Semi-physical test platform for aviation system

Abstract

The invention discloses an aviation system semi-physical test platform, and relates to the technical field of equipment testing. The system comprises a simulator test device, a risk control finished product cabinet, an Ethernet switch, a programmable power supply, a timing system device, a reflection memory switch and a closed-loop flight simulation environment. Wherein all signals in a flight control computer (GNCC) are introduced into the simulator test equipment through a test cable, are serially output from the simulator test equipment and are connected back to finished products such as a navigation sensor and an actuator, and then various test data in a closed-loop flight simulation environment are grabbed through a reflective memory network and a bus network for further analysis. Therefore, whether the flight control computer can accurately, effectively and timely realize flight control is judged, and various tests on the flight control computer can be completed through one set of system. And a large amount of time for equipment connection, environment establishment and test control is not needed.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of device testing, in particular to an aviation system semi-physical test platform. BACKGROUND

[0002] The GNC computer (GNNCC) is a computer device widely used in the field of aviation. In the product acceptance test, it is combined with the servo actuating system and the navigation sensor to perform open-loop testing of the product. In the integrated test of the GNC subsystem and the interlinked system, it is combined with the interfaces of each product and the airborne product with interlinking relationship to perform open-loop functional integrated testing.

[0003] Therefore, the GNC computer involves the generation, maintenance and switching of discrete and continuous signals, and the execution of each function directly affects the execution accuracy of the final test and even directly affects the success of the test. It should be tested to ensure that it can work stably and accurately.

[0004] However, the existing test platform does not target the GNC computer, and only relies on manual function testing. Therefore, an aviation system semi-physical test platform is needed to solve the technical problem of spending a lot of time connecting devices, building environments and testing control by relying on manual function testing. SUMMARY

[0005] The purpose of the present application is to overcome the shortcomings of the background art and provide an aviation system semi-physical test platform, which aims to realize the power supply of the GNC computer and the navigation sensor, the disconnection of the external interface, the signal acquisition and conditioning of the external interface, the switching of the physical model of the GNC computer interlinked device, the digital model simulation of the GNC computer interlinked device, the disconnection of the interface of the navigation device, the switching of the physical model of the interlinked device, and the digital model simulation of the interlinked device.

[0006] The purpose of the present application is achieved by the following technical solution: The present application provides an aviation system semi-physical test platform, comprising a simulator test device, a GNC product cabinet, an Ethernet switch, a programmable power supply, a timing device, a reflective memory switch and a closed-loop flight simulation environment, wherein, The simulator test device is set by an FPGA board and is installed with an embedded computer system, and is electrically connected with the GNC product cabinet, the Ethernet switch, the programmable power supply, the timing device, the reflective memory switch and the closed-loop flight simulation environment, respectively; The GNC product cabinet, the simulator test device and the closed-loop flight simulation environment are further connected by a 1553 bus network, the Ethernet switch is further electrically connected with the GNC product cabinet, the closed-loop flight simulation environment and the programmable power supply through Ethernet, and the reflective memory switch forms a reflective memory network and is electrically connected with the closed-loop flight simulation environment.

[0007] As a further solution, the FPGA board card comprises an MCU, a synchronous timing module, a DIDO module serial port, a serial port receiving module, a serial port sending module, an AIAO module, an input navigation plug and an output navigation plug; wherein, The MCU is electrically connected with the synchronous timing module, the DIDO module, the serial port receiving module, the serial port sending module and the AIAO module respectively, and the synchronous timing module is further electrically connected with a timing device through an optical port; The DIDO module is further provided with a DI conditioning module and a DO conditioning module, and is electrically connected with the input navigation plug and the output navigation plug respectively; The serial port receiving module and the serial port sending module are further provided with a serial port conditioning module, and are electrically connected with the input navigation plug and the output navigation plug respectively; The AIAO module is further provided with an AI conditioning module and an AO conditioning module, and is electrically connected with the input navigation plug and the output navigation plug respectively; The input navigation plug and the output navigation plug are further electrically connected with a power supply navigation plug through a single-pole single-throw switch, and the programmable power supply is electrically connected with the power supply navigation plug through a power supply handle.

[0008] As a further solution, the embedded computer system is provided with a main control software, comprising an application layer and an intermediate layer; wherein, The application layer comprises a finished product power-on module, an ICD management module, a signal acquisition module, a data monitoring module, a communication configuration module, a switch control / simulation module, a simulation control module, a real object / model switching module, a system timing module and a data monitoring module; The intermediate layer comprises a reflective memory communication protocol, a 1553 communication protocol, an Ethernet protocol, a C / S architecture and a VxWorks operating system; wherein, the embedded computer system is externally connected with an Ethernet through a dedicated network card, completes a 1553 bus through a 1553 simulation card, and is externally connected with a reflective memory network through a reflective memory card.

[0009] As a further solution, the closed-loop flight simulation environment is provided with a navigation sensor and an actuator; wherein, the navigation sensor and the actuator are electrically connected with a cable conversion optical terminal through a navigation plug, the cable conversion optical terminal is externally extended through cooperation of an optical port and an optical cable, and is electrically connected with an output navigation plug through a navigation plug.

[0010] As a further solution, the risk control finished product cabinet is provided with a GNNCC simulator and a monitoring hardware; wherein, the GNNCC simulator is connected with a bus network through a 1553 bus, and is electrically connected with an input navigation plug through a navigation plug; the monitoring hardware comprises a sensor detection module, an air duct temperature control module and an emergency alarm module, and is connected with an Ethernet respectively.

[0011] As a further solution, the time system device comprises a time-providing antenna, a high-precision internal clock source, a clock signal processing subsystem, a clock synchronization signal generation subsystem and a clock synchronization signal driving subsystem; wherein, The time-providing antenna, the high-precision internal clock source and the clock signal processing subsystem are electrically connected in sequence, the clock signal processing subsystem is further electrically connected with an external clock and the clock synchronization signal generation subsystem respectively, the clock synchronization signal generation subsystem is electrically connected with a second pulse and the clock synchronization signal driving subsystem respectively, and the clock synchronization signal driving subsystem is provided with an optical port and a 422 serial port respectively.

[0012] The aviation system semi-physical test platform provided by the application has at least the following beneficial effects: The application introduces all signals in a flight control computer (GNCC) into a simulator test device through a test cable, and connects back to navigation sensors and actuators and other finished products from the simulator test device, and further analyzes each test data in a closed-loop flight simulation environment through a reflection memory network and a bus network to determine whether the flight control computer can accurately, effectively and timely realize flight control, and thus each test of the flight control computer can be completed through a system. BRIEF DESCRIPTION OF DRAWINGS

[0013] The accompanying drawings, which are incorporated into and form part of the specification, illustrate embodiments consistent with the present application and, together with the specification, serve to explain the principles of the application.

[0014] In order to more clearly illustrate the technical solutions in the embodiments of the application or the related art, the accompanying drawings needed to be used in the embodiments or the related art description will be briefly introduced. Obviously, for those skilled in the art, other drawings can also be obtained without creative labor based on these drawings.

[0015] Figure 1 A schematic structural diagram of an aviation system semi-physical test platform provided by the application is shown in the figure. Figure 2 A schematic diagram of a GNCC simulator provided by the application is shown in the figure. Figure 3 A schematic diagram of a cable switching provided by the application is shown in the figure. Figure 4 A schematic diagram of a main control test software architecture provided by the application is shown in the figure. Figure 5 A schematic diagram of a main control control process provided by the application is shown in the figure. Figure 6 A schematic diagram of a comprehensive control interface provided by the application is shown in the figure. Figure 7A 1553 simulation main interface schematic diagram provided by the application is shown in the figure; The object, technical solutions and advantages of the present application will be further described with reference to the embodiments and the accompanying drawings. DETAILED DESCRIPTION

[0016] To make the object, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the accompanying drawings. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. The components of the embodiments of the present application described and shown in the accompanying drawings can be arranged and designed in various different configurations.

[0017] With reference to the accompanying Figure 1 The application discloses an aviation system semi-physical test platform, which comprises a simulator test device, a wind control finished product cabinet, an Ethernet switch, a programmable power supply, a timing device, a reflective memory switch and a closed-loop flight simulation environment. The simulator test device is set through an FPGA board and is installed with an embedded computer system and is electrically connected with the wind control finished product cabinet, the Ethernet switch, the programmable power supply, the timing device, the reflective memory switch and the closed-loop flight simulation environment respectively. The wind control finished product cabinet, the simulator test device and the closed-loop flight simulation environment are further connected through a bus network of a 1553 bus, the Ethernet switch is further electrically connected with the wind control finished product cabinet, the closed-loop flight simulation environment and the programmable power supply through an Ethernet respectively, and the reflective memory switch forms a reflective memory network and is electrically connected with the closed-loop flight simulation environment.

[0018] It should be noted that: all signals in the flight control computer (GNCC) are introduced into the simulator test device through a test cable in the embodiment, and are output from the simulator test device and connected back to the navigation sensors and actuators and other finished products, and then each test data in the closed-loop flight simulation environment is captured through the reflective memory network and the bus network for further analysis, so as to determine whether the flight control computer can accurately, effectively and timely realize flight control, and then each test of the flight control computer can be completed through a set of system.

[0019] The simulator test device uses a main control software to collect analog quantities of sensors of the measured flight control computer, outputs and controls instructions, collects and controls discrete quantities, and processes and switches serial port signals; the whole system is uniformly timed by the timing device to ensure time sequence synchronization, the simulator test device processes and collects finished product signals, and has no broken line and switching function.

[0020] On this basis, the simulator test equipment simulates the power supply of the aircraft to the flight control system and the finished power supply test, analyzes the experimental data, and compares with the simulation data in other test environments to ensure the open-loop and closed-loop tests of the finished flight control product; the flight control computer is monitored and protected by the flight control product cabinet, and the monitoring data is transmitted through Ethernet; the optical port is used for time-sensitive data transmission, such as time signal and test signal.

[0021] Specifically, the FPGA board of the simulator test equipment includes an MCU, a synchronous timing module, a DIDO module serial port, a serial port receiving module, a serial port sending module, an AIAO module, an input navigation plug, and an output navigation plug; wherein, The MCU is electrically connected with the synchronous timing module, the DIDO module, the serial port receiving module, the serial port sending module, and the AIAO module, and the synchronous timing module is further electrically connected with the timing device through the optical port; The DIDO module is further provided with a DI conditioning module and a DO conditioning module, and is electrically connected with the input navigation plug and the output navigation plug, respectively; The serial port receiving module and the serial port sending module are further provided with a serial port conditioning module, and are electrically connected with the input navigation plug and the output navigation plug, respectively; The AIAO module is further provided with an AI conditioning module and an AO conditioning module, and is electrically connected with the input navigation plug and the output navigation plug, respectively; The input navigation plug and the output navigation plug are further electrically connected with the power supply navigation plug through a single-pole single-throw switch, and the programmable power supply is electrically connected with the power supply navigation plug through a power supply handle.

[0022] It should be noted that the traditional programmable power supply also needs to be independently set with a controller, and the embodiment is to issue the control of each signal through the MCU in the FPGA to generate the corresponding power supply signal to control the single-pole single-throw switch, thereby realizing the on-off control of the programmable power supply, and the Ethernet realizes the specific programmable power supply control function.

[0023] As shown in Figure 2 The embodiment further sets a GNCC simulator in the flight control product cabinet to realize the test operation when the flight control computer is not online, or to set a test control group for comparison; wherein, the module structure diagram of the GNCC simulator is as shown in Figure 2 It mainly includes a main control system board, an embedded control board, a serial communication board, a digital input board, and a digital output board; and the clock synchronization and mutual connection are realized through the backplane. Specifically, the main control system board adopts COM Express Compact modular computer; the embedded control board adopts PowerPC+FPGA architecture, and performs data interaction with the serial communication board, digital output board, digital input board and electronic break board on the backboard through Local BUS bus; the serial communication board realizes bidirectional asynchronous RS422, unidirectional output asynchronous RS422 and unidirectional input synchronous RS422 serial ports in the FPGA on the board through the Local BUS of the embedded board.

[0024] The digital input performs signal conditioning on the balanced digital signal, 0 / 5V level digital signal and OC gate digital signal on the board, converts the signals into LVTTL signals that can be collected by the CPLD, and reads the corresponding digital input by the embedded control board through the Local BUS on the backboard; the digital output board outputs control signals through the Local BUS+CPLD of the embedded board, and outputs the corresponding balanced digital signal, 0 / 5V level digital signal and OC gate digital signal after the conditioning circuit.

[0025] The embedded computer system is provided with a main control software, including an application layer and an intermediate layer; wherein, The application layer includes a finished product power-on module, an ICD management module, a signal acquisition module, a data monitoring module, a communication configuration module, a switch control / simulation module, a simulation control module, a real object / model switching module, a system timing module and a data monitoring module; The intermediate layer includes a reflective memory communication protocol, a 1553 communication protocol, an Ethernet protocol, a C / S architecture and a VxWorks operating system; wherein, the embedded computer system is externally connected with the Ethernet through a special network card, completes the 1553 bus through a 1553 simulation card, and is externally connected with the reflective memory network through a reflective memory card.

[0026] It should be noted that the main control software is the basis for realizing the overall function, and on this basis, the test function is realized in combination with the main control test software, and the architecture diagram of the main control test software is as Figure 4 shown; wherein, the main control test software realizes electrical signal excitation of the device under test, power on / off control, and provides a man-machine monitoring interface for test process control, data analysis and data processing, simultaneously realizes remote control of other test and control software through the network interface by calling the DIF and 1553 simulation software interface. The interface provides button-arranged excitation signals and one-key wheel load excitation switching functions.

[0027] The following introduces the function division of the main control test software: The board drive module: the device realizes memory configuration file addition to the software ICD directory and electrical signal excitation of the device under test through the drive reflective memory card and serial card, realizes digital output excitation, and cooperates with the break box to output power type on / off signals and other signals.

[0028] Programmable power control module: provides a human-machine monitoring interface for test process control, data analysis, and data processing. The interface arranges GNCC and sensor excitation signals through buttons for easy user operation. At the same time, the interface also provides a one-key wheel load excitation switching function to quickly switch different excitation signals. Users can start, stop, and pause the test through the human-machine monitoring interface.

[0029] At the same time, fault handling and alarm mechanisms are introduced in the software to monitor the status of the excitation board and the programmable power supply in real time. If abnormal conditions are found (such as communication failure, power failure, etc.), timely alarms and corresponding handling measures are taken to ensure the reliability and safety of the test process.

[0030] Control module: contains programmable power control and other measurement and control software control functions.

[0031] Programmable power control module: controls the power on and off of the device under test to simulate actual use and test VMC power failure logic functions. The power supplied to the GNCC can be independently controlled, and the voltage range of each power supply can be adjusted. The specific independent control and voltage range adjustment functions should be implemented according to specific requirements.

[0032] Other measurement and control software control: obtains the status information of other measurement and control software returned by the human-machine monitoring module, controls the online software through the network / serial port, realizes the remote operation of the core functions of this part of the software, and realizes the unified scheduling of system signal timing. This software as the master control uses the control flow as shown in Figure 5 , sends running commands to each software in broadcast form through network / serial port signals. At the same time, the master control receives software running state data (including running state, key parameters) through the network / serial port to obtain the actual running state of each software.

[0033] Human-machine monitoring module: provides a human-machine monitoring interface for test process control, data analysis, and data processing. The interface arranges GNCC and sensor excitation signals through buttons for easy user operation. At the same time, the interface also provides a one-key wheel load excitation switching function to quickly switch different excitation signals. Users can start, stop, and pause the test through the human-machine monitoring interface.

[0034] At the same time, fault handling and alarm mechanisms are introduced in the software to monitor the status of the excitation board and the programmable power supply in real time. If abnormal conditions are found (such as communication failure, power failure, etc.), timely alarms and corresponding handling measures are taken to ensure the reliability and safety of the test process.

[0035] User permission management module: In order to ensure the safety of the test process and the confidentiality of the data, a user permission management function can be introduced. According to the identity and permission level of the user, the access and control range of the user to the software function and operation are limited, so that only authorized personnel can perform sensitive operations and access sensitive data.

[0036] Data processing module: The software can realize automated test process and operation, and can introduce script automation function. Users can write scripts to define specific test steps and operations, including setting of excitation signal, control of power supply, data acquisition and analysis, etc. The software will execute the corresponding actions according to the order and parameters defined in the script, improving the efficiency and accuracy of the test. At the same time, users can perform statistical, plotting and export storage operations on test data through the man-machine monitoring interface.

[0037] 1553 simulation module: The software mainly cooperates with the control computer, 1553B bus card, coupler, cable and other hardware to realize the interface test function with the flight control computer; including: 1) configure communication data; 2) select the 1553 address of the flight control computer; 3) define the basic data characteristics of the data block; 4) send data file; 5) receive data; 6) stop receiving; 7) exit the software.

[0038] Interface design: The interface of the software includes power control, hardware setting check, switch switching interface and 1553 simulation communication interface, and the comprehensive control interface is as shown in Figure 6 , and the 1553 simulation main interface is as shown in Figure 7 .

[0039] External interface: The software provides a software control interface, including software state, state control and core function interface, which supports external software to monitor and operate the test software in real time through the provided interface.

[0040] Interface design: The API interface function support platform is WIN XP / 7 / 10, and the development software platform is Microsoft Visual C++ of Microsoft Corporation. The functions are divided into two categories. The first category is basic functions, such as initializing the card, allocating resources and releasing resources. It is effective for all protocol modules and can be executed once. The second category is special functions, mainly used for data transmission, including BC, RT and BM function functions.

[0041] Further, the closed-loop flight simulation environment is provided with navigation sensors and actuators; since the finished product signal comes out from the main control test system, the distance from the aircraft end is far away, and the low-frequency signal attenuates seriously; therefore, a cable conversion optical transceiver is designed to convert at both ends, and the conversion schematic is as shown in Figure 3 .

[0042] Further, in order to ensure normal operation of the equipment; the risk control finished product cabinet is provided with a GNNCC simulator and monitoring hardware; wherein the GNNCC simulator is connected with the bus network through a 1553 bus and is electrically connected with the input plug through the plug; the monitoring hardware includes a sensor detection module, an air duct temperature control module and an emergency alarm module and is respectively connected with an Ethernet.

[0043] The timing device comprises a timing antenna, a high-precision internal clock source, a clock signal processing subsystem, a clock synchronization signal generation subsystem and a clock synchronization signal driving subsystem; wherein, The timing antenna, the high-precision internal clock source and the clock signal processing subsystem are electrically connected in sequence, the clock signal processing subsystem is further electrically connected with an external clock and the clock synchronization signal generation subsystem respectively, the clock synchronization signal generation subsystem is electrically connected with a second pulse and the clock synchronization signal driving subsystem respectively, and the clock synchronization signal driving subsystem is provided with an optical port and a 422 serial port respectively.

[0044] The above is only part of the embodiments of the present application, and does not limit the patent scope of the present application, and any equivalent structural transformation made by using the content of the present application specification and drawings, or direct / indirect application in other related technical fields is included in the patent protection scope of the present application.

Claims

1. A semi-physical test platform for aviation systems, characterized in that: Including simulator test equipment, risk control cabinet, Ethernet switch, programmable power supply, timing equipment, reflective memory switch and closed-loop flight simulation environment; among them, The simulator test equipment is configured with an FPGA board and is equipped with an embedded computer system, and is electrically connected to the risk control cabinet, Ethernet switch, programmable power supply, timing equipment, reflective memory switch, and closed-loop flight simulation environment. The risk control finished product cabinet, simulator test equipment and closed-loop flight simulation environment are also connected to a bus network via a 1553 bus. The Ethernet switch is also electrically connected to the risk control finished product cabinet, closed-loop flight simulation environment and programmable power supply respectively via Ethernet. The reflective memory switch constitutes a reflective memory network and is electrically connected to the closed-loop flight simulation environment.

2. The semi-physical test platform for aviation systems according to claim 1, characterized in that: The FPGA board includes an MCU, a synchronous timing module, a DIDO module serial port, a serial port receiving module, a serial port sending module, an AIAO module, an input aviation plug and an output aviation plug; wherein, The MCU is electrically connected to the synchronous timing module, DIDO module, serial port receiving module, serial port sending module and AIAO module respectively, and the synchronous timing module is also electrically connected to the time system device through the optical port; The DIDO module is further provided with a DI conditioning module and a DO conditioning module, which are electrically connected to the input aviation plug and the output aviation plug respectively; The serial port receiving module and the serial port sending module are further provided with a serial port conditioning module, and are electrically connected to the input aviation plug and the output aviation plug respectively; The AIAO module is further provided with an AI conditioning module and an AO conditioning module, which are electrically connected to the input aviation plug and the output aviation plug respectively; The input aviation plug and the output aviation plug are also electrically connected to the power supply aviation plug through a single-pole single-throw switch, and the programmable power supply is electrically connected to the power supply aviation plug through a power wiring handle.

3. The semi-physical test platform for aviation systems according to claim 2, characterized in that: The embedded computer system is provided with a main control software, including an application layer and an intermediate layer; wherein, The application layer includes a finished product power-on module, an ICD management module, a signal acquisition module, a data monitoring module, a communication configuration module, a switch control / simulation module, a simulation control module, a physical / model switching module, a system timing module, and a data monitoring module; The intermediate layer includes reflective memory communication protocol, 1553 communication protocol, Ethernet protocol, C / S architecture and VxWorks operating system; wherein, the embedded computer system is connected to Ethernet through a dedicated network card, completes the 1553 bus through a 1553 emulation card, and is connected to the reflective memory network through a reflective memory card.

4. The semi-physical test platform for aviation systems according to claim 3, characterized in that: The closed-loop flight simulation environment is provided with a navigation sensor and an actuator; wherein, the navigation sensor and the actuator are electrically connected to a cable-converting optical terminal through an aviation plug; the cable-converting optical terminal is externally extended through an optical port and an optical cable, and is electrically connected to an output aviation plug through an aviation plug.

5. The semi-physical test platform for aviation systems according to claim 2, characterized in that: The wind control finished product cabinet is equipped with a GNNCC simulator and monitoring hardware; wherein, the GNNCC simulator is connected to the bus network through a 1553 bus and electrically connected to the input aviation plug through an aviation plug; the monitoring hardware includes a sensor detection module, an air duct temperature control module and an emergency alarm module and is respectively connected to the Ethernet.

6. The semi-physical test platform for aviation systems according to claim 2, characterized in that: The timing equipment includes a timing antenna, a high-precision internal clock source, a clock signal processing subsystem, a clock synchronization signal generation subsystem and a clock synchronization signal driving subsystem; wherein, The timing antenna, high-precision internal clock source and clock signal processing subsystem are electrically connected in sequence. The clock signal processing subsystem is also electrically connected to the external clock and the clock synchronization signal generation subsystem respectively. The clock synchronization signal generation subsystem is electrically connected to the second pulse and the clock synchronization signal driving subsystem respectively. The clock synchronization signal driving subsystem is respectively provided with an optical port and a 422 serial port.

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