CN119292956A - A helicopter electromechanical management system simulation test platform and system - Google Patents
A helicopter electromechanical management system simulation test platform and system Download PDFInfo
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- CN119292956A CN119292956A CN202411192198.8A CN202411192198A CN119292956A CN 119292956 A CN119292956 A CN 119292956A CN 202411192198 A CN202411192198 A CN 202411192198A CN 119292956 A CN119292956 A CN 119292956A
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- 238000012360 testing method Methods 0.000 title claims abstract description 132
- 238000004088 simulation Methods 0.000 title claims abstract description 109
- 230000003993 interaction Effects 0.000 claims abstract description 18
- 238000007726 management method Methods 0.000 claims description 71
- 230000005284 excitation Effects 0.000 claims description 53
- 230000003750 conditioning effect Effects 0.000 claims description 17
- 238000012545 processing Methods 0.000 claims description 17
- 238000004891 communication Methods 0.000 claims description 9
- 238000002347 injection Methods 0.000 claims description 9
- 239000007924 injection Substances 0.000 claims description 9
- 238000012544 monitoring process Methods 0.000 claims description 9
- 238000012546 transfer Methods 0.000 claims description 7
- 238000013500 data storage Methods 0.000 claims description 6
- 238000001514 detection method Methods 0.000 claims description 3
- 238000004806 packaging method and process Methods 0.000 claims description 3
- 238000012986 modification Methods 0.000 abstract description 4
- 230000004048 modification Effects 0.000 abstract description 4
- 238000013461 design Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 239000002828 fuel tank Substances 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 238000004132 cross linking Methods 0.000 description 1
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- 238000005516 engineering process Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
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Abstract
本申请提供一种直升机机电管理系统模拟仿真测试平台及系统，属于直升机机电管理系统仿真测试技术领域，该直升机机电管理系统模拟仿真测试平台包括人机交互层、试验网络层、仿真测试层和系统试验连接层，其中，人机交互层根据接口控制文件ICD和预先设置的自动测试程序产生模拟仿真激励；并通过试验网络层传输模拟仿真激励给仿真测试层；仿真测试层根据模拟仿真激励来模拟仿真环境，产生相应的激励信号并发送给系统试验连接层；系统试验连接层将激励信号转换为DB78标准接口信号并输出给真件设备层；能提高测试效率，可满足不同的修改场景需求，对于不同机电管理系统的不同接口控制文件适配性好。
The present application provides a helicopter electromechanical management system simulation test platform and system, which belongs to the technical field of helicopter electromechanical management system simulation test. The helicopter electromechanical management system simulation test platform includes a human-computer interaction layer, a test network layer, a simulation test layer and a system test connection layer, wherein the human-computer interaction layer generates a simulation stimulus according to an interface control file ICD and a preset automatic test program; and transmits the simulation stimulus to the simulation test layer through the test network layer; the simulation test layer simulates the simulation environment according to the simulation stimulus, generates a corresponding stimulus signal and sends it to the system test connection layer; the system test connection layer converts the stimulus signal into a DB78 standard interface signal and outputs it to the real device layer; the test efficiency can be improved, the requirements of different modification scenarios can be met, and the adaptability to different interface control files of different electromechanical management systems is good.
Description
Technical Field
The invention belongs to the technical field of simulation test of a helicopter electromechanical management system, and particularly relates to a simulation test platform and system of the helicopter electromechanical management system.
Background
The electromechanical management system refers to an onboard equipment system which is necessary for supporting normal and safe operation of an aircraft and is not an avionics system, a flight control system and a propulsion system, and comprises a plurality of subsystems such as a power supply system, a fuel oil system, a hydraulic system, a ring control system and the like. The electromechanical management system simulation test platform can well simulate faults on the machine and is used for detecting whether the electromechanical management system can be completely and effectively operated.
In the related art, the simulation test equipment of the electromechanical management system is basically software for simulating the test developed independently for a single electromechanical management system, so that a large amount of time is consumed for adapting, and part of equipment cannot be automated, so that a user needs to manually detect test items. The suitability of different interface control files for different electromechanical management systems is poor.
Disclosure of Invention
In order to solve the technical problems of low efficiency of simulation test equipment of an electromechanical management system and poor suitability for different interface control files in the related art, the invention provides a simulation test platform and a simulation test system of the electromechanical management system of a helicopter, which can improve the test efficiency, can meet different scene modification requirements and have good suitability for different interface control files of different electromechanical management systems, and the technical scheme is as follows:
In a first aspect, a simulation test platform for a helicopter electromechanical management system is provided, comprising a man-machine interaction layer, a test network layer, a simulation test layer and a system test connection layer,
The man-machine interaction layer transmits the simulation excitation to the simulation test layer through the test network layer, and also sends a parameter setting command to the real piece equipment layer and receives a test result fed back by the real piece equipment layer;
the simulation test layer simulates a simulation environment according to the simulation excitation, generates a corresponding excitation signal and sends the excitation signal to the system test connection layer;
The system test connection layer converts the excitation signal into a DB78 standard interface signal and outputs the DB78 standard interface signal to the real part equipment layer.
Further, the system test connection layer is also used for distributing and managing power sources.
Optionally, the man-machine interaction layer comprises a main control industrial personal computer, wherein the main control industrial personal computer comprises a main control management unit and an FC bus communication unit, the main control management unit comprises a simulation management module, a model management module, an ICD management module, a data monitoring module, an automatic test module, a fault injection module, a data storage/playback/analysis module and a model library module,
The simulation management module is used for simulating the configuration of simulation excitation, the model management module is used for constructing an automatic test model, the ICD management module is used for editing and configuring an ICD, the data monitoring module is used for simulating the graphic monitoring of the simulation excitation, the automatic test module is used for setting and managing an automatic test program, the fault injection module is used for setting single-point faults of the automatic test program, the data storage/playback/analysis module is used for storing, processing and analyzing the simulation excitation, and the model library module is used for packaging the data of the automatic test program through the automatic test model and sending the data to the simulation test layer;
the FC bus communication unit comprises an FC simulation board card which is used for communication between the man-machine interaction layer and the FC board card of the equipment to be tested.
Optionally, the simulation test layer comprises an electromechanical system interface simulation device, wherein the electromechanical system interface simulation device comprises a PXIe simulator, the PXIe simulator is provided with an RS422A board card, an ARINC429 board card, a CAN bus board card, a DIO board card, an AO board card, an AI board card and a resistance analog output board card,
The system comprises an RS422A board card, an ARINC429 board card, a CAN bus board card, a DIO board card, an AO board card, an AI board card, a resistance analog output board card and a system test connection layer, wherein the RS422A board card is used for simulating and processing RS422A data, the ARINC429 board card is used for simulating and processing 429 data, the CAN bus board card is used for simulating and processing CAN data, the DIO board card is used for simulating and processing digital signals, the AO board card is used for output management of analog signals, the AI board card is used for input management of the analog signals, all board cards generate corresponding excitation signals and send the excitation signals to the system test connection layer, and the resistance analog output board card is used for simulating resistance values.
Optionally, the system test connection layer comprises signal conditioning and signal switching equipment, wherein the signal conditioning and signal switching equipment comprises a signal conditioning box and a signal switching box,
The signal conditioning box converts the excitation signal to obtain a DB78 standard interface signal, and the DB78 standard interface signal is output to the real-part equipment layer through the signal transfer box.
Further, the signal conditioning and signal switching device further comprises a signal breakpoint test box, wherein the signal breakpoint test box is used for completing detection and bypass acquisition of the excitation signal.
Further, the system test connection layer also comprises a power distribution control device, wherein the power distribution control device comprises a power master control box and a direct current power supply;
the power supply master control box is used for distributing and switching power supply, and the direct current power supply is used for providing stable direct current for the real equipment layer.
In a second aspect, a simulation test system for a helicopter electromechanical management system is provided, the system comprising the simulation test platform for a helicopter electromechanical management system of any one of the first aspect, and a real-part equipment layer,
The simulation test platform of the helicopter electromechanical management system generates simulation excitation according to an interface control file ICD and a preset automatic test program, generates corresponding excitation signals according to simulation excitation simulation environment, converts the excitation signals into DB78 standard interface signals and outputs the DB78 standard interface signals to a real equipment layer;
The helicopter electromechanical management system simulation test platform also sends a parameter setting command to the real equipment layer and receives a test result fed back by the real equipment layer.
The simulation test platform for the electromechanical management system of the helicopter provided by the invention adopts a modularized design, is favorable for adapting to different application scenes in the future, is favorable for improving the test efficiency by an automatic test design, can meet different scene modification requirements by convenient interface control file entry, has good suitability for different interface control files of different electromechanical management systems, and can adapt to simulation test requirements of a plurality of different electromechanical management systems.
Drawings
Fig. 1 is a schematic diagram of a simulation test platform of a helicopter electromechanical management system according to an embodiment of the invention.
Detailed Description
The application is described in further detail below with reference to specific embodiments and figures.
An embodiment of the invention provides a simulation test platform for a helicopter electromechanical management system, which comprises a man-machine interaction layer, a test network layer, a simulation test layer and a system test connection layer, as shown in figure 1.
The machine interaction layer generates simulation excitation according to the interface control file ICD and a preset automatic test program, and transmits the simulation excitation to the simulation test layer through the test network layer. The man-machine interaction layer also sends a parameter setting command to the real part equipment layer and receives a test result fed back by the real part equipment layer.
The man-machine interaction layer is used for man-machine delivery and master control management, configuring automatic test, inputting and managing different interface control files ICDs of different electromechanical management systems, loading ICDs with different requirements and automatic test, and changing the requirements according to different test environments at any time.
The main control industrial personal computer of the machine interaction layer is connected with the electromechanical system interface simulation equipment of the simulation test layer through the test network layer, and the main control industrial personal computer is communicated with the electromechanical system interface simulation equipment through the Ethernet and the hard wire network.
The simulation test layer generates corresponding excitation signals according to the simulation excitation simulation environment and sends the excitation signals to the system test connection layer.
The system test connection layer converts the excitation signal into a DB78 standard interface signal and outputs the DB78 standard interface signal to the real part equipment layer. The system test connection layer is used for conditioning and converting excitation signals, and further is also used for distributing and managing power sources.
In another embodiment, as shown in FIG. 1, the human-machine interaction layer comprises a master industrial personal computer. The master control industrial personal computer comprises a master control management unit and an FC bus communication unit.
The main control management unit comprises a simulation management module, a model management module, an ICD management module, a data monitoring module, an automatic test module, a fault injection module, a data storage/playback/analysis module and a model library module.
The simulation management module is used for simulating the configuration of simulation excitation;
the model management module is used for constructing an automatic test model;
the ICD management module is used for editing and configuring the ICD;
The data monitoring module is used for simulating the graphic monitoring of the simulation excitation;
the automatic test module is used for setting and managing an automatic test program;
the fault injection module is used for setting single-point faults of the automatic test program;
The data storage/playback/analysis module is used for storing, processing and analyzing the analog simulation excitation;
The model library module is used for packaging the data of the automatic test program through the automatic test model and sending the data to the simulation test layer.
The FC bus communication unit comprises an FC simulation board card 1 and an FC simulation board card 2,
The FC simulation board cards 1 and 2 are used for communication between the man-machine interaction layer and the FC board card of the equipment to be tested.
In yet another embodiment, the simulation stimulus signal type sent by the man-machine interaction layer is at least one of RS422A, ARINC, CAN, DIO, AO/AI, and correspondingly, as shown in FIG. 1, the simulation test layer comprises an electromechanical system interface simulation device, wherein the electromechanical system interface simulation device comprises a PXIe simulator, the PXIe simulator is provided with an RS422A board card, an ARINC429 board card, a CAN bus board card, a DIO board card, an AO board card, an AI board card and a resistance analog output board card.
The RS422A board card is used for simulating and processing RS422A data;
The ARINC429 board is used for simulating and processing 429 data;
The CAN bus board card is used for simulating and processing CAN data;
the DIO board card is used for simulating and processing digital signals;
the AO board card and the AI board card are used for simulating and processing the analog signals. The AO board card is used for the output management of the analog signals, and the AI board card is used for the input management of the analog signals;
all the boards generate corresponding excitation signals and send the excitation signals to the system test connection layer.
The resistance analog output board card is used for simulating resistance values.
In another embodiment, as shown in FIG. 1, the system test connection layer includes signal conditioning and signal switching equipment. The signal conditioning and signal switching equipment comprises a signal conditioning box and a signal switching box.
The signal conditioning box is used for converting the excitation signal to obtain a DB78 standard interface signal, and the DB78 standard interface signal is output to the real-part equipment layer through the signal switching box.
Furthermore, the signal conditioning box also carries out amplitude limiting processing on signals such as voltage, current and the like which exceed the standard range in the excitation signal.
The signal transfer box is used for converging various excitation signals to a unified aviation plug connector, the aviation plug connector is connected to the real piece equipment layer through a test cable, and meanwhile, the signal transfer box also provides an aviation plug interface for crosslinking the excitation signals and the real piece equipment layer.
Further, in another embodiment, the signal conditioning and signal switching device further includes a signal breakpoint test box, through which detection and bypass collection of the excitation signal can be implemented, and functions such as signal open circuit and short circuit can be included. The front panel of the signal breakpoint test box separates the test environment from the real part end, and can realize bypass and fault injection functions through field connection of a short circuit block, and can also measure input and output signals through equipment such as a universal meter, an oscilloscope and the like, and meanwhile, a fault injection module is installed to support manual disconnection. The fault injection module can be used for manually operating signal on-off through the disconnection block of the panel, and manually testing the connection between the real equipment layer and the simulation test layer at the front panel disconnection block.
In another embodiment, further as shown in FIG. 1, the system test connection layer further comprises a power distribution control device. The power distribution control device can comprise a power master control box and a direct current power supply.
The power supply main control box is used for distributing and switching the power supply;
the direct current power supply is used for providing stable direct current power supply for the real equipment layer.
In another embodiment, a plurality of devices under test, such as device under test 1, device under test 2 to device under test N, included in the real device layer may be determined according to actual conditions.
By way of example, the device under test may be an electromechanical management computer, a remote interface unit, an electromechanical parameter display, or the like.
An embodiment of the present invention further provides a simulation test system for a helicopter electromechanical management system, as shown in fig. 1, where the system includes a simulation test platform for a helicopter electromechanical management system according to an embodiment of the present invention, and a real device layer,
The simulation test platform of the helicopter electromechanical management system generates simulation excitation according to the interface control file ICD and a preset automatic test program, generates corresponding excitation signals according to the simulation excitation simulation environment, converts the excitation signals into DB78 standard interface signals and outputs the DB78 standard interface signals to the real equipment layer;
The helicopter electromechanical management system simulation test platform also sends a parameter setting command to the real equipment layer and receives a test result fed back by the real equipment layer. For example, the parameter setting command can be atmospheric temperature, airspeed, main inertial navigation and the like, and the test result fed back by the real equipment layer can be left fuel tank oil quantity, left externally hung auxiliary fuel tank oil quantity and the like.
The foregoing has outlined rather broadly the more detailed description of the application in order that the detailed description thereof that follows may be better understood, and in order that the present application may be better understood. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the application, which are all within the scope of the application. In addition, the application is not fully described in the conventional technology.
Claims (8)
1. A simulation test platform for a helicopter electromechanical management system is characterized by comprising a man-machine interaction layer, a test network layer, a simulation test layer and a system test connection layer,
The man-machine interaction layer is used for generating simulation excitation according to the interface control file ICD and a preset automatic test program, transmitting the simulation excitation to the simulation test layer through the test network layer, and sending a parameter setting command to the real piece equipment layer and receiving a test result fed back by the real piece equipment layer;
The simulation test layer is used for simulating a simulation environment according to the simulation excitation, generating corresponding excitation signals and sending the excitation signals to the system test connection layer;
the system test connection layer is used for converting the excitation signal into a DB78 standard interface signal and outputting the DB78 standard interface signal to the real part equipment layer.
2. The helicopter electromechanical management system simulation test platform of claim 1, wherein the system test connection layer is further used for distribution and management of power.
3. The simulation test platform of the helicopter electromechanical management system according to claim 1, wherein the man-machine interaction layer comprises a master industrial personal computer, the master industrial personal computer comprises a master management unit and an FC bus communication unit, wherein the master management unit comprises a simulation management module, a model management module, an ICD management module, a data monitoring module, an automatic test module, a fault injection module, a data storage/playback/analysis module and a model library module,
The simulation management module is used for simulating the configuration of simulation excitation, the model management module is used for constructing an automatic test model, the ICD management module is used for editing and configuring an ICD, the data monitoring module is used for simulating the graphic monitoring of the simulation excitation, the automatic test module is used for setting and managing an automatic test program, the fault injection module is used for setting single-point faults of the automatic test program, the data storage/playback/analysis module is used for storing, processing and analyzing the simulation excitation, and the model library module is used for packaging the data of the automatic test program through the automatic test model and sending the data to the simulation test layer;
the FC bus communication unit comprises an FC simulation board card which is used for communication between the man-machine interaction layer and the FC board card of the equipment to be tested.
4. The helicopter electromechanical management system simulation test platform of claim 1, wherein the simulation test layer comprises an electromechanical system interface simulation device, the electromechanical system interface simulation device comprises a PXIe simulator, the PXIe simulator is provided with an RS422A board card, an ARINC429 board card, a CAN bus board card, a DIO board card, an AO board card, an AI board card and a resistance analog output board card,
The system comprises an RS422A board card, an ARINC429 board card, a CAN bus board card, a DIO board card, an AO board card, an AI board card, a system test connection layer and a resistance analog output board card, wherein the RS422A board card is used for simulating and processing RS422A data, the ARINC429 board card is used for simulating and processing 429 data, the CAN bus board card is used for simulating and processing CAN data, the DIO board card is used for simulating and processing digital signals, the AO board card is used for output management of analog signals, the AI board card is used for input management of the analog signals, all the board cards generate corresponding excitation signals and are sent to the system test connection layer, and the resistance analog output board card is used for simulating resistance values.
5. The helicopter electromechanical management system simulation test platform of claim 1, wherein the system test connection layer comprises signal conditioning and signal transfer equipment, the signal conditioning and signal transfer equipment comprises a signal conditioning box and a signal transfer box,
The signal conditioning box is used for converting the excitation signal to obtain a DB78 standard interface signal, and outputting the DB78 standard interface signal to the real-part equipment layer through the signal transfer box.
6. The simulation test platform of the helicopter electromechanical management system of claim 5, wherein the signal conditioning and signal switching device further comprises a signal breakpoint test box for completing detection and bypass acquisition of the excitation signal.
7. The helicopter electromechanical management system simulation test platform of claim 5, wherein the system test connection layer further comprises a power distribution control device, wherein the power distribution control device comprises a power master control box and a direct current power supply;
the power supply master control box is used for distributing and switching power supply, and the direct current power supply is used for providing stable direct current for the real equipment layer.
8. A helicopter electromechanical management system simulation test system, which is characterized by comprising the helicopter electromechanical management system simulation test platform as claimed in any one of claims 1 to 7 and a real equipment layer,
The simulation test platform of the helicopter electromechanical management system generates simulation excitation according to an interface control file ICD and a preset automatic test program, generates corresponding excitation signals according to simulation excitation simulation environment, converts the excitation signals into DB78 standard interface signals and outputs the DB78 standard interface signals to a real equipment layer;
The helicopter electromechanical management system simulation test platform also sends a parameter setting command to the real equipment layer and receives a test result fed back by the real equipment layer.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411192198.8A CN119292956A (en) | 2024-08-28 | 2024-08-28 | A helicopter electromechanical management system simulation test platform and system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411192198.8A CN119292956A (en) | 2024-08-28 | 2024-08-28 | A helicopter electromechanical management system simulation test platform and system |
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| CN119292956A true CN119292956A (en) | 2025-01-10 |
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| CN202411192198.8A Pending CN119292956A (en) | 2024-08-28 | 2024-08-28 | A helicopter electromechanical management system simulation test platform and system |
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- 2024-08-28 CN CN202411192198.8A patent/CN119292956A/en active Pending
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