CN222189394U - A ground test device for integrated avionics system - Google Patents
A ground test device for integrated avionics system Download PDFInfo
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- CN222189394U CN222189394U CN202323424915.9U CN202323424915U CN222189394U CN 222189394 U CN222189394 U CN 222189394U CN 202323424915 U CN202323424915 U CN 202323424915U CN 222189394 U CN222189394 U CN 222189394U
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Abstract
The utility model relates to the field of avionics testing, and provides a ground testing device for a comprehensive avionics system. The test box is connected with a bus data simulator, the bus data simulator is connected with an instrument unit, an operating unit and a rear row unit, and the test box and the bus data simulator simulate and output corresponding other systems of the aircraft to the instrument unit, the operating unit and the rear row unit to generate communication signals and bus signals. The utility model uses the test box and the bus data simulator to simulate signals of other systems of the aircraft, does not need to integrate other real equipment of the aircraft, overcomes the inconsistent development progress of other systems of the aircraft in the development process of the aircraft, influences the development progress of the comprehensive avionics system, timely and rapidly tests and verifies the comprehensive avionics system, shortens the development period of new development or modification of the comprehensive avionics system, and reduces the overall development cost of the aircraft.
Description
Technical Field
The utility model relates to the field of avionics testing, in particular to a ground testing device for a comprehensive avionics system.
Background
Modern aircraft integrated avionics systems are closely cross-linked with other aircraft systems, which are required to be displayed, controlled, alerted, recorded, etc. by the integrated avionics systems. During development of an aircraft, integrated avionics systems often need to be newly developed or retrofitted to meet cross-linking with other aircraft systems.
The integrated avionics system, whether new or retrofit, has a lead time and cost. And before installation, joint debugging and joint testing are required to be carried out on the newly-researched or modified comprehensive avionics system and other aircraft systems, so that the comprehensive avionics system is ensured to meet corresponding requirements.
However, the development progress of other systems of the aircraft is not consistent, and the other systems of the aircraft need to be subjected to crosslinking test with the new or modified integrated avionics system, but due to the inconsistent development progress of the other systems of the aircraft, the new or modified integrated avionics system can not complete all the tests, and all the functions and performances of the other systems of the aircraft can not be verified, so that the development period of the integrated avionics system, even the aircraft, is increased, and the development cost is increased.
Disclosure of utility model
The utility model provides a ground testing device for an integrated avionics system, which solves the problems and comprises:
the device comprises an instrument unit, an operation unit, a back row unit, a test box and a bus data simulator;
The instrument unit is instrument equipment arranged on an instrument panel of the aircraft, the operation unit is operation equipment arranged on an operation table of the aircraft, and the rear row unit is second row equipment arranged on the aircraft and other avionics equipment of a rear fuselage of the aircraft;
the test box is connected with the bus data simulator, the bus data simulator is connected with the instrument unit, the control unit and the back row unit, and the test box and the bus data simulator simulate and output corresponding other aircraft systems to the instrument unit, the control unit and the back row unit to generate communication signals and bus signals.
Optionally, the test device further comprises a power supply unit, wherein the power supply unit is connected with the instrument equipment, the control equipment, the second row of equipment and the other avionics equipment and is used for supplying power to the whole test device.
Optionally, the power supply unit includes a power converter, and the power converter is directly connected to the mains.
Optionally, the device further comprises an antenna unit, wherein the antenna unit is an antenna installed on an aircraft, and the antenna on the aircraft is used for receiving signals sent by the handheld radio station and the navigation simulator.
Optionally, the antenna unit further includes an antenna bracket, the antenna on the aircraft includes an antenna on the aircraft back and an antenna on the aircraft belly, the antenna on the aircraft back is installed above the antenna bracket, and the antenna on the aircraft belly is installed below the antenna bracket.
Optionally, the test box further comprises an earphone and a microphone for receiving and outputting voice signals.
Optionally, the instrument unit includes an instrument panel bracket for providing instrument equipment on an aircraft instrument panel, the instrument panel bracket having a size consistent with a size of the aircraft instrument panel.
Optionally, the manipulation unit includes a manipulation stage support for setting a manipulation device on the aircraft manipulation stage, the manipulation stage support having a size consistent with a size of the aircraft manipulation stage.
Optionally, the rear row unit includes a rear row bracket, and the rear row bracket is used for installing equipment of a second row on the aircraft and other avionics equipment of a rear fuselage of the aircraft.
Optionally, the test board is used for setting the instrument equipment, the control equipment, the second row of equipment, the other avionics equipment, the test box and the bus data simulator, and the test board is made of metal materials or wood materials.
In summary, the utility model has the advantages that:
The utility model provides a ground testing device for a comprehensive avionics system. The device comprises an instrument unit, an operation unit, a back row unit, a test box and a bus data simulator, wherein the instrument unit is instrument equipment arranged on an instrument panel of an aircraft, the operation unit is operation equipment arranged on an operation console of the aircraft, the back row unit is equipment arranged on a second row on the aircraft and other avionics equipment of a back fuselage of the aircraft, the test box is connected with the bus data simulator, the bus data simulator is connected with the instrument unit, the operation unit and the back row unit, and the test box and the bus data simulator simulate and output corresponding other systems of the aircraft to the instrument unit, the operation unit and the back row unit to generate communication signals and bus signals.
In the prior art, real equipment or a system is generally adopted to be connected with the comprehensive avionics system, and then the comprehensive avionics system is tested, and the test box and the bus data simulator are adopted to simulate signals of other systems of the aircraft, so that other real equipment of the aircraft is not required to be integrated, the influence on the development progress of the comprehensive avionics system due to inconsistent development progress of other systems of the aircraft in the development process of the aircraft is overcome, the test and verification of the comprehensive avionics system can be timely and rapidly carried out, and meanwhile, each unit of the comprehensive avionics system can be independently tested, so that the development period of new development or modification of the comprehensive avionics system is shortened, and the overall development cost of the aircraft is reduced.
Drawings
FIG. 1 is a schematic diagram of a ground testing device for an integrated avionics system according to an embodiment of the present utility model.
Detailed Description
The present utility model will be described in further detail with reference to specific examples for the purpose of facilitating understanding to those skilled in the art.
The utility model provides a ground testing device of a comprehensive avionics system, as shown in figure 1, comprising:
The meter unit 10, the manipulation unit 20, the back row unit 30, the test box 40, the bus data simulator 50;
The instrument unit 10 is an instrument device mounted on an instrument panel of an aircraft, the operation unit 20 is an operation device mounted on an operation console of the aircraft, and the rear row unit 30 is a device mounted on a second row of the aircraft and other avionics devices of a rear fuselage of the aircraft;
the test box 40 is connected with the bus data simulator 50, the bus data simulator 50 is connected with the instrument unit 10, the control unit 20 and the rear unit 30, and the test box 40 and the bus data simulator 50 simulate and output corresponding other systems of the airplane to the instrument unit 10, the control unit 20 and the rear unit 30 to generate communication signals and bus signals.
Specifically, in this embodiment, the other systems of the aircraft are one or more of a hydraulic system, an electrical system, an engine system, and a fuel system.
In this embodiment, the test device further comprises a power supply unit, and the power supply unit is connected with the instrument device, the control device, the second row of devices and other avionics devices and is used for supplying power to the whole test device.
In this embodiment, the power supply unit includes a power converter, and the power converter is directly connected to the mains.
The power converter is selected according to the voltage and power of the whole integrated avionics system.
In this embodiment, the power converter is selected according to the maximum power when all the installation test devices are in operation, and the power converter is convenient to directly connect with the mains supply.
In this embodiment, the power converter converts the mains supply to a 28V voltage to power the test device.
In this embodiment, the device further includes an antenna unit, where the antenna unit is an antenna installed on an aircraft, and the antenna on the aircraft is configured to receive signals sent by the handheld radio station and the navigation simulator.
In this embodiment, the antenna unit further includes an antenna bracket, and the antenna on the aircraft includes an antenna on a back of the aircraft and an antenna on a belly of the aircraft, where the antenna on the back of the aircraft is mounted above the antenna bracket, and the antenna on the belly of the aircraft is mounted below the antenna bracket.
In this embodiment, the antenna support is made of a metal material, so that the antenna is grounded.
The antenna is a real antenna on the aircraft and is used for receiving signals from a handheld radio station and a navigation simulator, wherein the handheld radio station transmits communication radio wave signals, the navigation simulator simulates radio wave signals of a transponder, a range finder and a Vol/instrument landing system, and the antenna is used for testing communication functions and navigation functions of the comprehensive avionics system.
In this embodiment, the test box 40 is a signal generator, and is configured to simulate 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;
The bus data simulator 50 is used for simulating bus signals generated by other systems of the aircraft, so as to drive the comprehensive avionics system to perform signal receiving, signal processing, signal displaying and alarming.
In this embodiment, the communication signal is one or more of a discrete signal, an analog signal, a switching signal, and a frequency signal.
In the embodiment, the discrete signals are simulated by using buttons, the simulated signals are simulated by using knob type slide varistors, the frequency signals are simulated by using a frequency signal generator, and the frequency range and the duty ratio of the frequency signals are adjustable.
In other embodiments, the discrete signal is simulated using a toggle switch.
The control parts of the button, the knob type slide rheostat and the toggle switch are arranged on the control panel of the test box.
In this embodiment, the bus signal is one or more of ARINC429 bus signal, RS422 bus signal, RS232 bus signal, and CAN bus signal.
In this embodiment, the bus signal simulator uses host computer software, so that real-time operation is facilitated.
In this embodiment, the discrete signal includes a pitot tube heating signal, the switch signal includes a stall warning signal, a fire warning signal, and other specific signals of the aircraft, the analog signal includes a battery current signal, and the frequency signal includes a fuel sensor signal.
In this embodiment, the ARINC429 bus signal comprises a data recorder, the RS422 bus signal comprises a main control board, the RS232 bus signal comprises a communication navigation component, and the CAN bus signal comprises an engine.
In this embodiment, the test box 40 outputs the communication signal and the bus signal, and correspondingly, the meter unit 10 of the ground test device of the integrated avionics system has a corresponding display, for example, the switch of the test box 40 outputs a STALL warning signal, and correspondingly, the meter unit 10 displays a "STALL" warning.
In this embodiment, the test cartridge 40 further includes an earphone and a microphone for receiving and outputting voice signals.
In this embodiment, the instrument unit 10 is configured to display a related screen of the aircraft during flight and a scale value corresponding to a signal output by other systems of the aircraft, where the instrument unit 10 includes an instrument panel bracket, where the instrument panel bracket is configured to set instrument equipment on an instrument panel of the aircraft, and a size of the instrument panel bracket is consistent with a size of the instrument panel of the aircraft, so as to maintain consistency with the aircraft.
In this embodiment, the instrument panel support is customized according to the actual situation of the aircraft.
In this embodiment, the meter device includes a display, a controller, and a warning device.
In the present embodiment, the console unit 20 includes a console bracket for setting an operation device on the aircraft console, the console bracket having a size consistent with that of the aircraft console for maintaining consistency with the aircraft.
In this embodiment, the console support is customized according to the actual situation of the aircraft.
In this embodiment, the operation device includes a control panel, an automatic driving mode controller.
In this embodiment, the rear row unit 30 includes a rear row of brackets for mounting a second row of equipment on the aircraft and other avionics equipment on the rear fuselage of the aircraft.
In this embodiment, the ground test device for a comprehensive avionics system further includes a test board, where the test board is used for placing the instrument device, the handling device, the second row of devices, the other avionics devices, the test box 40, and the bus data simulator 50, and the test board is made of a metal material or a wood material, so that the manufacturing cost of the test board is reduced.
The embodiment also provides a use method of the ground test device of the integrated avionics system, which comprises the following steps:
Step S10, connecting an instrument unit 10, an operation unit 20, a back row unit 30, a test box 40 and a bus data simulator 50, wherein the test box 40 is connected with the bus data simulator 50, and the bus data simulator 50 is connected with the instrument unit 10, the operation unit 20 and the back row unit 30, wherein the instrument unit 10 is instrument equipment installed on an instrument panel of an airplane, the operation unit 20 is operation equipment installed on an operation console of the airplane, and the back row unit 30 is second row equipment installed on the airplane and other avionics equipment of a back fuselage of the airplane;
The test box 40 and the bus data simulator 50 generate communication signals and bus signals to the instrument unit 10, the control unit 20, and the rear unit 30, respectively, and simulate other systems of the aircraft.
In this embodiment, the other systems of the aircraft are one or more of a hydraulic system, an electrical system, an engine system, and a fuel system.
In this embodiment, the test device further comprises a power supply unit, and the power supply unit is connected with the instrument device, the control device, the second row of devices and other avionics devices and is used for supplying power to the whole test device.
In this embodiment, the device further includes an antenna unit, where the antenna unit is an antenna installed on an aircraft, and the antenna on the aircraft is used to detect signals sent by the handheld radio station and the navigation simulator.
In this embodiment, the antenna unit further includes an antenna bracket, and the antenna on the aircraft includes an antenna on a back of the aircraft and an antenna on a belly of the aircraft, where the antenna on the back of the aircraft is mounted above the antenna bracket, and the antenna on the belly of the aircraft is mounted below the antenna bracket.
In this embodiment, the antenna is a real antenna on an aircraft, and is configured to receive signals from a handheld radio station and a navigation simulator, where the handheld radio station transmits communication radio wave signals, and the navigation simulator simulates radio wave signals of a transponder, a range finder, and a vool/meter landing system, and the antenna is used to test the communication function and the navigation function of the integrated avionics system.
And step S20, powering up the comprehensive avionics system by utilizing the power supply unit, wherein the power supply unit comprises a power supply converter, and the power supply converter is directly connected with the mains supply.
In this embodiment, the power converter converts the mains supply to a 28V voltage to power the test device.
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, and the rear unit 30, or to a part of or all of them, respectively, to verify the correctness of the receiving, processing, displaying and alarming of the avionics system;
The test box 40 is used for simulating communication signals generated by other systems of the aircraft and is used as a signal generator, so that the comprehensive avionics system is driven to acquire, display and alarm signals;
The bus data simulator 50 is used for simulating bus signals generated by other systems of the aircraft so as to drive the comprehensive avionics system to perform signal receiving, signal processing, signal displaying and alarming;
The communication signal is one or more of discrete signal, analog signal, switch signal and frequency signal;
the bus signal is one or more of ARINC429 bus signal, RS422 bus signal, RS232 bus signal and CAN bus signal.
In the embodiment, the discrete signals are simulated by using buttons, the simulated signals are simulated by using knob type slide varistors, the frequency signals are simulated by using a frequency signal generator, and the frequency range and the duty ratio of the frequency signals are adjustable.
In other embodiments, the discrete signal is simulated using a toggle switch.
In this embodiment, the bus signal simulator uses host computer software, so that real-time operation is facilitated.
In this embodiment, the discrete signal comprises a pitot tube warming signal, the switching signal comprises a stall warning signal, the analog signal comprises a battery current signal, and the frequency signal comprises a fuel quantity sensor signal.
In this embodiment, the ARINC429 bus signal comprises a data recorder, the RS422 bus signal comprises a main control board, the RS232 bus signal comprises a communication navigation component, and the CAN bus signal comprises an engine.
Finally, any modification or equivalent replacement of some or all of the technical features by means of the structure of the device according to the utility model and the technical solutions of the examples described, the resulting nature of which does not deviate from the corresponding technical solutions of the utility model, falls within the scope of the structure of the device according to the utility model and the patent claims of the embodiments described.
Claims (10)
1. The utility model provides a synthesize avionics system ground testing arrangement which characterized in that includes:
the device comprises an instrument unit, an operation unit, a back row unit, a test box and a bus data simulator;
The instrument unit is instrument equipment arranged on an instrument panel of the aircraft, the operation unit is operation equipment arranged on an operation table of the aircraft, and the rear row unit is second row equipment arranged on the aircraft and other avionics equipment of a rear fuselage of the aircraft;
the test box is connected with the bus data simulator, the bus data simulator is connected with the instrument unit, the control unit and the back row unit, and the test box and the bus data simulator simulate and output corresponding other aircraft systems to the instrument unit, the control unit and the back row unit to generate communication signals and bus signals.
2. A comprehensive avionics system ground testing apparatus in accordance with claim 1, further comprising a power unit coupled to said instrumentation, said handling, said second row of equipment, and said other avionics devices for powering the entire testing apparatus.
3. The integrated avionics system ground testing apparatus of claim 2, wherein the power unit comprises a power converter that is directly connected to mains.
4. The integrated avionics system ground testing device of claim 1, further comprising an antenna unit, the antenna unit being an antenna mounted on an aircraft, the antenna on the aircraft configured to receive signals from a handheld radio station and a navigation simulator.
5. The integrated avionics system ground testing device of claim 4, wherein the antenna unit further comprises an antenna mount, the on-board antenna comprising an on-board antenna and an on-board antenna, the on-board antenna being mounted above the antenna mount, the on-board antenna being mounted below the antenna mount.
6. The integrated avionics system ground testing device of claim 1, wherein the test cartridge further comprises an earphone and a microphone for receiving and outputting voice signals.
7. The integrated avionics system ground testing apparatus of claim 1, wherein the instrument unit comprises an instrument panel support for providing instrument equipment on an aircraft instrument panel, the instrument panel support sized to conform to the size of the aircraft instrument panel.
8. A ground testing device for integrated avionics systems in accordance with claim 1, wherein said steering unit comprises a console support for positioning operating equipment on an aircraft console, said console support being sized to conform to the size of the aircraft console.
9. A ground testing device for integrated avionics systems in accordance with claim 1 wherein said back row unit includes a back row bracket for mounting a second row of equipment on an aircraft and other avionics equipment on the back fuselage of the aircraft.
10. The integrated avionics system ground testing apparatus of claim 1 further comprising a test station for setting the instrumentation, the handling equipment, the second tier equipment, the other avionics equipment, a test box, and a bus data simulator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323424915.9U CN222189394U (en) | 2023-12-14 | 2023-12-14 | A ground test device for integrated avionics system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323424915.9U CN222189394U (en) | 2023-12-14 | 2023-12-14 | A ground test device for integrated avionics system |
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| Publication Number | Publication Date |
|---|---|
| CN222189394U true CN222189394U (en) | 2024-12-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323424915.9U Active CN222189394U (en) | 2023-12-14 | 2023-12-14 | A ground test device for integrated avionics system |
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| CN (1) | CN222189394U (en) |
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2023
- 2023-12-14 CN CN202323424915.9U patent/CN222189394U/en active Active
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