituted. This enables the GE test platform to flexibly adapt to different types of airborne systems under test and to realize the measurement and control of various electrical parameters. When designing the GE test platform, it is necessary to select appropriate interfaces according to the test requirements and ensure their compatibility and coordination to achieve an efficient and accurate testing process.

[0103] In one alternative embodiment, continue to refer to Figure 2As shown, the discrete quantity interface includes a discrete quantity input interface and a discrete quantity output interface. The discrete quantity input interface is used to receive discrete signals from the airborne system under test. For example, the DI interface can be used as a discrete quantity input interface to receive discrete signals from the airborne system under test. The discrete quantity output interface is used to send discrete signals to the airborne system under test. For example, the DO interface can be used as a discrete quantity output interface to send discrete signals to the airborne system under test.

[0104] The voltage analog interface includes a voltage analog input interface and a voltage analog output interface. The voltage analog input interface is used to acquire voltage signals from the airborne system under test. For example, the AI ​​interface can be used as a voltage analog input interface to receive analog voltage signals from the airborne system under test. The voltage analog output interface is used to output control signals or excitation signals to the airborne system under test. The AO interface can be used as a voltage analog output interface to output analog voltage signals to the airborne system under test to control or regulate the operating state of the controller.

[0105] The signal conditioning resource interface includes a voltage signal conditioning resource interface and a current signal conditioning resource interface. The voltage signal conditioning resource interface is used to process voltage signals, primarily responsible for receiving, conditioning, and converting them. It can perform necessary amplification, filtering, isolation, and other processing on the input voltage signal to meet the needs of subsequent testing or analysis. This voltage signal conditioning resource interface ensures the accuracy and stability of the voltage signal, improving the precision and reliability of testing.

[0106] The current signal conditioning resource interface is used to process current signals. Specifically, it amplifies, filters, and isolates current signals to ensure their accuracy and stability. The design of the current signal conditioning resource interface needs to consider the characteristics of the current signal, such as its magnitude, range of variation, and potential interference, to ensure the accuracy of the test results.

[0107] In one alternative embodiment, continue to refer to Figure 2 As shown, the interface adaptation includes bus communication interface adaptation, acquisition and control interface adaptation, and power supply interface adaptation.

[0108] The real-time simulator and the bus interface are connected to the airborne system under test (SUT) via a bus communication interface adapter. By connecting the real-time simulator and the SUT, the actual operating environment can be simulated to perform real-time simulation testing on the SUT. The bus communication interface adapter also ensures unimpeded communication between the real-time simulator and the SUT. Through testing, the functionality and performance of the bus interface can be verified, ensuring its stable and reliable operation in practical applications.

[0109] The acquisition and control interface module connects to the airborne system under test (SUT) through partial acquisition and control interface adapters, ensuring that the SUT can accurately and in real time acquire various electrical parameters and status information of the SUT, providing a reliable foundation for subsequent data analysis and performance evaluation. The GE test platform can also send control commands to the SUT to automate and precisely control the test process, improving test efficiency and accuracy.

[0110] The boundary test and fault injection module, test load module, and test power supply module are connected to the test interface via another acquisition and control interface adapter. After the boundary test and fault injection module is connected to the test interface, it can simulate various electrical faults, such as open circuit, short circuit, and abnormal voltage, to evaluate the equipment's response and recovery capabilities. After the test load module is connected to the test interface, it can precisely control the size and changes of the load, thereby comprehensively evaluating the equipment's load capacity and stability. After the test power supply module is connected to the test interface, it can simulate various power environments, such as voltage fluctuations and power interruptions, to verify the equipment's power adaptability and protection capabilities.

[0111] The acquisition and control interface module connects to the airborne system under test (SUT) via a partial power supply interface adapter, ensuring that the power supplied by the GE test platform matches the power specifications required by the SUT, thus guaranteeing smooth testing. It also acquires various electrical signals from the SUT, such as voltage, current, and power, providing data support for subsequent test analysis. The boundary test and fault injection module, test load module, and test power supply module connect to the test interface via another partial power supply interface adapter, enabling comprehensive testing of all aspects of the SUT. This also ensures the accuracy and stability of power and signal transmission between the GE test platform and the SUT, thereby improving test precision and reliability.

[0112] The aforementioned bus communication interface adapter provides universal signal excitation and bus communication, ensuring accurate data transmission between the GE test platform and the airborne system under test. It is responsible for converting commands or data issued by the GE test platform into a format that the airborne system under test can recognize and process, and simultaneously transmitting the responses or data from the airborne system under test back to the GE test platform, thus achieving effective communication between the two parties.

[0113] The aforementioned acquisition and control interface adapter is responsible for signal acquisition and excitation generation, as well as control interaction with the airborne system under test (SUT). It can acquire the measurement signals required by the GE test platform from the SUT and convert them into a format that the GE test platform can process. Simultaneously, it can perform necessary control operations on the SUT according to instructions from the GE test platform, such as starting, stopping, and adjusting.

[0114] The aforementioned power supply interface adapter provides a stable and reliable power supply to the airborne system under test (SUT), ensuring that the power supply matches the SUT's requirements. It is responsible for converting the power output of the GE test platform into the voltage, current, and other parameters required by the SUT to meet its normal operating power requirements. Through the power supply interface adapter, the stable operation of the SUT during testing can be ensured, thereby obtaining accurate test results.

[0115] The above approach enables comprehensive and accurate testing of the airborne system under test, providing strong support for the research, development, production, and quality control of the airborne system under test.

[0116] Example 2

[0117] Reference Figure 3 As shown, Figure 3 This is a flowchart of the MBSE-based general electrical testing method provided by the present invention; this embodiment provides an MBSE-based general electrical testing method applied to an MBSE-based general electrical testing platform, which is the aforementioned MBSE-based general electrical testing platform.

[0118] Step 101: Determine the interface resources based on the interface type, quantity, function, and performance parameters of the airborne system under test, and allocate the interface resources of the GE test platform.

[0119] Specifically, step 101 is used to determine the test interface. Based on the interface type, quantity, function and performance parameters of the airborne system under test, the resources used, such as real-time simulator, bus interface, acquisition and control interface, boundary test, fault injection, test power supply and test load, are identified and the interface resources of the GE test platform are allocated.

[0120] Before step 101, a test outline for the airborne system under test needs to be developed. This test outline includes: explaining the purpose and nature of the test; specifying the test items, contents, and methods according to the functions, performance, and technical specifications of the airborne equipment under test; and clarifying the test object, the general electrical test platform, and the test software and simulation models to be developed.

[0121] Step 102: Develop a test program set and test stimulus model on the host computer. The test program set and test stimulus model include an interface driver.

[0122] Specifically, the aforementioned host computer can be a general-purpose computer, used to develop test program sets and test stimulus models. Based on the test plan for the airborne system under test, test programs and test stimulus models are developed on a general-purpose computer (using languages ​​such as C, Matlab / Simulink, Modelica, etc., depending on the type of real-time simulator). The test programs and simulation models include interface drivers to establish the connection between the test program sets and test stimulus models and the interface resources of the GE test platform. It should be noted that the development of the aforementioned test programs is determined based on the test plan for the airborne system under test; different airborne devices under test have different functions and performance characteristics, meaning the content of the test programs will differ.

[0123] When developing test programs and test stimulus models on a regular computer, you can choose the appropriate programming language and tools based on specific needs and objectives. C language is suitable for low-level and real-time control, Matlab / Simulink is suitable for system-level modeling and simulation, while Modelica is an object-oriented, equation-based simulation language suitable for modeling and simulating complex physical systems, and Modelica is suitable for modeling complex multi-domain systems.

[0124] Step 103: Fabricate test cables according to the interface type and quantity of the airborne system under test. The test cables include bus cables, signal cables, and power cables. Draw a test cable diagram and fabricate test cables, such as bus cables, signal cables, and power cables, according to the test plan and test interface allocation of the airborne system under test.

[0125] The aforementioned bus cables are typically used to transmit data or control signals, playing a vital role in connecting various devices and transmitting information in electrical systems. Signal cables are responsible for transmitting signals collected by sensors, detectors, and other devices to control equipment or displays for monitoring and control. Power cables transmit electrical energy from the power source to various electrical devices, such as motors and lamps, ensuring the normal operation of the equipment.

[0126] Step 104: The host computer downloads and deploys the test program set and test stimulus model to the real-time operating system in the real-time simulator via Ethernet. The real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power supply module and test load module are connected to the airborne system under test via test cables.

[0127] In step 104, the airborne system under test is connected to the GE test platform. A regular computer downloads and deploys the test program set and test stimulus model to the real-time simulator via Ethernet. Bus cables, signal cables and power cables are used to connect the airborne system under test to the GE test platform.

[0128] Step 105: Based on the test program set and test stimulus model, drive the real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power supply module and test load module to test the airborne system under test.

[0129] Step 105: Test the airborne system under test (SUT) using the test program set and test stimulus model. Based on the test program set and test stimulus model, drive resources such as the real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power supply module, and test load module to perform functional, performance, boundary, and fault injection tests on the SUT.

[0130] After step 105, the test data is recorded and output. For example, the real-time simulator uploads the test data and waveforms to a regular computer via Ethernet for display, analysis and recording of the data and waveforms.

[0131] As can be seen from the above embodiments, the MBSE-based general electrical testing method provided by the present invention achieves at least the following beneficial effects:

[0132] This invention provides a general electrical testing method based on MBSE (Balanced Surface Test Engineering). Based on MBSE technology, it uses test programs and simulation models to drive a general electrical test platform for testing aviation electrical control, power distribution, and data acquisition equipment. This method standardizes the general electrical test platform, allowing it to be reused in the research and development and testing of multiple airborne systems under test (such as airborne equipment), reducing testing investment, increasing asset utilization, and lowering maintenance and management costs. Technical personnel can focus their main efforts on developing dedicated simulation test models for airborne systems (including equipment), resulting in high testing efficiency and reduced workload. In addition to functional, performance, and technical indicator testing, it can also perform boundary testing and fault injection testing, expanding the scope and depth of testing and improving design quality.

[0133] Electrical Testing Cases

[0134] Reference Figure 4 As shown, Figure 4 This is a schematic diagram of the electrical principle of an aircraft power supply system provided by the present invention; the following section provides test cases of typical electrical equipment in the aircraft power supply system based on the general electrical test platform and following the steps of the general electrical test method based on MBSE.

[0135] The principle block diagram of an aircraft power supply system case is as follows: Figure 4 As shown, the basic principle of an aircraft power supply system is briefly described below:

[0136] The power control board is the cockpit human-machine interface device. Flight crew members operate this control board to send control commands to the aircraft's power supply system.

[0137] The alternator and its controller provide 115V and 400Hz main AC power to the aircraft power supply system; the APU (Auxiliary Power Unit) generator and its controller provide 115V and 400Hz auxiliary AC power to the system; the transformer rectifier converts the 115V AC power to 28V DC power; and the battery provides 28V DC emergency power to the aircraft power supply system.

[0138] The AC distribution box is controlled by the power control board and the power supply processor to achieve the primary distribution of 115V AC power; the DC distribution box is controlled by the power control board and the power supply processor to achieve the primary distribution of 28V DC power.

[0139] The remote power control device receives control from the power supply processor and power control board to achieve secondary distribution of 115V AC power and 28V DC power. The testing of this remote power control device involves technologies such as electrical control, power distribution, and bus interconnection; therefore, this remote power control device was selected as the test case.

[0140] The power supply processor collects status information from the above devices (such as power control boards, AC distribution boxes, DC distribution boxes, transformers and rectifiers, and remote power control devices), performs logic calculations, and controls and manages these devices. Simultaneously, the power supply processor interconnects with the electromechanical management computer and electromechanical parameter display via a bus to upload and display power supply information. The testing of this power supply processor involves various technologies such as bus interconnection, calculation management, electrical control, and electrical data acquisition; therefore, this power supply processor was selected as the test case.

[0141] Application Case 1: Power Supply Processor Testing

[0142] Combination Figure 2 , Figure 5 and Figure 6 As shown, Figure 5 This is a schematic diagram of the data simulation model of an aircraft power supply system provided by the present invention; Figure 6 This invention provides a test case diagram for a power supply processor device under test. The first step involves developing a test plan for the power supply processor, including: explaining the purpose and nature of the test, such as a C / S type test or factory acceptance test; specifying test items such as function, performance, boundary conditions, and fault injection according to the power supply processor's functions, performance, and technical specifications, and providing specific test content and methods; and clarifying the test object, the general electrical test platform, and the test software and simulation model to be developed.

[0143] The second step is to determine the test interfaces, specifying the resources needed, including the real-time simulator, bus interfaces, acquisition and control interface modules, boundary testing, fault injection, test power supply, and test load. The interface resources of the GE test platform are then allocated. In this application case, the GE test platform resources are allocated according to the power supply processor interfaces as follows:

[0144] The power supply processor under test has one 1394B bus, which is driven by a real-time emulator to perform test docking.

[0145] The power supply processor under test has 5 RS422 bus interfaces, which are driven by a real-time emulator for testing and docking.

[0146] The power supply processor under test has two 0V / 28VDC discrete inputs, and the real-time simulator drives two discrete output interfaces (DO) and two 28V signal conditioning for testing and docking.

[0147] The power supply processor under test has two 0V / 28VDC discrete outputs, which are driven by a real-time simulator to perform test docking with two discrete input interfaces (DI) and two 28V signal conditioning.

[0148] The power supply processor under test has one set of 0V~115V three-phase AC analog input, which is driven by a real-time simulator to perform test docking with one set of analog output interface AO and one set of 115VAC signal conditioning.

[0149] The power supply processor under test has one 0V~28V DC analog input, which is driven by a real-time simulator to perform test docking with one analog output interface AO and a set of 28V signal conditioning.

[0150] The power supply unit under test has one 28V DC power input, which is tested and connected to the 28V test power supply.

[0151] The third step is to develop the test program set and test stimulus model. Based on the power supply processor test plan, develop the test program set and test stimulus model on a general-purpose computer (using languages ​​such as C, Matlab / Simulink, Modelica, etc., depending on the type of real-time simulator). In this embodiment, the test stimulus model adopts a simulation model. Establish a mathematical simulation model of the power supply system, such as... Figure 5 As shown, the system and each device have been confirmed to be accurately modeled and operating as expected, and can be run according to the test plan for each test item. Figure 5 The power supply processor model was removed, and the remaining bus, discrete, and analog interfaces were all encapsulated using the corresponding hardware drivers from the GE test platform, such as... Figure 6 As shown on the left side;

[0152] The fourth step is to draw a cable diagram and make test cables, such as bus cables, signal cables and power cables, according to the power supply processor test plan and test interface allocation.

[0153] Step 5: Connecting the power supply processing equipment under test to the GE test platform. Figure 6 Ordinary computers download and deploy the test program set and simulation model formed in the third step to the real-time simulator via Ethernet; according to Figure 6 The test cables (such as bus cables, signal cables, and power cables) made in step four are used to connect the power supply processor under test to the GE test platform.

[0154] Step 6: Test the power supply processor driven by the test assembly and simulation model. (Please click...) Figure 6 Based on the test program set and simulation model, resources such as real-time simulator, bus interface, acquisition and control interface module and test power supply are driven to perform functional, performance, boundary and fault injection tests on the power supply processing equipment under test.

[0155] Step 7: Record and output test data. The real-time simulator uploads the test data and waveforms to a regular computer via Ethernet for display, analysis, and recording.

[0156] Application Case 2: Testing of Remote Power Control Devices

[0157] Reference Figure 2 and Figure 7 As shown, Figure 7 This is a test case diagram of a power distribution device under test provided by the present invention; Figure 7 The tested power distribution equipment includes remote power control devices. The first step is to develop a test plan for the remote power control device, including: explaining the purpose and nature of the test, such as C / S type device test or factory acceptance test; specifying the test items such as function, performance, boundary and fault injection according to the function, performance and technical specifications of the remote power control device, and giving the specific test content and methods; and clarifying the test object, general electrical test platform, and the test software and test stimulus model to be developed.

[0158] The second step is to determine the test interfaces, specifying the resources needed, including the real-time simulator, bus interface, data acquisition and control interface modules, boundary testing, fault injection, test power supply, and test load. The interface resources of the GE test platform are then allocated. In this application case, the GE test platform resources are allocated according to the interface of the remote power control device as follows:

[0159] The remote power control device under test has one RS422 bus, which is tested and connected by a real-time emulator driving one RS422 bus interface.

[0160] The remote power control device under test has one 0V / 28VDC discrete input, and is driven by a real-time simulator to perform testing and docking with one discrete output interface DO and one 28V signal conditioning.

[0161] The remote power control device under test has a 115V three-phase AC power input, which is connected to the 485 bus / LAN bus driven by the real-time simulator and the programmable 115V three-phase AC test power supply.

[0162] The remote power control device under test has one 28V DC power input, which is connected to the 485 bus / LAN bus driven by the real-time simulator and the programmable 28V DC test power supply for power supply.

[0163] The remote power control device under test outputs power to the 115V AC load, which is connected to the 115V AC test load.

[0164] The remote power control device under test outputs power to a 28V DC load, which is connected to a 28V AC test load.

[0165] The real-time simulator uses a CAN bus interface to drive a signal generator and / or power amplifier to apply boundary test stimuli and fault injection stimuli to the remote power control device under test.

[0166] The third step is to develop the test program set and test stimulus model. Based on the test scheme for the remote power control device, develop the test program set and test stimulus model on a regular computer (using languages ​​such as C, Matlab / Simulink, Modelica, etc., depending on the type of real-time simulator). In this application case, the test stimulus model adopts a simulation model. Establish a power supply system simulation model, such as... Figure 5 As shown, the system and each device have been confirmed to be accurately modeled and operating as expected, and can be run according to the test plan for each test item. Figure 5 The model of the medium-to-long-range power control device was removed, and the remaining bus, discrete quantities, and power interfaces were encapsulated using corresponding hardware drivers from the GE test platform. Boundary and fault stimulus simulation models were then established. For example... Figure 7 As shown on the left side;

[0167] The fourth step is to draw a cable diagram and make test cables, such as bus cables, signal cables and power cables, according to the test plan and test interface allocation of the remote power control device.

[0168] Step 5: Connecting the power distribution equipment under test to the general electrical test platform. (Followed by...) Figure 7 Ordinary computers download and deploy the test program set and simulation model formed in the third step to the real-time simulator via Ethernet; according to Figure 7The test cables (such as bus cables, signal cables, and power cables) made in step four are used to connect the power distribution equipment under test to the general electrical test platform.

[0169] Step 6: Test the power supply processor driven by the test assembly and simulation model. (Please click...) Figure 7 Based on the test program set and simulation model, the system drives resources such as real-time simulator, bus interface, acquisition and control interface model, and test power supply to perform functional, performance, boundary and fault injection tests on the physical power supply processor.

[0170] Step 7: Record and output test data. The real-time simulator uploads the test data and waveforms to a regular computer via Ethernet for display, analysis, and recording.

[0171] While specific embodiments of the invention have been described in detail by way of examples, those skilled in the art should understand that the examples are for illustrative purposes only and not intended to limit the scope of the invention. Those skilled in the art should understand that modifications can be made to the above embodiments without departing from the scope and spirit of the invention. The scope of the invention is defined by the appended claims.

Claims

1. A generic electrical test platform based on MBSE, characterized in that, It includes a real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power supply module, test load module and interface adapter; The real-time simulator is equipped with a real-time operating system, which is used to solve the test program set and test stimulus model, and to schedule resources in real time according to the solution results to complete the test tasks of the airborne system under test. The resources include the bus interface, the acquisition and control interface module, the test power supply module and the test load module. The test tasks of the airborne system under test include power allocation, command control, signal acquisition, boundary signal injection and fault signal injection. The bus interface is connected at one end to the real-time simulator and at the other end to the interface of the airborne system under test, in order to meet the bus communication test requirements of the airborne system under test. The acquisition and control interface module is connected at one end to the real-time simulator and at the other end to the interface of the airborne system under test, in order to meet the command control and signal testing requirements of the airborne system under test during testing. The boundary testing and fault injection module is used to test the working capability of the airborne system under test under boundary extreme conditions and to detect the environmental adaptability and fault detection of the airborne system under test. The test power module is connected to the power input interface of the airborne system under test and is used to simulate a power generation system to provide power to the airborne system under test. The test load module is connected to the output interface of the airborne system under test and is used to simulate electrical equipment as a simulated load for the airborne system under test, and to detect the load and overload protection of the airborne system under test. The interface adapter is used to organize the corresponding interfaces of the real-time simulator, the bus interface, the acquisition and control interface module, the boundary test and fault injection module, the test power supply module, and the test load module, and connect them to one side of the interface adapter box; furthermore, one set of interfaces from the interface adapter box is used to connect to the airborne system under test, and another set of interfaces is used to connect to a multimeter and an oscilloscope to achieve online testing; The interface adaptation includes a bus communication interface adaptation, an acquisition and control interface adaptation, and a power supply interface adaptation. The real-time simulator and the bus interface are respectively connected to the airborne system under test through the bus communication interface adaptation. The acquisition and control interface module is connected to the airborne system under test through part of the acquisition and control interface adaptation, and the boundary test and fault injection module, the test load module, and the test power supply module are connected to the test interface through another part of the acquisition and control interface adaptation. The acquisition and control interface module is connected to the airborne system under test through part of the power supply interface adaptation, and the boundary test and fault injection module, the test load module, and the test power supply module are connected to the test interface through another part of the power supply interface adaptation.

2. The MBSE-based general electrical test platform according to claim 1, characterized in that, The acquisition and control interface module includes a discrete quantity interface, a voltage analog quantity interface, a current analog quantity interface, a resistance analog quantity interface, an open quantity interface, and a signal conditioning resource interface. The discrete quantity interface is used to process discrete digital signals from the airborne system under test. The voltage analog quantity interface is used to acquire and control the voltage signals of the airborne system under test. The current analog quantity interface is used to acquire and control the current signals of the airborne system under test in real time. The resistance analog quantity interface is used to acquire changes in the resistance value of the airborne system under test in real time and convert them into processable analog signals, including pressure and displacement. The open quantity interface is used to receive and send the switching status signals of the airborne system under test, including passive and active switches. The signal conditioning resource interface is used to condition the analog signals input to the airborne system under test.

3. The MBSE-based general electrical test platform according to claim 2, characterized in that, The discrete quantity interface includes a discrete quantity input interface and a discrete quantity output interface. The discrete quantity input interface is used to receive discrete signals from the airborne system under test, and the discrete quantity output interface is used to send discrete signals to the airborne system under test. The voltage analog quantity interface includes a voltage analog quantity input interface and a voltage analog quantity output interface. The voltage analog quantity input interface is used to acquire voltage signals from the airborne system under test, and the voltage analog quantity output interface is used to output control signals or excitation signals to the airborne system under test. The signal conditioning resource interface includes a voltage signal conditioning resource interface and a current signal conditioning resource interface. The voltage signal conditioning resource interface is used to process voltage signals, and the current signal conditioning resource interface is used to process current signals.

4. A general electrical test method based on MBSE, applied to the general electrical test platform based on MBSE as described in any one of claims 1-3, characterized in that, Based on the interface type, quantity, function, and performance parameters of the airborne system under test, determine the interface resources and allocate them to the interface resources of the general electrical test platform; A test program set and a test stimulus model are developed on a host computer, the test program set and the test stimulus model including an interface driver; Test cables are fabricated according to the interface type and quantity of the airborne system under test, wherein the test cables include bus cables, signal cables and power cables; The host computer downloads and deploys the test program set and the test stimulus model to the real-time operating system in the real-time simulator via Ethernet. The real-time simulator, the bus interface, the acquisition and control interface module, the boundary test and fault injection module, the test power supply module, and the test load module are respectively connected to the airborne system under test via the test cable. Based on the test program set and the test stimulus model, the real-time simulator, the bus interface, the acquisition and control interface module, the boundary test and fault injection module, the test power supply module and the test load module are driven to test the airborne system under test.

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