Ground testing device for integrated avionics system

Abstract

The utility model relates to the field of avionics testing, and provides a ground testing device for an integrated avionics system. Comprising the steps that a test box is connected with a bus data simulator, the bus data simulator is connected with an instrument unit, a control unit and a rear row unit, and the test box and the bus data simulator simulate and output corresponding communication signals and bus signals generated by other systems of the airplane to the instrument unit, the control unit and the rear row unit. The test box and the bus data simulator are used for simulating signals of other systems of an airplane, other real equipment of the airplane does not need to be integrated, the influence on the development progress of a comprehensive avionics system due to inconsistent development progress of other systems of the airplane in the development process of the airplane is overcome, and the development progress of the comprehensive avionics system is ensured. The comprehensive avionics system can be tested and verified timely and quickly, the development period of new research or modification of the comprehensive avionics system is shortened, and the overall development cost of an aircraft is reduced.

Description

Technical Field

[0001] The utility model relates to the field of avionics testing, in particular to a ground testing device for an integrated avionics system. Background Art

[0002] Modern aircraft integrated avionics systems are closely linked with other aircraft systems, and other aircraft systems need to be displayed, controlled, warned, and recorded through the integrated avionics system. During the aircraft development process, the integrated avionics system usually needs to be newly developed or modified to meet the requirements of cross-linking with other aircraft systems.

[0003] Whether it is a new or modified integrated avionics system, it has a development cycle and cost. Moreover, before installation, the newly developed or modified integrated avionics system needs to be debugged and tested with other aircraft systems to ensure that the integrated avionics system meets the corresponding requirements.

[0004] However, the development progress of other aircraft systems is not consistent. Other aircraft systems need to be cross-linked with the newly developed or modified integrated avionics system. However, due to the inconsistent development progress of other aircraft systems, the newly developed or modified integrated avionics system may not be able to complete all tests and verify all functions and performances of other aircraft systems, thereby increasing the development cycle of the integrated avionics system and even the aircraft, and further increasing the development cost. Utility Model Content

[0005] In order to solve the above problems, the utility model provides a ground test device for an integrated avionics system, comprising:

[0006] Instrument unit, control unit, rear unit, test box, bus data simulator;

[0007] The instrument unit is an instrument device installed on the aircraft dashboard, the control unit is a control device installed on the aircraft control panel, and the rear row unit is the second row of equipment installed on the aircraft and other avionics equipment on the rear fuselage of the aircraft;

[0008] The test box is connected to the bus data simulator, and the bus data simulator is connected to the instrument unit, the control unit, and the rear row unit. The test box and the bus data simulator simulate the output of corresponding communication signals and bus signals generated by other systems of the aircraft to the instrument unit, the control unit, and the rear row unit.

[0009] Optionally, a power supply unit is also included, and the power supply unit is connected to the instrument equipment, the control equipment, the second row equipment, and the other avionics equipment to supply power to the entire test device.

[0010] Optionally, the power supply unit includes a power converter, and the power converter is directly connected to the mains.

[0011] Optionally, it also includes an antenna unit, which is an antenna installed on the aircraft. The antenna on the aircraft is used to receive signals sent by a handheld radio or a navigation simulator.

[0012] Optionally, the antenna unit also includes an antenna bracket, and the antenna on the aircraft includes an antenna on the back of the aircraft and an antenna on the belly of the aircraft, the antenna on the back of the aircraft is installed above the antenna bracket, and the antenna on the belly of the aircraft is installed below the antenna bracket.

[0013] Optionally, the test box further includes earphones and a microphone for receiving and outputting voice signals.

[0014] Optionally, the instrument unit includes an instrument panel bracket, which is used to set instrument equipment on the aircraft instrument panel, and the size of the instrument panel bracket is consistent with the size of the aircraft instrument panel.

[0015] Optionally, the control unit includes a control panel bracket, which is used to set the operating equipment on the aircraft control panel, and the size of the control panel bracket is consistent with the size of the aircraft control panel.

[0016] Optionally, the rear row unit includes a rear row bracket, which is used to install the second row of equipment on the aircraft and other avionics equipment on the rear fuselage of the aircraft.

[0017] Optionally, a test bench is also included, which is used to set the instrument equipment, the control equipment, the second row equipment, the other avionics equipment, the test box and the bus data simulator, and the test bench is made of metal or wood.

[0018] In summary, the advantages and beneficial effects of the utility model are:

[0019] The utility model provides a ground test device for an integrated avionics system, which includes an instrument unit, a control unit, a rear unit, a test box, and a bus data simulator; the instrument unit is an instrument device installed on an aircraft dashboard, the control unit is a control device installed on an aircraft control panel, and the rear unit is a device installed on the second row of the aircraft and other avionics equipment on the rear fuselage of the aircraft; the test box is connected to the bus data simulator, and the bus data simulator is connected to the instrument unit, the control unit, and the rear unit; the test box and the bus data simulator simulate the output of corresponding communication signals and bus signals generated by other systems of the aircraft to the instrument unit, the control unit, and the rear unit.

[0020] The prior art generally adopts real equipment or system to connect with the integrated avionics system to test the integrated avionics system, while the utility model uses the test box and the bus data simulator to simulate the signals of other aircraft systems, and does not need to integrate other real equipment of the aircraft. It overcomes the impact of the inconsistent development progress of other aircraft systems on the development progress of the integrated avionics system during the aircraft development process, and can test and verify the integrated avionics system in a timely and rapid manner. At the same time, each unit of the integrated avionics system can be tested separately, shortening the development cycle of new or modified integrated avionics systems and reducing the overall development cost of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 A schematic diagram of a ground test device for an integrated avionics system provided in an embodiment of the utility model. DETAILED DESCRIPTION

[0022] In order to facilitate understanding by those skilled in the art, the present invention will be further described in detail below in conjunction with specific embodiments.

[0023] The utility model provides a ground test device for an integrated avionics system, such as Figure 1 As shown, including:

[0024] Instrument unit 10, operating unit 20, rear unit 30, test box 40, bus data simulator 50;

[0025] The instrument unit 10 is an instrument device installed on the aircraft dashboard, the control unit 20 is a control device installed on the aircraft control panel, and the rear row unit 30 is a device installed on the second row of the aircraft and other avionics equipment on the rear fuselage of the aircraft;

[0026] The test box 40 is connected to the bus data simulator 50, and the bus data simulator 50 is connected to the instrument unit 10, the control unit 20, and the rear unit 30. The test box 40 and the bus data simulator 50 simulate the output of corresponding communication signals and bus signals generated by other systems of the aircraft to the instrument unit 10, the control unit 20, and the rear unit 30.

[0027] Specifically, in this embodiment, the other aircraft systems are one or more of a hydraulic system, an electrical system, an engine system, and a fuel system.

[0028] In this embodiment, a power supply unit is also included. The power supply unit is connected to the instrument equipment, the control equipment, the second row equipment and other avionics equipment to supply power to the entire test device.

[0029] In this embodiment, the power supply unit includes a power converter, and the power converter is directly connected to the mains.

[0030] The power converter is selected according to the voltage and power of the entire integrated avionics system.

[0031] In this embodiment, the power converter is selected according to the maximum power of all the installation and testing equipment when they are working, and the power converter is convenient for being directly connected to the mains.

[0032] In this embodiment, the power converter converts the mains power into a 28V voltage to power the test equipment.

[0033] In this embodiment, an antenna unit is also included. The antenna unit is an antenna installed on the aircraft. The antenna on the aircraft is used to receive signals sent by a handheld radio or a navigation simulator.

[0034] In this embodiment, the antenna unit also includes an antenna bracket, and the antenna on the aircraft includes an antenna on the back of the aircraft and an antenna on the belly of the aircraft. The antenna on the back of the aircraft is installed above the antenna bracket, and the antenna on the belly of the aircraft is installed below the antenna bracket.

[0035] In this embodiment, the antenna bracket is made of metal material to facilitate grounding of the antenna.

[0036] The antenna is a real antenna on the aircraft, which is used to receive signals from a handheld radio and a navigation simulator, wherein the handheld radio transmits communication radio wave signals, and the navigation simulator simulates the radio wave signals of a transponder, a rangefinder, and a Volt / Instrument Landing System, and the communication function and navigation function of the integrated avionics system are tested through the antenna.

[0037] In this embodiment, the test box 40 is a signal generator, which is used to simulate the communication signals generated by other systems of the aircraft, so as to drive the integrated avionics system to perform signal acquisition, signal display and alarm;

[0038] The bus data simulator 50 is used to simulate bus signals generated by other systems of the aircraft, thereby driving the integrated avionics system to perform signal reception, signal processing, signal display and alarm.

[0039] In this embodiment, the communication signal is one or more of a discrete signal, an analog signal, a switch signal and a frequency signal.

[0040] In this embodiment, the discrete signal is simulated using a button, and the analog signal is simulated using a knob-type sliding resistor; the frequency signal is simulated using a frequency signal generator, and the frequency range and duty cycle of the frequency signal are adjustable.

[0041] In other embodiments, the discrete signal is simulated using a toggle switch.

[0042] The control parts of the button, the knob-type sliding rheostat and the toggle switch are arranged on the operating panel of the test box.

[0043] In this embodiment, the bus signal is one or more of an ARINC429 bus signal, an RS422 bus signal, an RS232 bus signal, and a CAN bus signal.

[0044] In this embodiment, the bus signal simulator uses host computer software to facilitate real-time operation.

[0045] In this embodiment, the discrete signal includes a pitot tube heating signal; the switch signal includes a stall warning signal, a fire alarm signal and other specific signals of the aircraft; the analog signal includes a battery current signal; and the frequency signal includes a fuel level sensor signal.

[0046] In this embodiment, the ARINC429 bus signal includes a data recorder; the RS422 bus signal includes a main control board; the RS232 bus signal includes a communication navigation component; and the CAN bus signal includes an engine.

[0047] In this embodiment, the test box 40 outputs the communication signal and the bus signal, and correspondingly, the instrument unit 10 of the integrated avionics system ground test device has a corresponding display. For example: the switch of the test box 40 outputs a stall alarm signal, and correspondingly, the instrument unit 10 will display a "STALL" alarm.

[0048] In this embodiment, the test box 40 further includes an earphone and a microphone for receiving and outputting voice signals.

[0049] In this embodiment, the instrument unit 10 is used to display relevant images when the aircraft is flying and scale values ​​corresponding to signals output by other systems of the aircraft. The instrument unit 10 includes a dashboard bracket, which is used to set instrument equipment on the aircraft dashboard. The size of the dashboard bracket is consistent with the size of the aircraft dashboard, so as to maintain consistency with the aircraft.

[0050] In this embodiment, the instrument panel bracket is customized according to the actual situation of the aircraft.

[0051] In this embodiment, the instrument equipment includes a display, a controller and a warning device.

[0052] In this embodiment, the control unit 20 includes a control panel bracket, which is used to set the operating equipment on the aircraft control panel. The size of the control panel bracket is consistent with the size of the aircraft control panel, so as to maintain consistency with the aircraft.

[0053] In this embodiment, the control console bracket is customized according to the actual situation of the aircraft.

[0054] In this embodiment, the operating device includes a control panel and an automatic driving mode controller.

[0055] In this embodiment, the rear row unit 30 includes a rear row bracket, which is used to install the second row of equipment on the aircraft and other avionics equipment on the rear fuselage of the aircraft.

[0056] In this embodiment, the integrated avionics system ground test device also includes a test bench, which is used to place the instrument equipment, the control equipment, the second row of equipment, the other avionics equipment, the test box 40 and the bus data simulator 50. The test bench is made of metal or wood to reduce the manufacturing cost of the test bench.

[0057] This embodiment also provides a method for using the integrated avionics system ground test device, including:

[0058] Step S10, connecting the instrument unit 10, the control unit 20, the rear unit 30, the test box 40, and the bus data simulator 50, wherein the test box 40 is connected to the bus data simulator 50, and the bus data simulator 50 is connected to the instrument unit 10, the control unit 20, and the rear unit 30; the instrument unit 10 is an instrument device installed on the instrument panel of the aircraft, the control unit 20 is a control device installed on the control console of the aircraft, and the rear unit 30 is the second row device installed on the aircraft and other avionics equipment on the rear fuselage of the aircraft;

[0059] The test box 40 and the bus data simulator 50 simulate and output corresponding communication signals and bus signals generated by other systems of the aircraft to the instrument unit 10 , the control unit 20 , and the rear unit 30 .

[0060] In this embodiment, the other aircraft systems are one or more of a hydraulic system, an electrical system, an engine system, and a fuel system.

[0061] In this embodiment, a power supply unit is also included. The power supply unit is connected to the instrument equipment, the control equipment, the second row equipment and other avionics equipment to supply power to the entire test device.

[0062] In this embodiment, an antenna unit is also included. The antenna unit is an antenna installed on the aircraft. The antenna on the aircraft is used to detect signals sent by a handheld radio or a navigation simulator.

[0063] In this embodiment, the antenna unit also includes an antenna bracket, and the antenna on the aircraft includes an antenna on the back of the aircraft and an antenna on the belly of the aircraft. The antenna on the back of the aircraft is installed above the antenna bracket, and the antenna on the belly of the aircraft is installed below the antenna bracket.

[0064] In this embodiment, the antenna is a real antenna on the aircraft, which is used to receive signals from a handheld radio and a navigation simulator, wherein the handheld radio transmits communication radio wave signals, and the navigation simulator simulates the radio wave signals of a transponder, a rangefinder, and a VOLT / instrument landing system, and the communication function and navigation function of the integrated avionics system are tested through the antenna.

[0065] Step S20, using the power supply unit to power on the integrated avionics system, wherein the power supply unit includes a power converter, and the power converter is directly connected to the mains.

[0066] In this embodiment, the power converter converts the mains power into a 28V voltage to power the test equipment.

[0067] Step S30, the test box 40 and the bus data simulator 50 output communication signals or bus signals to the instrument unit 10, the control unit 20, the rear unit 30, or a part of or all of them, to verify the correctness of the reception, processing, display and alarm of the avionics system;

[0068] The test box 40 is used to simulate the communication signals generated by other systems of the aircraft and is used as a signal generator to drive the integrated avionics system to perform signal acquisition, signal display and alarm;

[0069] The bus data simulator 50 is used to simulate bus signals generated by other systems of the aircraft, thereby driving the integrated avionics system to perform signal reception, signal processing, signal display and alarm;

[0070] The communication signal is one or more of a discrete signal, an analog signal, a switch signal and a frequency signal;

[0071] The bus signal is one or more of an ARINC429 bus signal, an RS422 bus signal, an RS232 bus signal, and a CAN bus signal.

[0072] In this embodiment, the discrete signal is simulated using a button, and the analog signal is simulated using a knob-type sliding resistor; the frequency signal is simulated using a frequency signal generator, and the frequency range and duty cycle of the frequency signal are adjustable.

[0073] In other embodiments, the discrete signal is simulated using a toggle switch.

[0074] In this embodiment, the bus signal simulator uses host computer software to facilitate real-time operation.

[0075] In this embodiment, the discrete signal includes a pitot tube heating signal; the switch signal includes a stall warning signal; the analog signal includes a battery current signal; and the frequency signal includes a fuel level sensor signal.

[0076] In this embodiment, the ARINC429 bus signal includes a data recorder; the RS422 bus signal includes a main control board; the RS232 bus signal includes a communication navigation component; and the CAN bus signal includes an engine.

[0077] Finally, it should be noted that any modification or equivalent replacement of part or all of the technical features based on the device structure of the utility model and the technical solution of the described embodiment, which does not deviate from the essence of the corresponding technical solution of the utility model, belongs to the patent scope of the device structure of the utility model and the described implementation scheme.

Claims

1. A ground test device for an integrated avionics system, characterized in that: include: Instrument unit, control unit, rear unit, test box, bus data simulator; The instrument unit is an instrument device installed on the aircraft dashboard, the control unit is a control device installed on the aircraft control panel, and the rear row unit is the second row of equipment installed on the aircraft and other avionics equipment on the rear fuselage of the aircraft; The test box is connected to the bus data simulator, and the bus data simulator is connected to the instrument unit, the control unit, and the rear row unit. The test box and the bus data simulator simulate the output of corresponding communication signals and bus signals generated by other systems of the aircraft to the instrument unit, the control unit, and the rear row unit.

2. The integrated avionics system ground test device according to claim 1, characterized in that: It also includes a power supply unit, which is connected to the instrument equipment, the operating equipment, the second row of equipment, and the other avionics equipment to supply power to the entire test device.

3. The integrated avionics system ground test device according to claim 2, characterized in that: The power supply unit comprises a power converter, and the power converter is directly connected to the mains.

4. The integrated avionics system ground test device according to claim 1, characterized in that: It also includes an antenna unit, which is an antenna installed on the aircraft. The antenna on the aircraft is used to receive signals sent by a handheld radio station and a navigation simulator.

5. The integrated avionics system ground test device according to claim 4, characterized in that: The antenna unit also includes an antenna bracket, and the antenna on the aircraft includes an antenna on the back of the aircraft and an antenna on the belly of the aircraft. The antenna on the back of the aircraft is installed above the antenna bracket, and the antenna on the belly of the aircraft is installed below the antenna bracket.

6. The integrated avionics system ground test device according to claim 1, characterized in that: The test box also includes earphones and a microphone for receiving and outputting voice signals.

7. The integrated avionics system ground test device according to claim 1, characterized in that: The instrument unit comprises an instrument panel bracket, and the instrument panel bracket is used to set instrument equipment on an aircraft instrument panel, and the size of the instrument panel bracket is consistent with the size of the aircraft instrument panel.

8. The integrated avionics system ground test device according to claim 1, characterized in that: The control unit comprises a control panel bracket, and the control panel bracket is used to set the operating equipment on the aircraft control panel, and the size of the control panel bracket is consistent with the size of the aircraft control panel.

9. The integrated avionics system ground test device according to claim 1, characterized in that: The rear row unit includes a rear row bracket, which is used to install the second row of equipment on the aircraft and other avionics equipment on the rear fuselage of the aircraft.

10. The integrated avionics system ground test device according to claim 1, characterized in that: It also includes a test bench, which is used to set the instrument equipment, the control equipment, the second row equipment, the other avionics equipment, the test box and the bus data simulator.

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