Flight control system test equipment

Abstract

The utility model relates to the technical field of equipment detection devices, in particular to flight control system test equipment, which comprises a power supply module, a tested product interface, a switch module, a simulation test module and an industrial personal computer, and is characterized in that the simulation test module comprises a PXI controller, an FC board card, an ARINC429 bus board card, a serial port board card, an LVDT / RVDT simulation board card and a Hall signal simulation board card; and the FC board card, the ARINC429 bus board card, the serial port board card, the LVDT / RVDT simulation board card and the Hall signal simulation board card are respectively in communication connection with the PXI controller. According to the utility model, the automation degree of finished product verification is improved, the verification time is shortened, and the verification efficiency is improved.

Description

Technical Field

[0001] This utility model relates to the technical field of equipment testing devices, specifically to a flight control system testing device. Background Technology

[0002] Flight control system testing equipment is used to test the basic functions of fly-by-wire control computer, fly-by-wire flight control console and inertial measurement unit before installation. Its main tests include power supply, communication interface, basic functions and performance. Currently, the above tests are mostly carried out by separate testing devices, which have a complicated testing process and low inspection efficiency. Utility Model Content

[0003] In view of the shortcomings of the existing technology, the purpose of this utility model is to provide a flight control system test device.

[0004] To achieve the above objectives, this utility model provides the following technical solution: a flight control system test device, comprising a power supply module, a product under test interface, a switch module, a simulation test module, and an industrial control computer. The simulation test module includes a PXI controller, an FC board, an ARINC429 bus board, a serial port board, an LVDT / RVDT simulation board, and a Hall signal simulation board. The FC board, ARINC429 bus board, serial port board, LVDT / RVDT simulation board, and Hall signal simulation board are respectively connected to the PXI controller for communication. Furthermore, the FC board, ARINC429 bus board, serial port board, LVDT / RVDT simulation board, and Hall signal simulation board are connected to the switch module and then to the product under test interface. The industrial control computer includes a host computer and a distributed quantity simulation board and an analog quantity simulation board connected to the host computer for communication. The distributed quantity simulation board and the analog quantity simulation board are respectively connected to the PXI controller. The host computer is connected to the control terminal of the switch module. The power supply module is used to supply power to both the simulation test module and the industrial control computer.

[0005] In some embodiments, the power supply module includes a power controller, a power adapter box, an excitation power adapter box, and a direct current controlled power supply. The power controller is used to control the connection of the power adapter box, the excitation power adapter box, and the direct current controlled power supply. The power adapter box is used to supply power to the PXI controller and the industrial computer. The excitation power adapter box is used to supply power to the LVDT / RVDT simulation board. The direct current controlled power supply is used to supply power to the FC board, the ARINC429 bus board, the serial port board, and the Hall signal simulation board.

[0006] In some embodiments, the switch module includes two interface connectors and a number of microswitches. The number of microswitches is consistent with the number of connection ports of the FC board, ARINC429 bus board, serial port board, LVDT / RVDT simulation board, and Hall signal simulation board. One end of the microswitch is connected to one of the interface connectors and then connected to the corresponding FC board, ARINC429 bus board, serial port board, LVDT / RVDT simulation board, or Hall signal simulation board. The other end of the microswitch is connected to another interface connector and then connected to the interface of the product under test.

[0007] In some embodiments, the product under test has multiple interfaces.

[0008] In some embodiments, each of the interfaces of the product under test is connected in series with an independent switch module.

[0009] In some embodiments, the experimental equipment further includes a display, a printer, and a workbench, wherein the display and printer are respectively communicatively connected to a host computer, and the display, printer, and host computer are mounted on the workbench.

[0010] Compared with the prior art, the beneficial effects of this utility model are: the equipment of this application is used to test the basic functions of the fly-by-wire control computer, fly-by-wire flight control console and inertial measurement components before installation, including power supply, communication interface and basic functions and performance, which simplifies the test operation steps, improves the automation level of finished part verification, shortens the verification time and improves the verification efficiency.

[0011] Details of one or more embodiments of this application are set forth in the following drawings and description to make other features, objects and advantages of this application more readily apparent. The embodiments of this application will provide a detailed description and understanding of the application. Attached Figure Description

[0012] Figure 1 This is a system module diagram of the present invention;

[0013] Figure 2 This is a schematic diagram of the switch module connection of this utility model;

[0014] Figure 3 This is a diagram showing the interconnectivity of the fly-by-wire flight control system.

[0015] Figure 4 A schematic diagram of the cross-linking of the fly-by-wire flight control system for the flight control system test equipment;

[0016] Figure 5 A schematic diagram of the cross-linking of the fly-by-wire flight control system for the flight control system test equipment;

[0017] Figure 6This is a schematic diagram of the cross-linking test interface for the fly-by-wire flight control computer.

[0018] Figure 7 This is a block diagram illustrating the working principle of the flight control system test equipment.

[0019] Figure 8 Functional block diagram of the signal simulation test machine.

[0020] In the diagram: 1. Power supply module; 2. Interface of the product under test; 3. Switch module; 4. Simulation test module; 5. Industrial computer; 6. Monitor; 7. Printer; 8. Interface connector; 9. Micro switch. Detailed Implementation

[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0022] Please see Figure 1 This utility model provides a technical solution: a flight control system test device, including a power supply module, a product under test interface, a switch module, a simulation test module, and an industrial control computer. The simulation test module includes a PXI controller, an FC board, an ARINC429 bus board, a serial port board, an LVDT / RVDT simulation board, and a Hall signal simulation board. The FC board, ARINC429 bus board, serial port board, LVDT / RVDT simulation board, and Hall signal simulation board are respectively connected to the PXI controller for communication. The FC board, ARINC429 bus board, serial port board, LVDT / RVDT simulation board, and Hall signal simulation board are respectively connected to the switch module and then connected to the product under test interface. The industrial control computer includes a host computer and a distributed quantity simulation board and an analog quantity simulation board that are connected to the host computer for communication. The distributed quantity simulation board and the analog quantity simulation board are respectively connected to the PXI controller. The host computer is connected to the control terminal of the switch module. The power supply module is used to supply power to the simulation test module and the industrial control computer.

[0023] A fly-by-wire flight control system is a closed-loop manual control system that converts the pilot's control commands into electrical signals, integrates and processes them with feedback signals from the aircraft's attitude sensors through a computer, and outputs control signals that are transmitted to the control surface actuators via cables, thereby enabling full-authority control of the aircraft.

[0024] The fly-by-wire flight control system mainly consists of a fly-by-wire control computer, a fly-by-wire flight control console, an inertial measurement unit, tail rotor servo valves, tail rotor servo cylinders, main rotor servos, stick displacement sensors, parallel servos, and electrical transmission lines. To ensure the proper functioning of each flight control component before installation, the fly-by-wire flight control system must undergo functional and performance testing.

[0025] The fly-by-wire flight control computer receives control information from the fly-by-wire console via the HB6096 (ARINC429), attitude information from the inertial measurement unit via the RS422 bus, and position feedback information from the four propeller surfaces (forward, left, right, and tail rotor) via LVDT / RVDT / Hall signals. After comparative analysis and algorithmic calculations, it outputs commands to drive the propeller actuators and related actuators to control the propellers. Simultaneously, it transmits relevant digital or analog information to external avionics systems via the FC bus, enabling them to adjust their operating status in a timely manner and complete the corresponding actions to form a closed-loop control system.

[0026] The flight control system test equipment is mainly used for testing fly-by-wire flight control systems before installation. Considering its application scenarios, it has three main functions: First, it simulates external signals of the fly-by-wire flight control system to stimulate its operation and verify its proper functioning. Second, it simulates internal devices of the fly-by-wire system, enabling system-level testing and verification based on existing equipment even when some components are incomplete, confirming the functionality of existing components. Third, it utilizes the RS422 bus within the test interface of the fly-by-wire flight control computer to perform MBIT and DFTI tests on the fly-by-wire system.

[0027] The power supply module includes a power controller, a power adapter box, an excitation power adapter box, and a direct current controlled power supply. The power controller is used to control the connection of the power adapter box, the excitation power adapter box, and the direct current controlled power supply. The power adapter box is used to supply power to the PXI controller and the industrial computer. The excitation power adapter box is used to supply power to the LVDT / RVDT simulation board. The direct current controlled power supply is used to supply power to the FC board, the ARINC429 bus board, the serial port board, and the Hall signal simulation board.

[0028] The equipment is used to test the basic functions of the fly-by-wire control computer, fly-by-wire flight control console, and inertial measurement unit before installation, including power supply, communication interface, and basic functions and performance; the testing equipment has the following functions:

[0029] 1. Online real-time monitoring of the flight control computer's detection port in the flight control system, including self-test maintenance information and DFTI information;

[0030] 2. Test the communication functions of the fly-by-wire control computer, fly-by-wire flight control console, and inertial measurement unit of the flight control system;

[0031] 3. It can test the attitude output information of the inertial measurement unit;

[0032] 4. It can decode, display and record data from the flight test interface of the flight control computer in real time.

[0033] like Figure 2 As shown, the switch module includes two interface connectors and several microswitches. The number of microswitches is consistent with the number of connection ports of the FC board, ARINC429 bus board, serial port board, LVDT / RVDT simulation board, and Hall signal simulation board. One end of the microswitch is connected to one of the interface connectors and then connected to the corresponding FC board, ARINC429 bus board, serial port board, LVDT / RVDT simulation board, or Hall signal simulation board. The other end of the microswitch is connected to the other interface connector and then connected to the interface of the product under test.

[0034] In practical applications, to improve the testing of multiple products at once, the tested product interface is provided with multiple interfaces, and each tested product interface is connected in series with an independent switch module.

[0035] After passing through the interface connector, the test module enters the switch module. The switch module is essentially a series of single-pole double-throw microswitches with programmable control functions. The switch is divided into a common terminal, a normally open terminal, and a normally closed terminal. The common terminal is connected to the flight control computer (the product under test) through a universal interface connector. The normally closed terminal is connected to the corresponding channel of the resource board through a connector. The normally open terminal is connected to the peripheral equipment of the flight control system through a universal interface connector.

[0036] To facilitate product testing operations and provide an intuitive display of test results and text output of the results, the testing equipment also includes a monitor, a printer, and a workbench. The monitor and printer are respectively connected to the host computer, and the monitor, printer, and host computer are mounted on the workbench.

[0037] like Figure 3-6 As shown, through the technical solution of this application,

[0038] 1. Assuming all components of the fly-by-wire flight control system are in a test state, the flight control system test equipment is mainly used to simulate avionics and electromechanical equipment that are interconnected with the fly-by-wire flight control system. While stimulating the fly-by-wire flight control system to work normally, it receives data uploaded by the fly-by-wire flight control system for avionics display, etc.

[0039] When all components of the fly-by-wire flight control system are ready for testing, the flight control system test equipment simulates other onboard systems interconnected with the fly-by-wire system: it simulates the avionics integrated processor via the FC bus, and simulates signals sent to the fly-by-wire system from the altitude control, inertial navigation, and fire control systems via three ARINC429 buses. It also receives signals sent from the fly-by-wire system to the backup display, integrated display, and flight parameters via the same three ARINC429 buses. This enables the excitation of the fly-by-wire system and displays its output signals to determine whether the fly-by-wire system is functioning correctly.

[0040] 2. In cases where not all components of the fly-by-wire flight control system are in a test state, the flight control system test equipment, in addition to simulating other onboard systems interconnected with the fly-by-wire flight control system, also needs to simulate equipment within the fly-by-wire flight control system that is not in a test state, in order to construct a complete fly-by-wire flight control system and enable testing of existing fly-by-wire flight control system equipment to determine whether the equipment is working properly.

[0041] When conducting related tests on fly-by-wire flight control systems, it is required that the fly-by-wire flight control computer, control console, measurement components, stick displacement sensors, etc., all be tested using actual components. For the remaining components, some may not be in a test state. Detailed requirements are as follows: One of the following five components is allowed to be missing: tail rotor servo valve / cylinder, nose main rotor servo valve, left main rotor servo valve, right main rotor servo valve, and horizontal stabilizer servo. Simulation testing using flight control system testing equipment is permitted. All four types of parallel servos (collective pitch / pitch / roll / yaw) are allowed to be missing, and simulation testing using flight control system testing equipment is permitted.

[0042] With the participation of some physical components, the remaining fly-by-wire flight control system components are simulated by simulation resources in the flight control system test equipment, thus forming a complete fly-by-wire flight control system, thereby enabling the functional and performance testing of the existing physical components of the fly-by-wire flight control system.

[0043] When testing a fly-by-wire flight control system, in addition to simulating the onboard systems connected to the external fly-by-wire system to stimulate its normal operation and judging whether the fly-by-wire system is functioning properly by monitoring the data output by the fly-by-wire system to the integrated display, backup display, flight parameters, etc., the MBIT, DIF, and DFTI interfaces of the fly-by-wire flight control computer can also be used to perform MBIT, DIF, and DFTI tests on the fly-by-wire flight control system.

[0044] The flight control system test equipment connects to the MBIT interface in the fly-by-wire flight control computer test interface through its own 1-receive-1-transmit RS422 bus channel. It sends MBIT commands to the fly-by-wire flight control computer according to the MBIT communication protocol. The fly-by-wire flight control computer receives the commands, performs a self-test according to a specific procedure, and feeds back the self-test results to the flight control system test equipment according to the communication protocol after the self-test is completed, thus completing the MBIT test of the fly-by-wire flight control system.

[0045] The flight control system test equipment connects to the DIF interface in the fly-by-wire flight control computer test interface through its own 1-receive-1-transmit RS422 bus channel, and connects to the DFTI channel in the fly-by-wire flight control computer test interface through its own RS422 bus receiving channel, thereby realizing the DFTI test and DIF test of the fly-by-wire flight control system.

[0046] The flight control system test equipment in this application is based on two parts: analysis of the system under test and testing methods. The test simulation signals to be implemented mainly include three types of signals: the first type simulates other airborne systems interconnected with the fly-by-wire flight control system; the second type simulates signals required by devices missing from the flight control system; and the third type simulates signals required for MBIT and DFTI testing of the fly-by-wire flight control system. Detailed statistics of the three types of signals are shown below:

[0047] Cross-linked airborne signals

[0048] The first category of signals, along with other airborne signals interconnected with the fly-by-wire flight control system, are categorized and statistically analyzed as follows:

[0049] FC signal

[0050] The flight control system test equipment has 3 transmit and 3 receive FC signals to simulate the interconnection between the three airborne subsystems (navigation, integrated display, and CNI) and the fly-by-wire flight control system. At the same time, the simulation signals need to be interconnected with the four channels on the fly-by-wire flight control computer. Therefore, a minimum 7 transmit and 7 receive FC bus switch is required.

[0051] ARINC429 signal

[0052] The flight control system test equipment needs to simulate airborne equipment such as radio altimeters, inertial navigation, fire control, backup display, integrated display, and flight parameters that are interconnected with the fly-by-wire flight control system. Based on the relationship between transmitting and receiving signals, the ARINC429 bus that needs to be implemented consists of 3 ARINC429 receiving channels and 3 ARINC429 transmitting channels.

[0053] Discrete signals

[0054] The statistics of discrete signals that need to be simulated and tested by the flight control system test equipment are shown in Table 1 below:

[0055] Table 1. Statistical Table of Discrete Signals

[0056]

[0057]

[0058] The first 24 signals need to be sent to 4 fly-by-wire flight control computer channels simultaneously; the remaining 8 signals need to be sent to 2 fly-by-wire flight control computer channels simultaneously.

[0059] 1) Analog signals

[0060] The flight control system test equipment needs to receive the collective pitch demodulation position H / L (±10V) output by the fly-by-wire flight control computer in order to identify the collective pitch situation.

[0061] Internal signals of the flight control system

[0062] The second category of signals consists of signals required by devices that are missing from the simulated flight control system. These signals are categorized and statistically analyzed as follows:

[0063] 1) Simulation of equipment such as tail rotor servo valves / cylinders, nose main rotor servo valves, left main rotor servo valves, right main rotor servo valves, and horizontal stabilizer servo.

[0064] When any one of the five types of equipment—tail rotor servo valve / cylinder, front main rotor servo valve, left main rotor servo valve, right main rotor servo valve, and horizontal stabilizer servo—is missing, it can be simulated using flight control system test equipment. Based on this, the signals that need to be simulated are: 4 power resistors, 4 RVDT signals, 4 LVDT signals, 2 Hall sensor signals, and 4 analog signals (pressure sensors).

[0065] 2) Simulation of equipment such as collective pitch / pitch / roll / yaw parallel servos

[0066] When all four types of parallel servos (collective pitch, pitch, roll, and yaw) are missing, they can be simulated using flight control system test equipment. Based on this, the signal that needs to be simulated is: 16 microswitches.

[0067] FTI test signal

[0068] The third category consists of signals required for MBIT and DFTI testing of the fly-by-wire flight control system during FTI testing. These signals are categorized and statistically analyzed as follows:

[0069] 1) MBIT test interface

[0070] The flight control system test equipment needs to achieve interconnection with the MBIT interface in the fly-by-wire flight control computer test interface. The required signals are: 2*2 RS422 receiving channels and 2*2 RS422 transmitting channels. A single computer only needs 2 RS422 receiving channels and 2 RS422 transmitting channels.

[0071] 2) DFTI test interface

[0072] The flight control system test equipment needs to be interconnected with the DFTI interface in the fly-by-wire flight control computer test interface. The required signals are: 2*2 RS422 receiving channels, of which a single computer only needs 2 RS422 receiving channels.

[0073] Signal Summary

[0074] Based on the above analysis, the signals that the flight control system test equipment needs to simulate during the testing process are shown in Table 2 below:

[0075] Table 2. Statistics of Test Simulation Signals from Flight Control System Experimental Equipment

[0076]

[0077] Signal implementation

[0078] Based on the above analysis, the signals that the flight control system test equipment needs to simulate are shown in Table 3, the statistical table of test simulation signals for the flight control system test equipment. The main signal simulation test implementation methods are as follows: FC signals are simulated using an FC bus board; FC signal interfaces are implemented using an FC switch; ARINC429 signals are simulated using an ARINC429 bus board; discrete signals are simulated using a discrete quantity simulation board; power resistors are implemented using fixed-value power resistors; RVDT and LVDT signals are implemented using an RVDT / LVDT simulation board; Hall sensor signals are implemented using a Hall simulation board; analog signals are implemented using an analog quantity simulation board; microswitches are implemented using single-pole double-throw switches; and RS422 buses are implemented using RS422 bus boards. A detailed statistical table of the implementation methods for each type of signal is shown below:

[0079] Table 3 Statistical Table of Test Simulation Signal Implementation

[0080]

[0081] like Figure 7 As shown, the flight control system test equipment can operate in an environment of 0℃~+40℃ using a 50~60Hz / 220~240VAC power supply. It is used for the interconnection of internal devices within the flight control system, the interconnection between the flight control system and avionics equipment, testing, and simulation. It has multiple functions including interface adaptation, test simulation, and test management. The internal interconnection and configuration of the flight control system includes interface connection and adaptation of the flight control computer, flight control console, servos, and displacement sensors, bus data monitoring, and signal simulation.

[0082] Flight control system testing equipment is crucial for pre-installation verification of flight control systems. Based on its functions, it can be divided into subsystems such as test management system, cross-linking simulation system, interface adaptation system, power supply and distribution system, and auxiliary systems. Its main purpose is to test the basic functions of the fly-by-wire control computer, fly-by-wire flight control console, and inertial measurement unit before final assembly, including power supply, signal simulation, interface adaptation, and test cables.

[0083] Its main uses and basic functions include:

[0084] 1) Provides a flight control computer test interface to enable online real-time monitoring of the flight control computer test port of the flight control system, including self-test maintenance information and DFTI information;

[0085] 2) Test the communication functions of the fly-by-wire control computer, fly-by-wire flight control console, and inertial measurement unit of the flight control system;

[0086] 3) The attitude output information of the inertial measurement unit is tested and can be parsed;

[0087] 4) It can decode, display and record data from the flight test interface of the flight control computer in real time, and can store and query test data;

[0088] 5) Complete the power-on, power-off, activation, and maintenance control of the flight control system;

[0089] 6) It has simulation setting functions for various signals, including bus signals, analog signals, and discrete signals;

[0090] 7) This device provides a control interface for external devices to invoke the device.

[0091] The flight control system test equipment was designed based on the relevant interface control documents and other technical requirements of the model. These documents and requirements were incorporated into the structural, operational, and software logic design. The structure is rational, user-friendly, and aesthetically pleasing. The equipment adopts a modular and universal design philosophy to ensure good system performance and comprehensive interfaces. Hardware selection follows the principles of high reliability and strong anti-interference capabilities. A reliability development plan was formulated to ensure stable and continuous operation of the equipment, while also providing good signal testing capabilities and self-testing functions. The specific functions of each subsystem are as follows:

[0092] 1) Test Management System

[0093] The test management system uses a workstation as its hardware core and runs test management software via Ethernet to conduct overall test control of the entire flight control system's ground verification. As a comprehensive management platform, it performs power supply and distribution control for airborne prototype components; simulation and testing control of airborne prototype component bus and non-bus data; switching control between prototype and simulation components; and the collection, analysis, processing, display, and storage of test data.

[0094] 2) Crosslinking simulation system

[0095] To implement the modular and universal requirements of the cross-linking simulation system, the simulation test machines are divided into bus signal simulation test machines and discrete / analog signal simulation test machines based on signal type. Both types of test machines are equipped with several simulation test boards for bus, analog, discrete, Hall signals, LVDT / RVDT, etc. Both test machines are connected to an Ethernet switch and controlled by a host computer-based test management system.

[0096] The cross-linking simulation system uses a bus signal simulation tester and a discrete / analog signal simulation tester as its hardware cores, and runs their respective application software to complete the corresponding signal simulation tasks.

[0097] To ensure the real-time performance of bus signal communication, the bus signal simulation test machine uses a PXIe bus industrial computer with higher bandwidth as its platform, which can fully accommodate the large data volume communication bandwidth requirements of the bus boards. The discrete / analog signal simulation test machine uses a PCI bus as its platform to uniformly control each functional board.

[0098] 3) Interface adaptation system

[0099] The interface adapter system consists of one analog signal interface box, one discrete signal interface box, one bus signal interface box, and one LVDT / RVDT / Hall signal interface box.

[0100] The signal interface box rationally allocates and switches between simulation and real-simulation inputs to the cross-linking simulation system: by fully simulating the output signals of external devices that are cross-linked with the flight control system through the interface box, the purpose of simulating the external environment of the flight control system is achieved; the signals output by the real components inside the flight control system can also be connected to the flight control computer, etc., through the interface box via test cables to realize the cross-linking of the real components inside the flight control system.

[0101] The interface adaptation system mainly performs five functions:

[0102] a) Each interface box connects the function board interface to the interface box via adapter cables according to the signal type;

[0103] b) Disconnect each cross-link signal through the disconnection block on the front panel of the interface box to facilitate testers to perform individual tests on the test simulation signal or manually inject faults at any time via the disconnection block.

[0104] c) To enable automatic switching between real and simulated components, the function board is connected to the internal switch module after passing through the disconnect block in the interface box. The switch module contains several switching channels, each channel being a single-pole double-throw switch. The switches are connected to the function board and the external airborne real components of the flight control system, respectively. The switch module is connected to the switch via Ethernet and can be remotely controlled.

[0105] d) After switching modules, the interface box introduces each channel of the function board into each pin of the J599 / 26JJ35SN connector according to the actual needs of the product under test.

[0106] e) Implement the introduction, conditioning, distribution, and transfer of test signals. The output signals of each component of the flight control system are introduced into the interface box. Each interface box distributes and conditions the signals according to the type and attributes of the signals being tested, and then interfaces with the test resources to complete the signal testing.

[0107] 4) Power supply and distribution system

[0108] The power supply and distribution system uses a DC flow control power supply, power controller, product power adapter box and excitation power adapter box as the hardware core. It controls the power system on the simulator to provide unified power supply to the flight control system components through the test management system. It can complete the monitoring of power supply voltage and current, and at the same time provide power supply to various functional components inside the test system.

[0109] 5) Auxiliary systems

[0110] It consists of a cabinet, workbench, rod displacement sensor testing fixture, test cables, etc.

[0111] like Figure 8 As shown, the signal simulation test machine needs to simulate and acquire signals including FC bus signals, ARINC429 bus signals, RS422 bus signals, discrete signals, analog voltage signals, LVDT / RVDT signals, Hall signals, etc. Among them, FC bus signals, ARINC429 bus signals, and RS422 bus signals not only need to be simulated but also acquired, and complete bus communication is achieved according to the communication protocol; while for analog signals, discrete signals, Hall signals, LVDT / RVDT signals, and other signals from internal devices of the flight control system, only simulation is required.

[0112] For the FC bus signals, discrete signals, and analog signals that connect the avionics system and the flight control system, the signal simulation test machine uses FC bus boards (in conjunction with FC switches), discrete output boards, and analog voltage output boards to simulate bus signals and non-bus signals, thereby simulating the communication between the avionics system and the flight control system.

[0113] For the ARINC429 bus signals and RS422 bus signals in the inertial measurement unit and fly-by-wire flight control console within the flight control system, the signal simulation test machine uses ARINC429 bus cards and RS422 serial communication cards to simulate ARINC429 bus signals, RS422 bus signals and discrete signals, and realizes the simulation test of the output signals of the inertial measurement unit and fly-by-wire flight control console.

[0114] For signals such as Hall signals and LVDT / RVDT signals on internal sensors and servo motors of the flight control system, the signal simulation test machine uses Hall signal simulation boards and LVDT / RCDT simulation boards to simulate the corresponding signals, so that system testing can be performed when the corresponding devices are not available.

[0115] For FTI testing of the flight control system, the signal simulation test machine uses an RS422 serial communication board to connect the MBIT and DFTI interfaces in the flight control computer's measurement and control interface, and decodes, displays and records the data in real time according to the communication protocol.

[0116] The above embodiments merely illustrate several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

[0117] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A flight control system testing device, characterized in that: The system includes a power supply module, a product under test (DUT) interface, a switch module, a simulation test module, and an industrial computer. The simulation test module includes a PXI controller, an FC board, an ARINC429 bus board, a serial port board, an LVDT / RVDT simulation board, and a Hall effect signal simulation board. The FC board, ARINC429 bus board, serial port board, LVDT / RVDT simulation board, and Hall effect signal simulation board are each connected to the PXI controller. Furthermore, the FC board, ARINC429 bus board, serial port board, LVDT / RVDT simulation board, and Hall effect signal simulation board are connected to the switch module and then to the DUT interface. The industrial computer includes a host computer and discrete quantity simulation boards and analog quantity simulation boards that communicate with the host computer. The discrete quantity simulation boards and analog quantity simulation boards are each connected to the PXI controller. The host computer is connected to the control terminal of the switch module. The power supply module supplies power to both the simulation test module and the industrial computer.

2. The flight control system test equipment according to claim 1, characterized in that: The power supply module includes a power controller, a power adapter box, an excitation power adapter box, and a direct current control power supply. The power controller is used to control the connection of the power adapter box, the excitation power adapter box, and the direct current control power supply. The power adapter box is used to supply power to the PXI controller and the industrial computer. The excitation power adapter box is used to supply power to the LVDT / RVDT simulation board. The direct current control power supply is used to supply power to the FC board, the ARINC429 bus board, the serial port board, and the Hall signal simulation board.

3. The flight control system test equipment according to claim 2, characterized in that: The switch module includes two interface connectors and several microswitches. The number of microswitches is consistent with the number of connection ports of the FC board, ARINC429 bus board, serial port board, LVDT / RVDT simulation board, and Hall signal simulation board. One end of the microswitch is connected to one of the interface connectors and then connected to the corresponding FC board, ARINC429 bus board, serial port board, LVDT / RVDT simulation board, or Hall signal simulation board. The other end of the microswitch is connected to the other interface connector and then connected to the interface of the product under test.

4. The flight control system test equipment according to claim 3, characterized in that: The product under test has multiple interfaces.

5. The flight control system test equipment according to claim 4, characterized in that: Each of the tested products has an independent switch module connected in series at its interface.

6. The flight control system test equipment according to claim 5, characterized in that: The experimental equipment also includes a monitor, a printer, and a workbench. The monitor and printer are respectively connected to the host computer, and the monitor, printer, and host computer are mounted on the workbench.

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