CN214504211U - Flying parameter recorder test system - Google Patents
Flying parameter recorder test system Download PDFInfo
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- CN214504211U CN214504211U CN202120021057.5U CN202120021057U CN214504211U CN 214504211 U CN214504211 U CN 214504211U CN 202120021057 U CN202120021057 U CN 202120021057U CN 214504211 U CN214504211 U CN 214504211U
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Abstract
The utility model relates to a test technical field discloses a flying parameter record appearance test system, and test system includes: a system control module; the power supply module is connected with the system control module and used for receiving the instruction of the system control module and realizing the configuration of the power supply signal of the test system of the flight parameter recorder through the instruction; the signal generation module is connected with the system control module and comprises a program control signal generator; and the test channel switching control module is respectively connected with the signal generation module and the power supply module in a one-way mode and is connected with the system control module in a two-way mode. The utility model discloses following beneficial effect has at least: the output of various airborne electrical signals, bus data signals and the like can be provided for the flying parameter recorder, and the test efficiency of the flying parameter recording tester is improved.
Description
Technical Field
The utility model relates to a test technical field, in particular to flying parameter record appearance test system.
Background
The flight parameter recorder is a key component of an airplane flight parameter recording system as front-end acquisition equipment of an airplane recorder (black box), and needs to acquire various airborne electrical signals and bus data signals, convert the acquired electrical signals and bus data signals into data information and send the data information to the recorder through an RS422 bus for data recording.
In recent years, the performance and the function of the flying parameter recorder are improved, and the traditional product testing technology and means cannot meet the testing and inspection requirements of the new generation of flying parameter recorder.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, the utility model provides a flying parameter record appearance test system can provide various machine carried electrical signal, bus data signal for flying parameter record appearance.
According to the utility model discloses a flying parameter record appearance test system, include: the system control module is used for realizing the test control of the flight parameter recorder; the power supply module is connected with the system control module and used for receiving an instruction of the system control module and realizing the configuration of a power supply signal of the flight parameter recorder test system through the instruction; the signal generation module is connected with the system control module and comprises a program-controlled signal generator and is used for receiving an instruction of the system control module and providing a test excitation signal for the flight parameter recorder, and the test excitation signal comprises a sine signal, a square wave signal, a direct current signal and a low-voltage alternating current and direct current signal; and the test channel switching control module is respectively connected with the signal generation module and the power supply module in a one-way mode and is connected with the system control module in a two-way mode, and is used for realizing switching control between each test channel and each signal acquisition channel in the flight parameter recorder test system.
According to some embodiments of the utility model, power module includes programme-controlled DC power supply and programme-controlled interchange intermediate frequency power supply, wherein, programme-controlled DC power supply with system control module one-way connection is used for receiving system control module's instruction, for test channel switches control module and provides the power to configure into output controllable switching signal and DC signal, programme-controlled interchange intermediate frequency power supply with system control module one-way connection is based on high frequency power electronic switch transform technique for output three-phase 36V, single-phase 36V, 115V and 220V ac signal.
According to some embodiments of the utility model, test channel switches control module includes signal conditioning unit, switch matrix unit and test interface unit, the switch matrix unit with signal conditioning unit one-way connection, the switch matrix unit with test interface unit both way junction.
According to some embodiments of the utility model, the signal conditioning unit respectively with system control module programme-controlled signal generator reaches switch matrix unit connects, receives the instruction that system control module sent will flight parameter signal conditioning that programme-controlled signal generator sent or convert negative pressure signal and/or direct current differential signal output into extremely switch matrix unit.
According to the utility model discloses a some embodiments, the signal conditioning unit includes single-ended to differential circuit, single-ended to differential circuit includes that first fortune is put, second fortune is put and isolation transformer, first fortune is put and second fortune is put respectively with isolation transformer connects for convert the single-ended signal of input into differential signal and realize differential signal's output through isolation transformer.
According to some embodiments of the utility model, the switch matrix unit respectively with system control module the unit is taked care of to the signal programme-controlled DC power supply programme-controlled interchange intermediate frequency power supply reaches the test interface unit connects, include: the device comprises a matching resistance network, a test channel switching component, an instruction analysis control component and an RS232 interface driving component; the test channel switching assembly is respectively in bidirectional connection with the matching resistor network and in unidirectional connection with the instruction analysis control assembly, and the instruction analysis control assembly is in bidirectional connection with the RS232 interface drive.
According to some embodiments of the utility model, the test channel switching subassembly includes a plurality of switches that are used for the passageway to switch, the switch is contact mechanical magnetism latching relay.
According to some embodiments of the invention, the test interface unit comprises: the RS232 communication component is used for providing an RS232 communication interface; the RS422 communication component is used for providing an RS422 communication interface; the PCI interface multimeter component is used for extracting the amplitude parameter of the direct current signal or the alternating current signal; the ARINC429 bus communication component is used for providing an ARINC429 communication interface; and the 1553B communication component is used for providing a 1553B communication interface and simulating three working modes of BC, RT and BM to realize data receiving and transmitting.
According to some embodiments of the present invention, the system control module realizes test control of the flight parameter recorder based on the industrial personal computer, and includes a PCI interface unit, a USB interface unit, an RS422 interface unit, an RS232 interface unit, a VGA interface unit, and an HDMI interface unit; the system control module also integrates an operating system and user interface operating software.
According to some embodiments of the utility model, system control module with test channel switches control module and passes through RS422 and connect, passes through USB with mouse keyboard and is connected, passes through VGA interface connection with the display, passes through RS232 with programme-controlled interchange intermediate frequency power supply and is connected, with programme-controlled signal generator passes through RS232 and connects, passes through RS232 with programme-controlled DC power supply and is connected.
According to the utility model discloses parameter recorder test system flies has following beneficial effect at least: the device can provide outputs of various airborne electrical signals, bus data signals and the like for the flight parameter recorder, and read recorded data formed by the flight parameter recorder aiming at the various airborne electrical signals and the bus data signals in real time.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 is one of the block schematic block diagrams of the system of an embodiment of the present invention;
fig. 2 is a second block diagram of the system according to an embodiment of the present invention;
fig. 3 is a schematic block diagram of a single-ended to differential circuit module according to an embodiment of the present invention;
fig. 4 is a schematic block diagram of a switch matrix module according to an embodiment of the present invention;
fig. 5 is a third block diagram of the system according to the embodiment of the present invention.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present invention, and should not be construed as limiting the present invention.
In the description of the present invention, a plurality of means are one or more, a plurality of means are two or more, and the terms greater than, less than, exceeding, etc. are understood as not including the present number, and the terms greater than, less than, within, etc. are understood as including the present number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.
Referring to fig. 1, fig. 1 is one of block schematic diagrams of a system according to an embodiment of the present invention, including: the system control module is used for realizing the test control of the flight parameter recorder;
the power supply module is connected with the system control module and used for receiving the instruction of the system control module and realizing the configuration of the power supply signal of the test system of the flight parameter recorder through the instruction;
the signal generation module is connected with the system control module and comprises a program-controlled signal generator and a control module, wherein the program-controlled signal generator is used for receiving an instruction of the system control module and providing a test excitation signal for the flight parameter recorder, and the test excitation signal comprises a sine signal, a square wave signal, a direct current signal and a low-voltage alternating current and direct current signal;
and the test channel switching control module is respectively connected with the signal generation module and the power supply module in a one-way mode and is connected with the system control module in a two-way mode and used for realizing switching control between each test channel and each signal acquisition channel in the test system of the flight parameter recorder.
It should be noted that, a test excitation signal is provided for the flight parameter recorder through the signal generation module, the power supply module configures a power supply signal for the flight parameter recorder, the test channel switching control module realizes switching control between each test channel and the signal acquisition channel, and can realize output of various airborne electrical signals, bus data signals and the like provided for the flight parameter recorder, read recorded data formed by the flight parameter recorder aiming at the various airborne electrical signals and the bus data signals in real time, and judge whether the function and performance of the recorder reach the standard.
The test system of the flight parameter recorder is a special test instrument for carrying out intelligent detection, fault location and performance evaluation on the flight parameter recorder, can provide outputs of various airborne electrical signals, bus data signals and the like for the flight parameter recorder, reads recorded data formed by the flight parameter recorder aiming at the various airborne electrical signals and the bus data signals in real time, judges whether the function and the performance of the recorder reach the standard or not, and can realize board-level fault location of the flight parameter recorder. The flight parameter recorder testing system is used as full-automatic testing equipment, can provide a friendly man-machine interaction interface, and realizes full-automatic testing of functions and performances of each channel of the recorder by a method of controlling channel signal output, data recovery and input-output comparison through software. The flight parameter recorder testing system can automatically configure airplane models of the recorder, automatically select the recorded airplane models and parameter quantity, and also can detect the model signals output by the recorder and identify the host machine models; the FLASH data in the recorder can be read, written and downloaded, and the storage function of the FLASH can be detected.
The flight parameter recorder testing system adopts a structure of an FPGA testing channel switching module, an industrial control host and various external signal sources, and expands a multi-channel simulated flight parameter control interface, a channel switching interface, a sampling test command interface and a sampling data storage interface by utilizing the FPGA. The industrial control host is used as a system control center, an upper computer program is operated, various control commands are generated, simulated flight parameters are displayed in real time, an external instrument is controlled through a serial port to generate required flight parameters, FPGA communication is achieved to obtain all data, a test report and a fault analysis report are formed, and the unmanned test intelligent function of the maximum program is achieved.
Fig. 2 is the second schematic block diagram of the module of the system of the embodiment of the present invention, in the figure, the power module includes program-controlled dc power supply and program-controlled ac intermediate frequency power supply, program-controlled dc power supply is connected with system control module in one way, an instruction for receiving system control module provides the power supply for test channel switching control module and configures into output controllable switching signal and dc signal, program-controlled ac intermediate frequency power supply is connected with system control module in one way, based on high-frequency power electronic switch conversion technology, and is used for outputting three-phase 36V, single-phase 36V, 115V and 220V ac signal.
Specifically, the program-controlled signal generator can provide programmable low-voltage alternating current signals, can provide low-voltage alternating current signals such as sine signals, square signals, direct current signals and the like, provides low-voltage alternating current and direct current signals for the collector, and can provide three-phase 36V, single-phase 36V, 115V, 220V and other high-voltage alternating current signals for the program-controlled three-phase 400Hz medium-frequency power supply. The power supply needs to adopt a high-frequency power electronic switch conversion technology, is specially designed and manufactured for aerospace electronic and electrical equipment, is used for supplying power to electronic equipment such as airborne equipment, radars, navigation and the like, and is a replacement product of a unit type variable-frequency power supply in other occasions needing 400Hz medium-frequency power supplies.
Referring to fig. 2, the test channel switching control module includes a signal conditioning unit, a switch matrix unit and a test interface unit, the switch matrix unit is unidirectionally connected to the signal conditioning unit, and the switch matrix unit is bidirectionally connected to the test interface unit.
Specifically, the test channel switching control module can provide an external input/output interface for connecting with the 03C collector and controlling the on/off of the signal input/output of the collection channel; the test channel switching module mainly comprises a signal conditioning module for signal input conditioning, a switch matrix module, a test interface module and the like.
The utility model discloses among some embodiments, signal conditioning unit respectively with system control module, programme-controlled signal generator and switch matrix unit connection, receive the instruction that system control module sent, condition or convert the flight parameter signal that programme-controlled signal generator sent into negative pressure signal and/or direct current difference signal output to switch matrix unit.
The signal conditioning unit includes single-ended to differential circuit, and fig. 3 does the utility model discloses single-ended to differential circuit module schematic block diagram, in the figure, single-ended to differential circuit includes that first fortune is put, second fortune is put and isolation transformer, and first fortune is put and is put respectively with isolation transformer with second fortune and be connected for convert the single-ended signal of input into differential signal and realize differential signal's output through isolation transformer.
Specifically, the signal conditioning module is mainly used for conditioning flight parameter signals generated by an internal function module of the system, conditioning or converting negative pressure signals and direct current differential signals, including 0-100 mV direct current differential signals, and outputting the following signals after signal conditioning:
0-100 mV of direct current differential signal;
-5- +5V dc differential signals;
-32V single ended dc signal;
the single-end to differential circuit of the signal conditioning module adopts a double operational amplifier circuit to convert the single-end signal output by the signal source module into a differential signal, and the differential signal passes through an isolation transformer to realize differential signal output.
Referring to fig. 4, fig. 4 is the utility model discloses a schematic block diagram of switch matrix module, switch matrix unit are connected with system control module, signal conditioning unit, programme-controlled dc power supply, programme-controlled ac intermediate frequency power supply and test interface unit respectively, include: the device comprises a matching resistance network, a test channel switching component, an instruction analysis control component and an RS232 interface driving component; the test channel switching assembly is respectively connected with the matching resistor network in a bidirectional mode and the instruction analysis control assembly in a unidirectional mode, and the instruction analysis control assembly is connected with the RS232 interface in a driving bidirectional mode.
Specifically, the switch matrix module adopts the special switch matrix module of signal nondestructive transmission that utility model people's company developed, and this module has used the verification through long-term test, accords with the requirement of test index completely. The module is mainly designed by considering factors such as impedance matching, channel isolation, signal crosstalk, insulation and voltage resistance performance, four-wire method resistance measurement and the like of a channel switching link, and comprises 3 parts of each signal channel switching module, a matching resistance network module, an RS232 interface and an instruction analysis control module, so that the functions of switching among testing channels, conditioning and protecting acquired signals and the like are realized.
Among some embodiments of the present invention, the testing channel switching assembly includes a plurality of switches for switching channels, and the switches are contact type mechanical magnetic latching relays.
Specifically, the test channel switching component is a key design in a system and is responsible for matching flight parameter signals output by the system with signal driving, internal recovery switching and switching between 03C host signal interfaces, in order to ensure that interference or errors cannot be caused to excitation signal transmission and recovery in the process of switching various channels, a switch for switching selects a contact type mechanical magnetic latching relay, the magnetic latching relay can completely disconnect related power supplies and power supply ground signals after completing relay switching, the influences of external interference and the like of a switching path are eliminated, and the cleanliness of the tested signals is ensured.
The utility model discloses among some embodiments, the test interface unit includes RS232 communication component, RS422 communication component, PCI interface multimeter subassembly, ARINC429 bus communication component and 1553B communication component, RS232 communication component and RS422 communication component are used for providing RS232 and RS422 communication interface, PCI interface multimeter subassembly is used for the amplitude parameter of back-picking direct current signal or alternating current signal, ARINC429 bus communication component is used for providing ARINC429 communication interface, 1553B communication component is used for providing 1553B communication interface, can simulate BC, three kinds of mode of RT and BM, realize the receiving and dispatching of data.
The utility model discloses among some embodiments, system control module realizes the test control to flying parameter record appearance based on the industrial computer, including PCI interface unit, USB interface unit, RS422 RS232 interface unit and VGA HDMI interface unit, system control module has still integrated operating system and user interface operating software.
Specifically, the system control module is realized by adopting an industrial personal computer, wherein the PCI slots are used for integrating various PCI interface modules, integrating a USB interface, an RS422/RS232 interface and a VGA/HDMI interface, and are used for controlling other program control modules, connecting a liquid crystal display mouse keyboard and the like, and matching an operating system, it can be understood that the operating system can be an operating system of any version, including a WIN7 operating system, a WIN10 operating system, a deep operating system and the like, application interface software is installed, relevant control processes are realized through the interface software, and relevant function modules are controlled to realize the analog input and output of flight parameters.
Fig. 5 is the second block schematic diagram of the module of the system of the embodiment, flying parameter record appearance test system adopts standard industrial control rack as overall structure in the picture, at the inside integrated a plurality of functional modules of rack, including programme-controlled DC power supply, programme-controlled signal generator, programme-controlled three-phase 400Hz intermediate frequency power, system control center, realize based on the industrial computer, LCD and mouse keyboard, test channel switches control module, PCI interface RS422/232 communication module, PCI interface multimeter module, PCI interface ARINC429 bus communication module and PCI interface 1553B communication module, system control center adopts professional industrial computer to realize, supporting operating system, installation application interface software, the user realizes operating system through operation application interface software.
The utility model discloses among some embodiments, system control module passes through RS422 with test channel switching control module and is connected, passes through USB with mouse keyboard and is connected, passes through VGA interface connection with the display, passes through RS232 with programme-controlled interchange intermediate frequency power and is connected, passes through RS232 with programme-controlled signal generator and is connected, passes through RS232 with programme-controlled DC power and is connected.
In some embodiments of the present invention, after the full-automatic test function is started, 255 flying parameter data are automatically outputted to the collector according to the program setting, simultaneously, each path of the output simulated flight parameters is automatically sampled and stored, the test is executed, the system compares the received recorder data with the stored corresponding simulated flight parameters, so as to determine whether the acquisition state and the performance index of the recorder meet the requirements, analyze the fault reason according to the detection result and carry out board-level positioning on the fault, effectively solve the problem of insufficient guarantee capability of the first-line test of the airport, integrate various instruments with the flying parameter recorder testing system, under the control of a system computer, the type of the instrument and the voltage, frequency, polarity and other parameters of output signals of the instrument are changed through serial port communication, various flight parameters are simulated, and the simulated parameters are continuously output in a value range of the flight parameters.
Among some embodiments of the present invention, the present invention further comprises adjusting the parameter types and parameter values, executing the test, and realizing the individual output test or step test of the specific parameters.
Specifically, the flight parameter recorder testing system has a step testing function, a user can adjust the type and the numerical value of the output simulation flight parameter according to the testing requirement each time, the single output testing of some parameters is completed, and the full-automatic testing and the step testing can be performed.
Although specific embodiments have been described herein, those of ordinary skill in the art will recognize that many other modifications or alternative embodiments are equally within the scope of this disclosure. For example, any of the functions and/or processing capabilities described in connection with a particular device or component may be performed by any other device or component. In addition, while various illustrative implementations and architectures have been described in accordance with embodiments of the present disclosure, those of ordinary skill in the art will recognize that many other modifications of the illustrative implementations and architectures herein are also within the scope of the present disclosure.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.
Claims (10)
1. A flying parameter recorder testing system, comprising:
the system control module is used for realizing the test control of the flight parameter recorder;
the power supply module is connected with the system control module and used for receiving an instruction of the system control module and realizing the configuration of a power supply signal of the flight parameter recorder test system through the instruction;
the signal generation module is connected with the system control module and comprises a program-controlled signal generator and is used for receiving an instruction of the system control module and providing a test excitation signal for the flight parameter recorder, and the test excitation signal comprises a sine signal, a square wave signal, a direct current signal and a low-voltage alternating current and direct current signal;
and the test channel switching control module is respectively connected with the signal generation module and the power supply module in a one-way mode and is connected with the system control module in a two-way mode, and is used for realizing switching control between each test channel and each signal acquisition channel in the flight parameter recorder test system.
2. The flight parameter recorder test system according to claim 1, wherein the power module includes a programmable dc power supply and a programmable ac intermediate frequency power supply, wherein the programmable dc power supply is unidirectionally connected to the system control module, is configured to receive an instruction from the system control module, supplies power to the test channel switching control module, and is configured to output a controllable switching signal and a dc signal, and the programmable ac intermediate frequency power supply is unidirectionally connected to the system control module, and is configured to output three-phase 36V, single-phase 36V, 115V, and 220V ac signals based on a high-frequency power electronic switching conversion technique.
3. The flying parameter recorder test system according to claim 2, wherein the test channel switching control module comprises a signal conditioning unit, a switch matrix unit and a test interface unit, the switch matrix unit is unidirectionally connected with the signal conditioning unit, and the switch matrix unit is bidirectionally connected with the test interface unit.
4. The flying parameter recorder test system according to claim 3, wherein the signal conditioning unit is connected to the system control module, the program-controlled signal generator and the switch matrix unit, respectively, receives a command sent by the system control module, conditions or converts a flight parameter signal sent by the program-controlled signal generator into a negative pressure signal and/or a direct current differential signal, and outputs the negative pressure signal and/or the direct current differential signal to the switch matrix unit.
5. The flying parameter recorder test system according to claim 4, wherein the signal conditioning unit comprises a single-ended to differential circuit, the single-ended to differential circuit comprises a first operational amplifier, a second operational amplifier and an isolation transformer, and the first operational amplifier and the second operational amplifier are respectively connected to the isolation transformer for converting an input single-ended signal into a differential signal and outputting the differential signal through the isolation transformer.
6. The flying parameter recorder testing system according to claim 3,
the switch matrix unit is respectively connected with the system control module, the signal conditioning unit, the program-controlled direct-current power supply, the program-controlled alternating-current intermediate-frequency power supply and the test interface unit, and comprises: the device comprises a matching resistance network, a test channel switching component, an instruction analysis control component and an RS232 interface driving component;
the test channel switching assembly is respectively in bidirectional connection with the matching resistor network and in unidirectional connection with the instruction analysis control assembly, and the instruction analysis control assembly is in bidirectional connection with the RS232 interface drive.
7. The flying reference recorder testing system according to claim 6, wherein the test channel switching assembly comprises a plurality of switches for channel switching, the switches being contact mechanical magnetic latching relays.
8. The flying parameter recorder testing system according to claim 3, wherein the test interface unit comprises:
the RS232 communication component is used for providing an RS232 communication interface;
the RS422 communication component is used for providing an RS422 communication interface;
the PCI interface multimeter component is used for extracting the amplitude parameter of the direct current signal or the alternating current signal;
the ARINC429 bus communication component is used for providing an ARINC429 communication interface;
and the 1553B communication component is used for providing a 1553B communication interface and simulating three working modes of BC, RT and BM to realize data receiving and transmitting.
9. The flying parameter recorder test system according to claim 1, wherein the system control module realizes test control of the flying parameter recorder based on an industrial personal computer, and comprises a PCI interface unit, a USB interface unit, an RS422 interface unit, an RS232 interface unit, a VGA interface unit and an HDMI interface unit; the system control module also integrates an operating system and user interface operating software.
10. The flying parameter recorder test system according to claim 1, wherein the system control module is connected with the test channel switching control module through RS422, connected with a mouse keyboard through USB, connected with a display through VGA interface, connected with a program-controlled ac intermediate frequency power supply through RS232, connected with the program-controlled signal generator through RS232, and connected with a program-controlled dc power supply through RS 232.
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| CN202120021057.5U CN214504211U (en) | 2021-01-05 | 2021-01-05 | Flying parameter recorder test system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113086241A (en) * | 2021-03-23 | 2021-07-09 | 珠海欧比特宇航科技股份有限公司 | Airborne flight parameter simulation device and system |
| CN115328006A (en) * | 2022-10-13 | 2022-11-11 | 苏州华兴源创科技股份有限公司 | Signal control circuit |
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2021
- 2021-01-05 CN CN202120021057.5U patent/CN214504211U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113086241A (en) * | 2021-03-23 | 2021-07-09 | 珠海欧比特宇航科技股份有限公司 | Airborne flight parameter simulation device and system |
| CN113086241B (en) * | 2021-03-23 | 2023-03-10 | 珠海欧比特宇航科技股份有限公司 | Airborne flight parameter simulation device and system |
| CN115328006A (en) * | 2022-10-13 | 2022-11-11 | 苏州华兴源创科技股份有限公司 | Signal control circuit |
| CN115328006B (en) * | 2022-10-13 | 2023-01-20 | 苏州华兴源创科技股份有限公司 | Signal control circuit |
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