General electrical test platform based on MBSE and method thereof

Abstract

The invention discloses an MBSE-based general electrical test platform and a method thereof. The MBSE-based general electrical test platform comprises a real-time simulation machine, 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, the real-time simulation machine carries a real-time operating system and is used for resolving the test program set and the test excitation model and scheduling resources in real time according to a resolving result; one end of the bus interface is connected with the real-time simulation machine, and the other end of the bus interface is connected with an interface of the tested airborne system; one end of the acquisition and control interface module is connected with the real-time simulation machine, and the other end of the acquisition and control interface module is connected with an interface of the tested airborne system; the test power supply module is connected with a power supply input interface of the tested airborne system; and the test load module is connected with an output interface of the tested airborne system. According to the invention, the manpower, time and fund investment for building the test model is reduced, the asset utilization rate is improved, and the maintenance and management cost of the electrical test platform is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation electrical test and experiment, and more specifically, to a general electrical test platform and method based on MBSE. Background Art

[0002] Generally speaking, aircraft systems mainly include flight control systems, avionics systems and electromechanical systems. Among them, electromechanical systems include electromechanical control 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, fluids, electrical and lighting.

[0003] Electrical is a public profession. The aircraft power supply system provides power supply and distribution for the entire aircraft system. The power, hydraulic, landing gear, fuel, fire protection, environmental control and lighting systems all contain corresponding electrical subsystems to perform electrical signal acquisition and electrical control management functions. The electromechanical control management collects information, conducts comprehensive control and information fusion for each electromechanical subsystem, and conducts information cross-linking with avionics and flight control. It can be seen that when designing aircraft systems, the cross-linking relationship of electrical design at the component level, system level, function level, information level, etc. is very complex, and the degree of coupling between systems is also very high. With the development of aircraft towards multi-electric / full-electric direction, including with the development of electric aircraft (EVTOL), the importance of electrical is further enhanced. The function, performance, reliability, safety, etc. of electrical are directly related to the safety of aircraft. Therefore, the test and testing of airborne systems related to electrical design and airborne systems under test are crucial.

[0004] The current status of electrical testing in aircraft host units and onboard system research units is as follows:

[0005] (1) The research and development unit of the airborne system under test shall invest manpower, time and financial resources to develop the corresponding equipment test equipment according to the equipment technical agreement and design plan, and test the product samples (including digital models and physical objects) of each stage of the airborne system under test. Since the requirements and design plans of the airborne systems under test required by different aircraft are different, the corresponding equipment test equipment is often also dedicated;

[0006] (2) At the system level, the aircraft host unit shall propose technical transformation and condition construction plans in accordance with the overall development requirements and system design plan, and apply for funds from the superior authorities; after the funds are approved, a system-level test model shall be built to conduct system joint tests in the scheme stage, principle sample system joint tests, and actual sample system joint tests. The application, approval, and investment and construction of technical transformation plans require a large amount of manpower, time, and financial resources. Different aircraft models often have different system design technologies, so the system-level test model is tightly coupled with the model and presents a dedicated feature;

[0007] The above-mentioned airborne system-level equipment test devices and system-level test models are included in the scope of fixed asset management. If they are dedicated and not universal, the asset utilization rate is not high and long-term maintenance and management costs are required. In summary, in order to conduct system-level and equipment-level electrical tests, the main and auxiliary machine units have invested a lot of manpower, time, and financial resources, and the asset utilization rate is not high, and the maintenance and management costs are high. Therefore, it is a technical problem that needs to be solved urgently 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 structure in an aircraft 1394B bus communication simulation test platform provided by the prior art; see Figure 1 As shown, the aircraft 1394B bus communication simulation test platform includes a simulation computer as a system operation platform, peripheral equipment connected to the simulation computer as auxiliary testing, and also includes: a communication platform, which is connected to the simulation computer and the peripheral equipment through a 1394 bus network and is used to collect and receive two-way communication messages; an extended part, which is connected to the communication platform through a 1394 bus network and is used to meet the testability and increase the test coverage of the auxiliary modules. This solution only involves the 1394 bus network and does not involve other resources. Therefore, it does not solve the above technical problems. Summary of the invention

[0009] In view of this, the present invention provides a general electrical testing platform based on MBSE to solve the problem in the prior art that in order to conduct system-level and equipment-level electrical tests, the main and auxiliary machine units have invested a lot of manpower, time and financial resources, the asset utilization rate is low, and the maintenance and management costs are high.

[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 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 the test stimulus model, and to schedule resources in real time according to the solution results to complete the test task of the airborne system under test, wherein the resources include the bus interface, the acquisition and control interface module, the signal injection, the test power module and the test load module, and the test task of the airborne system under test includes power distribution, command control, signal acquisition, boundary signal injection and fault signal injection;

[0012] The bus interface, one end of which is connected to the real-time simulator, and the other end of which is connected to the interface of the tested airborne system, is used to meet the bus communication test requirements of the tested airborne system;

[0013] The acquisition and control interface module, one end of which is connected to the real-time simulator, and the other end of which is connected to the interface of the airborne system under test, is used to meet the command control and signal test requirements when testing the airborne system under test, wherein 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 opening quantity interface and a signal conditioning resource interface, wherein the discrete quantity interface is used to process discrete digital signals in the airborne system under test; the voltage analog quantity interface is used to acquire and control the voltage signal of the airborne system under test; the current analog quantity interface is used to acquire and control the current signal of the airborne system under test; the resistance analog quantity interface is used to acquire changes in resistance value in the airborne system under test; the opening quantity interface is used to receive and send switch state signals of the airborne system under test; and the signal conditioning resource interface is used to condition analog signals input into the airborne system under test;

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

[0015] The test power supply 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 supply for 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 an electrical device as a simulated load of the airborne system under test to detect the load and overload protection of the airborne system under test;

[0017] The interface adapter is used to organize the corresponding interfaces in the real-time simulation machine, the bus interface, the acquisition and control interface module, the boundary test and fault injection module, the test power 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 a discrete signal of the airborne system under test, and the discrete quantity output interface is used to send a discrete signal 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, wherein the voltage analog quantity input interface is used to collect the voltage signal from the airborne system under test, and the voltage analog quantity output interface is used to output a control signal or an excitation signal 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 adaptation includes bus communication interface adaptation, acquisition control interface adaptation and power supply interface adaptation;

[0022] The real-time simulator and the bus interface are respectively connected to the tested airborne system via the bus communication interface adapter;

[0023] The acquisition and control interface module is connected to the tested airborne system through a part of the acquisition control 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 part of the acquisition control interface adapter;

[0024] The acquisition and control interface module is connected to the onboard system under test through a part 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 part of the power supply interface adapter.

[0025] In a second aspect, a general electrical test method based on MBSE is applied to a general electrical test platform based on MBSE, wherein the general electrical test platform based on MBSE is the general electrical test platform based on MBSE described above, and 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 test platform are allocated;

[0026] Developing a test program set and a test stimulus model on a host computer, wherein the test program set and the test stimulus model include an interface driver;

[0027] Making test cables according to the interface type and quantity of the tested airborne system, wherein the test cables include bus cables, signal cables and power cables;

[0028] The host computer downloads the test program set and the test stimulus model through Ethernet and deploys them to the real-time operating system in the real-time simulator, and the real-time simulator, the bus interface, the acquisition and control interface module, the boundary test and fault injection module, the test power module and the test load module are respectively connected to the tested airborne system through 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 achieve at least the following beneficial effects:

[0031] First, a general electrical test platform based on MBSE is built with real-time and general electrical test resources. The general electrical test platform is decoupled from the specific airborne system under test and is not directly related to it. Different airborne systems under test can reuse these test resources, which reduces the manpower, time and capital investment in building test models, improves asset utilization and reduces the maintenance and management costs of the electrical test platform.

[0032] Second, when the airborne system under test is being developed and tested, the hardware is physically "fixed and immovable"; the "changing and moving" parts are only 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 "changing and moving" parts, namely the test program set, the test stimulus model and the test cable, can be quickly changed and adjusted, thereby improving the test efficiency;

[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 are downloaded to the real-time simulator, and the airborne system under test is connected using the corresponding test cable. This allows the development and test switching of different airborne systems under test to be realized, thus achieving peak-shifting and parallel development and testing of multiple models of airborne systems under test.

[0034] Fourth, the fault injection resource can be combined with boundary test stimulus software to perform electrical boundary tests, such as voltage disturbance, signal disturbance, level boundary test and software boundary test, etc.; combined with fault injection stimulus software, it can perform fault injection tests, such as open circuit fault, short circuit fault, error signal, reverse phase sequence, spike injection and surge injection, etc., thereby expanding the scope of test and increasing the depth of test;

[0035] Fifth, through the coordination between discrete quantity interface, voltage analog quantity interface, current analog quantity interface, resistance analog quantity interface, opening quantity interface and signal conditioning resource interface, the acquisition and control interface of the general electric test platform is formed, so that the general electric test platform can flexibly adapt to different types of airborne systems under test and realize the measurement and control of various electrical parameters. When designing a general electric 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 test process.

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

[0037] Further features and advantages of the present invention will become apparent from the following detailed description of exemplary embodiments of the present invention with reference to the attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0039] Figure 1 It is a general diagram of the 1394b bus 3CC network topology structure in an aircraft 1394B bus communication simulation test platform provided by the prior art;

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

[0041] Figure 3 is a flow chart of a general electrical testing method based on MBSE provided by the present invention;

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

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

[0044] Figure 6 It is a test case diagram of a tested power supply processor type device 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 DESCRIPTION

[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 the relative arrangement of components and steps, numerical expressions and numerical values ​​set forth in these embodiments do not limit the scope of the present invention unless otherwise specifically stated.

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

[0048] Technologies, methods, and equipment known to ordinary technicians in the relevant art may not be discussed in detail, but where appropriate, the technologies, methods, and equipment should be considered as part of the specification.

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

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

[0051] Embodiment 1

[0052] Figure 2 is the architecture diagram of the general electrical test platform based on MBSE provided by the present invention; see 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 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 the 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 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] A bus interface, one end of which is connected to the real-time simulator and the other end of which is connected to the interface of the airborne system under test, to meet the bus communication test requirements of the airborne system under test;

[0055] An acquisition and control interface module, one end of which is connected to the real-time simulator and the other end is connected to the interface of the airborne system under test, and is used to meet the command control and signal testing requirements when testing the airborne system under test, wherein 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 opening quantity interface and a signal conditioning resource interface, wherein the discrete quantity interface is used to process discrete digital signals in the airborne system under test; the voltage analog quantity interface is used to acquire and control the voltage signal of the airborne system under test, such as the voltage signal output by the sensor or the voltage signal to be controlled; the current analog quantity interface is used to acquire and control the current signal of the airborne system under test; the resistance analog quantity interface is used to acquire the change of the resistance value in the airborne system under test; the opening quantity interface is used to receive and send the switch state signal of the airborne system under test; the signal conditioning resource interface is used to condition the analog signal input into the airborne system under test;

[0056] Boundary test and fault injection module, used to test the working ability of the airborne system under extreme boundary conditions and to detect the environmental adaptability and fault detection of the airborne system under test;

[0057] A test power supply module, which 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;

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

[0059] 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 module and test load module, and connect them to the interface adapter box.

[0060] Specifically, continue to refer to Figure 2 As shown, the above-mentioned general electric test platform based on MBSE can be a general electric test platform based on MBSE, which includes a real-time simulator, a bus interface, an acquisition and control interface module, a boundary test and fault injection module, a test power module, a test load module and an interface adapter; using the above-mentioned MBSE (Model-Based Systems Engineering) to drive the general electric semi-physical test platform can significantly improve the test efficiency, accuracy and flexibility, and provide strong support for the research and development and testing of electrical systems.

[0061] The above-mentioned real-time simulator is the core of the general electric test platform. It mainly solves the test program set and the test stimulus model, and performs real-time scheduling of resources such as the bus interface, acquisition and control interface module, signal injection, test power module, and test load module according to the solution results, and completes the power distribution, command control, signal acquisition, boundary signal injection, and fault signal injection test tasks during the test of the airborne system under test. At present, there are many types of commercial real-time simulators. When selecting a real-time simulator, based on the capture technology 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 language, and scalability. In this embodiment, the NIPXIe-8881 high-performance 8-core controller module can be selected as the control core, equipped with a real-time operating system. It should be noted that the above-mentioned airborne system under test includes the airborne equipment under test.

[0062] The above-mentioned test program set is a general test program set designed for the general electric test platform. The test program set integrates software such as real-time operating system and hardware driver, and configures and manages the hardware interface resources of each component of the general electric test platform through the software; the above-mentioned test stimulus model is constructed through Matlab / Simulink and C language, and drives the various hardware modules in the general electric test platform through software, provides the signal stimulus required by the airborne system under test, simulates the use environment of the airborne system under test, and simulates the cross-linking equipment and system environment of the airborne system under test.

[0063] The above-mentioned Matlab / Simulink is an integrated development environment launched by MathWorks, which is mainly used for mathematical calculations, 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 visual simulation tool in Matlab, which is used for multi-domain simulation and model-based design.

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

[0065] The above-mentioned bus interface is the key part connecting the general electric test platform and the airborne system under test, and is used to meet the bus communication test requirements of the airborne system under test. Specifically, the bus interface is responsible for realizing data transmission and communication between the general electric test platform and the airborne system under test, ensuring the accurate transmission and reception of test signals. Through the bus interface, the general electric test platform can obtain various parameters and status information of the airborne system under test, and then conduct comprehensive and accurate testing and analysis of the airborne system under test.

[0066] At present, the bus types commonly used in the airborne systems under test include 1553 bus, 1394 bus, AFDX (Avionics Full-Duplex Switched Ethernet) bus, CAN (Controller Area Network) bus, 429 bus, 629 bus, etc. These buses generally have commercial boards to choose from, and the bus board selection and configuration, as well as subsequent expansion configuration, can be carried out based on the airborne system under test.

[0067] The above-mentioned 1553 bus is an airborne bus standard widely used in the aviation field, with the characteristics of high reliability, real-time and flexibility; the 1394 bus, also known as FireWire, is a high-speed serial bus standard, mainly 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, with the characteristics of high bandwidth, low latency and strong real-time performance, and is an important part of modern avionics systems; the CAN bus is a widely used field bus standard, known for its high reliability and flexibility; the 429 bus is a digital data bus standard widely used in the civil aviation field, used to transmit flight parameters and status information. The 629 bus is an airborne bus type used in specific fields or applications. The above buses are suitable for different airborne equipment and application scenarios. In the general electric test platform, it is necessary to select the appropriate bus interface and bus type according to the specific test requirements and the type of airborne equipment to ensure the smooth progress of the test work.

[0068] The acquisition and control interface module includes acquisition and control interface resources, which are used to meet the command control and signal testing requirements when testing the airborne system under test. It mainly refers to the acquisition and control interface module that can achieve precise control of the airborne system under test and effective signal acquisition. Specifically: various control instructions such as start, stop, and adjust parameters are sent to the airborne system under test through the acquisition and control interface module. These control instructions ensure that the airborne system under test can operate according to the predetermined procedures and requirements during the test process, so as to achieve a comprehensive evaluation of its performance. The acquisition and control interface module can also receive and process various signals generated by the airborne system under test during the test process, such as voltage, current, frequency, temperature, etc. Through the real-time acquisition and analysis of these signals, the General Electric test platform can obtain the working status, performance parameters, and possible fault information of the airborne system under test, providing strong support for subsequent fault diagnosis and performance optimization.

[0069] Continue to refer to Figure 2As shown, the discrete quantity interface converts discrete digital signals (such as dry contacts, wet contacts, and voltage signals) into a digital format that can be recognized and processed by the general electrical test platform for subsequent analysis and testing. The discrete quantity interface also has an electrical isolation function to prevent electrical interference from affecting the airborne system under test, and has overvoltage and overcurrent protection functions to ensure that the airborne system under test is protected from damage under abnormal conditions. It can not only process discrete digital signals in the airborne system under test, but also provide electrical isolation and protection. It is easy to configure and integrate, providing great convenience and reliability for electrical testing.

[0070] The discrete quantity interface can be a ground / open discrete quantity interface and a 28V / open discrete quantity interface. The ground / open discrete quantity interface refers to two signal states of grounding / open circuit. Grounding can refer to the body of the aircraft. This interface is used to collect and control discrete signals with two states (such as on / off, with / without). The 28V / open discrete quantity interface refers to the use of 28V voltage and open circuit to indicate many working states of the onboard system under test. The 28V voltage is not a stable value, but a variable voltage ranging from 18 to 32V.

[0071] The above-mentioned voltage analog interface can receive voltage signals transmitted by the airborne system under test. These signals are usually analog quantities. Through the real-time simulator, the received voltage signals are collected and converted in real time and converted into digital signals for subsequent processing and analysis. It can not only accurately collect 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 the electrical system.

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

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

[0074] The current analog quantity interface may be a 4mA-20mA current analog quantity interface. The 4mA-20mA current analog quantity interface is a common analog signal transmission interface used for transmitting continuous current signals, and the signal range is between 4mA and 20mA.

[0075] The above-mentioned resistance analog interface can collect the numerical changes of resistance in the airborne system under test in real time, and provide data support for subsequent testing and analysis. The resistance analog interface has the characteristics of high precision, stability and compatibility. For example, it can accurately reflect the slight changes in resistance value, ensure the accuracy of test results, maintain consistent collection effects in long-term testing, improve test reliability, and be compatible with multiple resistance types to meet the test requirements of different airborne systems.

[0076] The resistance analog quantity interface may be a PT1000 resistance analog quantity interface, which is used to collect the temperature signal of the PT1000 thermal resistor and convert it into a processable analog quantity signal.

[0077] The resistance analog interface can also be a 900-3k resistance analog interface, which is used to connect resistance sensors with resistance values ​​between 900 ohms and 3 kiloohms to collect various analog signals, such as pressure and displacement.

[0078] The above-mentioned opening quantity interface can receive switch status signals issued by the airborne system under test, which usually include signals of passive switches (such as buttons, contactor contacts and travel switches) and active switches (such as proximity switches and transistor switch circuits); it can also send switch control signals to the airborne system under test to realize remote control and monitoring of the switch status in the airborne system under test.

[0079] The above-mentioned signal conditioning resource interface can accurately condition the analog signal, eliminate noise and interference in the signal, improve the accuracy and reliability of the test, and support various types of analog signal input, so that the test platform can adapt to the needs of different airborne systems under test and enhance the flexibility of the test.

[0080] It should be noted that the acquisition and control interface module also includes other standard interfaces and expansion slots. Through other standard interfaces and expansion slots, the General Electric test platform can be connected to various airborne systems under test to meet different test requirements, thereby improving the flexibility and applicability of the General Electric test platform.

[0081] Boundary test and fault injection module, the boundary test and fault injection module includes boundary test and fault injection resources, which are used to test the working ability of the airborne system under extreme boundary conditions, and artificially inject fault signals to detect the environmental adaptability and fault detection of the airborne system under test, so as to find potential errors or unstable factors; that is, by applying voltage disturbances, signal disturbances, tolerance boundaries, level boundaries, open circuit faults, short circuit faults and other test stimuli, the operating boundaries, anti-interference capabilities and fault-tolerant reconstruction of the airborne system under test are tested.

[0082] Common boundary test and fault injection modules can be selected from: commercial boards, such as signal generators and power amplifiers, which are devices used to inject fault signals and monitor signals. The signal generators and power amplifiers can belong to the general electric test platform. Depending on the conditions of the airborne system under test, the power and signal range of the power amplifier are different, and they are selected according to the requirements of the airborne system under test. That is, the specific selection of the above signal generators and power amplifiers needs to be selected and configured based on the airborne system under test, and then expanded.

[0083] Boundary tests include voltage boundary tests, current boundary tests and time boundary tests. Among them, 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 extremely short periods of time, such as long-term working tests and fast switching tests.

[0084] Fault injection resources refer to the artificial introduction of faults into the airborne system under test to evaluate the fault tolerance and recovery capabilities of the airborne system under test. 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: Imposing 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: Input abnormal signals, such as noise and interference signals, into the airborne system under test to test the signal processing capability and anti-interference ability of the airborne system under test.

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

[0088] Level boundary injection: The performance of the airborne system under test when the level approaches or exceeds the logic threshold, such as high-low level conversion and logic judgment.

[0089] Open circuit fault injection: simulates an open circuit fault in the circuit to test the response and fault location capability of the airborne system under test in the case of an open circuit.

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

[0091] The above-mentioned test power supply module includes a test power supply for simulating a power generation system. It can accurately simulate the power supply characteristics of an actual power generation system, provide power supply conditions close to the real working environment for the airborne system under test, and provide a variety of power supply systems, such as 28VDC, 270VDC, 540VDC, 115VAC and other power supply systems to meet the power supply requirements of different devices under test. The test power supply technology requires programmable control (supports remote control and programming through a computer to realize automated test processes) and adjustable (such as voltage, current and other parameters can be finely adjusted according to test requirements to meet the requirements of different test scenarios). The test power supply technology is mature and fully commercialized.

[0092] The test power supply module provides power supply for the airborne system under test, thereby providing a key device with stable and adjustable power supply for the airborne system under test; 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, which is connected to the output interface of the airborne system under test and is used to simulate electrical equipment. As a simulated load of the airborne system under test, it detects the load and overload protection performance of the airborne system under test. It can establish multiple power loads such as 28VDC, 270VDC, 540VDC and 115VAC that match the test power supply. Usually, the above-mentioned test loads use electronic loads or resistive loads, which have mature technology and are fully commercialized.

[0094] The above-mentioned interface adapter organizes the corresponding interfaces in the real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power module and test load module, and connects them to one side of the interface adapter box. The "three-way" principle is adopted to divide these interfaces "one group into two groups". One group of interfaces is used to connect the airborne system under test, and the other group of interfaces is used to connect a multimeter and an oscilloscope to realize online testing.

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

[0096] The above-mentioned real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power module, test load module and interface adapter are all market-oriented and standardized test resources, which provide general test resources for electrical airborne systems. However, they are not customized and dedicated test resources that are strongly related to a certain type of airborne system under test. Therefore, it is a general electrical test platform.

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

[0098] First, a general electrical test platform based on MBSE is built with real-time and general electrical test resources. The general electrical test platform is decoupled from the specific airborne system under test and is not directly related to it. Different airborne systems under test can reuse these test resources, which reduces the manpower, time and capital investment in building test models, improves asset utilization and reduces the maintenance and management costs of the electrical test platform.

[0099] Second, when the airborne system under test is being developed and tested, the hardware is physically "fixed and immovable"; the "changing and moving" parts are only 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 "changing and moving" parts, namely the test program set, the test stimulus model and the test cable, can be quickly changed and adjusted, thereby improving the test efficiency;

[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 are downloaded to the real-time simulator, and the airborne system under test is connected using the corresponding test cable. This allows the development and test switching of different airborne systems under test to be realized, thus achieving peak-shifting and parallel development and testing of multiple models of airborne systems under test.

[0101] Fourth, the fault injection resource can be combined with boundary test stimulus software to perform electrical boundary tests, such as voltage disturbance, signal disturbance, level boundary test and software boundary test, etc.; combined with fault injection stimulus software, it can perform fault injection tests, such as open circuit fault, short circuit fault, error signal, reverse phase sequence, spike injection and surge injection, etc., thereby expanding the scope of test and increasing the depth of test;

[0102] Fifth, through the coordination between discrete quantity interface, voltage analog quantity interface, current analog quantity interface, resistance analog quantity interface, opening quantity interface and signal conditioning resource interface, the acquisition and control interface of the general electric test platform is formed, so that the general electric test platform can flexibly adapt to different types of airborne systems under test and realize the measurement and control of various electrical parameters. When designing a general electric 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 test process.

[0103] In an 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, wherein the discrete quantity input interface is used to receive discrete signals of the airborne system under test, for example, the DI interface can be used as a discrete quantity input interface to receive discrete signals of 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, wherein the voltage analog input interface is used to collect 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 working state.

[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 and is mainly responsible for receiving, conditioning and converting voltage signals. It can perform necessary amplification, filtering, isolation and other processing on the input voltage signal to meet the needs of subsequent testing or analysis. The voltage signal conditioning resource interface can ensure the accuracy and stability of the voltage signal and improve the accuracy and reliability of the test.

[0106] The current signal conditioning resource interface is used to process the current signal. Specifically, it amplifies, filters, isolates, and processes the current signal to ensure the accuracy and stability of the signal. The design of the current signal conditioning resource interface needs to take into account the characteristics of the current signal, such as the current size, range of variation, and possible interference, to ensure the accuracy of the test results.

[0107] In an alternative embodiment, continue to refer to Figure 2 As shown, interface adaptation includes bus communication interface adaptation, acquisition 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 through the bus communication interface adapter. By connecting the real-time simulator and the airborne system under test, the actual operating environment can be simulated to perform real-time simulation tests on the airborne system under test. The bus communication interface adapter can also ensure that the communication between the real-time simulator and the airborne system under test is unimpeded. Through testing, the function and performance of the bus interface can be verified to ensure that it can work stably and reliably in actual applications.

[0109] The acquisition and control interface module is connected to the airborne system under test through a partial acquisition control interface adapter, which can ensure that the airborne system under test can accurately and real-time collect various electrical parameters and status information of the airborne system under test, providing a reliable basis for subsequent data analysis and performance evaluation; the general electric test platform can also send control instructions to the airborne system under test to realize the automation and precise control of the test process, thereby improving test efficiency and accuracy.

[0110] 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 control interface adapter. After the boundary test and fault injection module is connected to the test interface, various electrical faults such as open circuit, short circuit, voltage abnormality, etc. can be simulated to evaluate the response and recovery capabilities of the equipment; after the test load module is connected to the test interface, the size and change of the load can be accurately controlled to comprehensively evaluate the load capacity and stability of the equipment; after the test power supply module is connected to the test interface, various power supply environments can be simulated, such as voltage fluctuations, power outages, etc., to test the power adaptability and protection capabilities of the equipment.

[0111] The acquisition and control interface module is connected to the airborne system under test through a partial power supply interface adapter to ensure that the power supply provided by the general electric test platform matches the power supply specifications required by the airborne system under test, thereby ensuring the smooth progress of the test. At the same time, it can collect various electrical signals of the airborne system under test, such as voltage, current, power, etc., to provide data support for subsequent test analysis. The boundary test and fault injection module, test load module and test power supply module are connected to the test interface through another part of the power supply interface adapter to achieve comprehensive testing of all aspects of the airborne system under test, and can also ensure the accuracy and stability of the power supply and signal transmission between the general electric test platform and the airborne equipment under test, thereby improving the accuracy and reliability of the test.

[0112] The above bus communication interface adapter provides universal signal excitation and bus communication to ensure accurate data transmission between the general electric test platform and the airborne system under test. It is responsible for converting the instructions or data issued by the general electric test platform into a format that can be recognized and processed by the airborne system under test, and at the same time, it returns the response or data of the airborne system under test to the general electric test platform to achieve effective communication between the two parties.

[0113] The acquisition control interface adapter is responsible for signal acquisition and stimulus generation, as well as control interaction with the airborne system under test. It can collect the measurement signals required by the general electric test platform from the airborne system under test and convert them into a format that the general electric test platform can process. At the same time, it can also perform necessary control operations on the airborne system under test according to the instructions of the general electric test platform, such as starting, stopping and adjusting.

[0114] The above-mentioned power supply interface adapter provides a stable and reliable power supply for the airborne system under test, and ensures that the power supply matches the requirements of the airborne system under test. It is responsible for converting the power output of the general electric test platform into the voltage, current and other parameters required by the airborne system under test to meet the power requirements for its normal operation. Through the power supply interface adapter, it can be ensured that the airborne system under test can operate stably during the test process, so as to obtain accurate test results.

[0115] The above scheme can realize comprehensive and accurate testing of the airborne system under test, and provide strong support for the research and development, production and quality control of the airborne system under test.

[0116] Embodiment 2

[0117] Reference Figure 3 As shown, Figure 3 is a flow chart of a general electrical testing method based on MBSE provided by the present invention; this embodiment provides a general electrical testing method based on MBSE, which is applied to a general electrical testing platform based on MBSE. The general electrical testing platform based on MBSE is the general electrical testing platform based on MBSE mentioned above.

[0118] Step 101, determining interface resources according to the interface type, quantity, function and performance parameters of the airborne system under test, and allocating interface resources of the general electric test platform;

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

[0120] Before step 101, it is also necessary to formulate a test outline for the airborne system under test, which includes explaining the purpose and nature of the test; specifying the test items, content and methods according to the functions, performance and technical indicators of the airborne equipment under test; clarifying the test product, the general electric test platform, and the test software and simulation model to be developed;

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

[0122] Specifically, the host computer can be a common computer, and a test program set and a test stimulus model are developed. According to the test plan of the airborne system under test, a test program and a test stimulus model are developed on a common computer (C language, Matlab / Simulink, Modelica and other languages ​​can be used, depending on the type of real-time simulator), and the test program and the simulation model contain an interface driver to realize the association of the test program set and the test stimulus model with the interface resources of the general electric test platform. It should be noted that the development of the above test program is determined according to the test plan of the airborne system under test, and different airborne devices under test have different functions and performances, that is, different test program contents.

[0123] When developing test programs and test stimulus models on ordinary computers, you can choose appropriate programming languages ​​and tools according to specific needs and goals. C language is suitable for low-level and real-time control, Matlab / Simulink is suitable for system-level modeling and simulation, and Modelica is an object-oriented, equation-based simulation language suitable for modeling and simulation of complex physical systems. Modelica is suitable for modeling complex multi-domain systems.

[0124] Step 103: Make test cables 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; draw a test 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 airborne system under test.

[0125] The above-mentioned bus cables are usually used to transmit data or control signals, and play an important role in connecting various devices and transmitting information in the electrical system; signal cables are responsible for transmitting signals collected by sensors, detectors and other devices to control devices or displays for monitoring and control; power cables transmit electrical energy from the power supply to various electrical devices, such as motors, lamps, etc., to ensure the normal operation of the equipment.

[0126] Step 104, 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 through Ethernet, and the real-time simulator, the bus interface, the acquisition and control interface module, the boundary test and fault injection module, the test power module and the test load module are respectively connected to the airborne system under test through test cables;

[0127] In step 104, the airborne system under test is connected to the general electric test platform, and the test program set and the test stimulus model are downloaded and deployed to the real-time simulator by an ordinary computer via Ethernet, and the airborne system under test is connected to the general electric test platform with a bus cable, a signal cable and a power cable.

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

[0129] Step 105: Test the airborne system under test driven by the test program set and the test stimulus model. Based on the test program set and the test stimulus model, drive the real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power module, test load module and other resources to perform function, performance, boundary and fault injection tests on the airborne system under test.

[0130] After step 105, the test data is recorded and outputted, for example, the real-time simulator uploads the test data and waveform to a common computer via Ethernet to display, analyze and record the data and waveform.

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

[0132] The MBSE-based general electrical testing method provided by the present invention is based on MBSE technology, uses a test program set and a simulation model to drive a general electrical testing platform, and performs test tests on aviation electrical control, power distribution, and acquisition equipment. In this method, the general electrical testing platform is universalized and can be reused in the research and development and testing of multi-satellite airborne systems (such as airborne equipment under test), with reduced test investment, high asset utilization rate, and reduced maintenance and management costs; technical personnel will focus their main efforts on the development of special simulation test models for airborne systems (including equipment), with high test efficiency and reduced workload; in addition to function, performance, and technical indicator tests, boundary tests and fault injection tests can also be performed, which expands the scope and depth of test tests and improves design quality.

[0133] Electrical test cases

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

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

[0136] The power control panel is a human-machine interface device in the cockpit. The flight crew operates the control panel and issues control commands to the aircraft power supply system.

[0137] The AC generator 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, 400Hz auxiliary AC power to the system; the transformer rectifier converts 115V AC power into 28V DC power; 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 processor to realize the primary distribution of 115V AC power; the DC distribution box is controlled by the power control board and the power processor to realize the primary distribution of 28V DC power;

[0139] The remote power control device is controlled by the power processor and the power control board to achieve secondary distribution of 115V AC power and 28V DC power. The test of the remote power control device includes electrical control, power distribution and bus cross-linking technologies, so the remote power control device is selected as a test case;

[0140] The power supply processor collects the status information of the above devices (such as power control board, AC distribution box, DC distribution box, transformer rectifier and remote power control device), performs logic solution, and controls and manages the above devices. At the same time, the power supply processor cross-links information with the electromechanical management computer and the electromechanical parameter display through the bus to upload and display power supply information. The test of the power supply processor includes a variety of bus cross-linking, solution management, electrical control, electrical collection and other technologies, so the power supply processor is selected as a test case.

[0141] Application Case 1: Power Supply Processor Test

[0142] Combination Figure 2 , Figure 5 and Figure 6 As shown, Figure 5 It is a principle block diagram of a data simulation model of an aircraft power supply system provided by the present invention; Figure 6 It is a test case diagram of a power supply processor type device under test provided by the present invention; the first step is to formulate a test plan for the power supply processor, including: explaining the purpose and nature of the test, such as C / S type test or factory acceptance test; according to the function, performance and technical indicators of the power supply processor, specifying test items such as function, performance, boundary and fault injection, and giving specific test content and methods; clarifying the test product, general electric test platform, and the test software and simulation model to be developed;

[0143] The second step is to determine the test interface, clarify the real-time simulator, bus interface, acquisition and control interface module, boundary test, fault injection, test power supply and test load, and allocate the interface resources of the general electric test platform. In this application case, according to the interface of the power supply processor, the resources of the general electric test platform are allocated as follows:

[0144] The power supply processor under test has one 1394B bus, and the real-time simulator drives one 1394B bus interface for test docking;

[0145] The 5-way RS422 bus of the power supply processor under test is driven by the real-time simulator to conduct test 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 test docking;

[0147] The tested power supply processor has two 0V / 28VDC discrete outputs, and the real-time simulator drives two discrete input interfaces DI and two 28V signal conditioning for test docking;

[0148] The power supply processor under test has a set of 0V~115V three-phase AC analog input, and the real-time simulator drives a set of analog output interfaces AO and a set of 115VAC signal conditioning for test docking;

[0149] The power supply processor under test has one 0V~28V DC analog input, and the real-time simulator drives one analog output interface AO and a set of 28V signal conditioning for test docking;

[0150] The power supply processor under test has one 28V DC working power input, and the test connection is carried out by a 28V test power supply.

[0151] The third step is to develop a test program set and a test stimulus model. According to the power supply processor test plan, develop a test program set and a test stimulus model on a common computer (using C, Matlab / Simulink, Modelica and other languages, depending on the type of real-time simulator). In this embodiment, the test stimulus model uses a simulation model. Establish a mathematical simulation model of the power supply system, such as Figure 5 As shown, it is confirmed that the system and each device are modeled accurately and the operation is in line with expectations, and can be operated according to the test items of the test plan. Figure 5 The power supply processor model is removed, and the remaining bus, discrete quantity, and analog quantity interfaces are encapsulated using the corresponding hardware driver of the general electric test platform, such as Figure 6 The left part is shown;

[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: Connect the power supply processor to the general electric test platform. Figure 6 , the ordinary computer downloads the test program set and simulation model formed in the third step to the real-time simulation machine through Ethernet; press Figure 6 , use the test cables (such as bus cables, signal cables and power cables) made in the fourth step to connect the power supply processor type equipment under test with the general electric test platform;

[0154] Step 6: Test the power processor driven by the test assembly and simulation model. Figure 6 , based on the test program set and simulation model, drive the real-time simulator, bus interface, acquisition and control interface module, test power supply and other resources to perform function, performance, boundary and fault injection tests on the power supply processor type equipment under test;

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

[0156] Application Case 2: Remote Power Control Device Test

[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 power distribution equipment under test includes remote power control devices. The first step is to formulate a test plan for the remote power control device, including: explaining the purpose and nature of the test, such as C / S type test, or factory acceptance test; specifying test items such as function, performance, boundary and fault injection according to the functions, performance and technical indicators of the remote power control device, and giving specific test content and methods; clarifying the test product, general electric test platform, and the test software and test stimulus model to be developed;

[0158] The second step is to determine the test interface, clarify the real-time simulator, bus interface, acquisition and control interface module, boundary test, fault injection, test power supply and test load resources used, and allocate the interface resources of the general electric test platform. In this application case, according to the interface of the remote power control device, the general electric test platform resources are allocated as follows:

[0159] The remote power control device under test has one RS422 bus, and the real-time simulator drives one RS422 bus interface for test docking;

[0160] The remote power control device under test has one 0V / 28VDC discrete input, and the real-time simulator drives one discrete output interface DO and one 28V signal conditioning for test docking;

[0161] The remote power control device under test has a 115V three-phase AC power input, and the real-time simulator drives the 485 bus / LAN bus and the program-controlled 115V three-phase AC test power supply to connect the power supply;

[0162] The remote power control device under test has a 28V DC working power input, and the real-time simulator drives the 485 bus / LAN bus and the program-controlled 28V DC test power supply to connect the power supply;

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

[0164] The remote power control device under test distributes power to the 28V DC load, which is connected to the 28V AC test load;

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

[0166] The third step is to develop a test program set and a test stimulus model. According to the test plan of the remote power control device, develop a test program set and a test stimulus model on a common computer (languages ​​such as C, Matlab / Simulink, Modelica, etc. can be used, depending on the type of real-time simulator). In this application case, the test stimulus model uses a simulation model. Establish a power supply system simulation model, such as Figure 5 As shown, it is confirmed that the system and each device are modeled accurately and the operation is in line with expectations, and can be operated according to the test items of the test plan. Figure 5 The model of the remote power control device is removed, and the remaining bus, discrete quantity, and power electrical interface are encapsulated with the corresponding hardware driver of the general electric test platform. The boundary and fault excitation simulation model is established. Figure 7 The left part is shown;

[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: Connect the power distribution equipment to the general electric test platform. Figure 7 , the ordinary computer downloads the test program set and simulation model formed in the third step to the real-time simulation machine through Ethernet; press Figure 7, use the test cables (such as bus cables, signal cables and power cables) made in the fourth step to connect the power distribution equipment under test with the general electric test platform;

[0169] Step 6: Test the power processor driven by the test assembly and simulation model. Figure 7 , based on the test program set and simulation model, drive the real-time simulator, bus interface, acquisition and control interface model, test power supply and other resources to perform function, performance, boundary and fault injection tests on the power supply processor;

[0170] Step 7: Test data recording and output. The real-time simulator uploads the test data and waveform to a common computer via Ethernet to display, analyze and record the data and waveform.

[0171] Although some specific embodiments of the present invention have been described in detail by way of example, it will be appreciated by those skilled in the art that the above examples are for illustration only and are not intended to limit the scope of the present invention. It will be appreciated by those skilled in the art that the above embodiments may be modified without departing from the scope and spirit of the present invention. The scope of the present invention is defined by the appended claims.

Claims

1. A general electrical test platform based on MBSE, characterized in that: It includes real-time simulator, bus interface, acquisition and control interface module, boundary test and fault injection module, test power 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 the test stimulus model, and to schedule resources in real time according to the solution results to complete the test task of the airborne system under test, wherein the resources include the bus interface, the acquisition and control interface module, the signal injection, the test power module and the test load module, and the test task of the airborne system under test includes power distribution, command control, signal acquisition, boundary signal injection and fault signal injection; The bus interface, one end of which is connected to the real-time simulator, and the other end of which is connected to the interface of the tested airborne system, is used to meet the bus communication test requirements of the tested airborne system; The acquisition and control interface module, one end of which is connected to the real-time simulator, and the other end of which is connected to the interface of the airborne system under test, is used to meet the command control and signal test requirements when testing the airborne system under test, wherein 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 opening quantity interface and a signal conditioning resource interface, wherein the discrete quantity interface is used to process discrete digital signals in the airborne system under test; the voltage analog quantity interface is used to acquire and control the voltage signal of the airborne system under test; the current analog quantity interface is used to acquire and control the current signal of the airborne system under test; the resistance analog quantity interface is used to acquire changes in resistance value in the airborne system under test; the opening quantity interface is used to receive and send switch state signals of the airborne system under test; and the signal conditioning resource interface is used to condition analog signals input into the airborne system under test; The boundary test and fault injection module is used to test the working ability of the tested airborne system under extreme boundary conditions and to detect the environmental adaptability and fault detection of the tested airborne system; The test power supply 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 supply for 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 an electrical device as a simulated load of the airborne system under test to detect the load and overload protection of the airborne system under test; The interface adapter is used to organize the corresponding interfaces in the real-time simulation machine, the bus interface, the acquisition and control interface module, the boundary test and fault injection module, the test power module and the test load module, and connect them to the interface adapter box.

2. The general electrical test platform based on MBSE according to claim 1, characterized in that: 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 a discrete signal of the airborne system under test, and the discrete quantity output interface is used to send a discrete signal 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, wherein the voltage analog quantity input interface is used to collect the voltage signal from the airborne system under test, and the voltage analog quantity output interface is used to output a control signal or an excitation signal 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, 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.

3. The general electrical test platform based on MBSE according to claim 1, characterized in that: The interface adaptation includes bus communication interface adaptation, acquisition control interface adaptation and power supply interface adaptation; The real-time simulator and the bus interface are respectively connected to the tested airborne system via the bus communication interface adapter; The acquisition and control interface module is connected to the tested airborne system through a part of the acquisition control 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 part of the acquisition control interface adapter; The acquisition and control interface module is connected to the onboard system under test through a part 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 part of the power supply interface adapter.

4. A general electrical testing method based on MBSE, applied to a general electrical testing platform based on MBSE, wherein the general electrical testing platform based on MBSE is the general electrical testing platform based on MBSE according to any one of claims 1 to 3, characterized in that: Determine interface resources according to the interface type, quantity, function and performance parameters of the airborne system under test, and allocate interface resources of the general electric test platform; Developing a test program set and a test stimulus model on a host computer, wherein the test program set and the test stimulus model include an interface driver; Making test cables according to the interface type and quantity of the tested airborne system, wherein the test cables include bus cables, signal cables and power cables; The host computer downloads the test program set and the test stimulus model through Ethernet and deploys them to the real-time operating system in the real-time simulator, and the real-time simulator, the bus interface, the acquisition and control interface module, the boundary test and fault injection module, the test power module and the test load module are respectively connected to the tested airborne system through 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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