CN112824229B - Avionics function test testing system - Google Patents
Avionics function test testing system Download PDFInfo
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- CN112824229B CN112824229B CN201911143140.3A CN201911143140A CN112824229B CN 112824229 B CN112824229 B CN 112824229B CN 201911143140 A CN201911143140 A CN 201911143140A CN 112824229 B CN112824229 B CN 112824229B
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Abstract
The invention discloses an avionics function test system, which comprises: the system comprises a control module, a simulator interface control module, a signal acquisition and simulation data structure management module and a redundant cloud data synchronous display control module; the output end of the control module is connected with the input end of the simulator, the output end of the simulator is connected with the input end of the simulator interface control module, the output end of the simulator interface control module is connected with the input end of the signal acquisition and simulation data structure management module, and the output end of the signal acquisition and simulation data structure management module is connected with the input end of the redundant cloud data synchronous display control module and the receiving end of the control module. The avionic function test system provided by the invention has the effects of developing a function test program and carrying out experiment verification on the actual application condition of a simulator, reproducing the automatic application scene and improving the reliability and the production efficiency of the automatic test of the function test.
Description
Technical Field
The embodiment of the invention relates to the technical field of avionics, in particular to an avionics function test system.
Background
The airplane needs to perform function tests on eight systems such as avionics, flight control, hydraulic, environmental control and power systems in the ground final assembly stage, a series of ground test works verify the functions of single-system and multi-system cross-linking according to a preset flow, the interfaces, functions and performances of all systems of the whole airplane are guaranteed to meet design requirements, and the subsequent test flight task is guaranteed to be smoothly developed.
The test system in the prior art has complete planning on the types and the number of the signals of the whole airplane after the airplane is assembled, realizes the automatic test coverage rate of more than 90 percent in the aspect of functional test, is convenient for executing the test with high efficiency and high precision, and simultaneously improves the convenience in the aspects of effectively searching fault points, positioning fault reasons and the like.
However, the test system in the prior art is used for the later functional test after the assembly of the airplane is completed, and is not suitable for the earlier research of the functional test of the assembly.
Disclosure of Invention
The invention provides an avionics function test system, which is used for realizing the effects of developing a function test program and carrying out experimental verification on the actual application condition of a simulator, reproducing the automatic application scene and improving the reliability and the production efficiency of the automatic test of the function test.
The embodiment of the invention provides an avionics function test system, which is characterized by comprising the following components: the system comprises a control module, a simulator interface control module, a signal acquisition and simulation data structure management module and a redundant cloud data synchronous display control module;
the output end of the control module is connected with the input end of the simulator and used for sending a control instruction to the simulator;
the output end of the simulator is connected with the input end of the simulator interface control module and used for generating a simulation signal according to the control instruction and sending the simulation signal to the simulator interface control module;
the output end of the simulator interface control module is connected with the input end of the signal acquisition and simulation data structure management module and is used for collecting the analog signals to form a collected signal, converting the collected signal into a digital string, packaging the digital string into a program flow packet according to a timestamp and sending the program flow packet to the signal acquisition and simulation data structure management module;
a first output end of the signal acquisition and simulation data structure management module is connected with an input end of the redundant cloud data synchronous display and control module, and a second output end of the signal acquisition and simulation data structure management module is connected with a receiving end of the control module, so that the program flow packet is analyzed to form an analysis signal, the analysis signal is sent to the control module, and the analysis signal is sent to the redundant cloud data synchronous display and control module according to the timestamp;
the redundant cloud data synchronous display and control module is used for storing and displaying the analytic signals;
the control module is further used for adjusting the control instruction according to the difference value between the analytic signal and a preset analytic signal when the difference value between the analytic signal and the preset analytic signal is larger than a preset value, so that the difference value between the analytic signal and the preset analytic signal is smaller than the preset value;
the analog signals include control signals, fault signals, and status signals.
Further, the simulator interface control module includes: the system comprises a multi-bus data transmission management submodule, a first document management submodule, a data bus simulation technology submodule and a test execution submodule;
the input end of the multi-bus data transmission management submodule is connected with the output end of the simulator, and the output end of the multi-bus data transmission management submodule is connected with the input end of the first document management submodule and used for collecting the analog signals to form a collected signal and sending the collected signal to the first document management submodule;
the data bus simulation technology submodule is connected with a receiving end of the first document management submodule, an output end of the first document management submodule is connected with an input end of the test execution submodule, and the data bus simulation technology submodule is used for controlling the first document management submodule so that the first document management submodule converts the collected signal into a digital string and sends the digital string to the test execution submodule;
and the output end of the test execution submodule is connected with the input end of the signal acquisition and simulation data structure management module and is used for packaging the digital strings into a program flow packet according to a timestamp and sending the program flow packet to the signal acquisition and simulation data structure management module.
Further, the signal acquisition and simulation data structure management module comprises: the signal acquisition and simulation data structure management module comprises: the system comprises a signal real-time acquisition interface sub-module, a data analysis and simulation signal interface sub-module and a second document management sub-module;
the input end of the signal real-time acquisition interface sub-module is connected with the output end of the simulator interface control module, and the output end of the signal real-time acquisition interface sub-module is respectively connected with the input end of the second document management sub-module and the input end of the data analysis and simulation signal interface sub-module, and is used for receiving the program flow packet and sending the program flow packet to the data analysis and simulation signal interface sub-module;
a first output end of the data analysis and simulation signal interface sub-module is connected with an input end of the redundant cloud data synchronous display and control module, and a second output end of the data analysis and simulation signal interface sub-module is connected with a receiving end of the control module;
the second document management submodule is used for controlling the data analysis and simulation signal interface submodule so that the data analysis and simulation signal interface submodule analyzes the program flow packet to form an analysis signal, sends the analysis signal to the control module and sends the analysis signal to the redundant cloud data synchronous display and control module according to the timestamp.
Further, the redundant cloud data synchronization display and control module comprises: the system comprises a distributed data center server, a general aircraft flight simulation data server and a simulation cockpit display and control console;
the input end of the distributed data center server is connected with the output end of the signal acquisition and simulation data structure management module, the acquisition end of the distributed data center server is connected with the general aircraft flight simulation data server, and the output end of the distributed data center server is connected with the input end of the display and control console of the simulation cockpit;
the general airplane flight simulation data server is used for generating airplane model parameters and sending the airplane model parameters to the distributed data center server;
the distributed data center server is used for storing the analysis signal and the airplane model parameter, and sending the analysis signal and the airplane model parameter to the simulation cockpit display and control console when judging that the analysis signal and the airplane model parameter are preset signals;
and the simulated cockpit display and control console is used for displaying the analytic signal and the airplane model parameters.
Furthermore, the display control console of the simulated cockpit also comprises an output end; the distributed data center server also comprises a feedback end; the output end of the simulation cockpit display and control console is connected with the feedback end of the distributed data center server, and the simulation cockpit display and control console is used for sending the state change instruction of the simulation cockpit display and control console to the distributed data center server so that the distributed data center server stores the state change instruction.
Further, the simulation cockpit display and control platform includes: the control unit, the display panel, the instrument, the button and the steering column;
the control unit is respectively connected with a display panel, an instrument, a button and a steering column, and is used for receiving the analytic signal and the airplane model parameter, changing the current states of the display panel, the instrument, the button and the steering column according to the analytic signal and the airplane model parameter, acquiring a state change instruction and sending the state change instruction to the distributed data center server;
and the state change instruction is a change instruction between the state of the display panel, the instrument, the button and the steering column after the change of the parameters of the airplane model and the current state according to the analytic signal.
Further, the distributed data center server is further configured to store the state change instruction.
Furthermore, the control end of the control module is connected with the control end of the redundant cloud data synchronous display and control module, and the control module is further used for calling the analysis signal stored by the redundant cloud data synchronous display and control module and controlling the state of the airplane according to the called analysis signal.
Further, the redundant cloud data synchronization display and control module further comprises: the method comprises the steps that a cloud data network building device and a plurality of terminals are arranged; the cloud data network building equipment is respectively connected with the distributed data center server and the plurality of terminals;
the cloud data network building equipment is used for respectively storing the analysis signals stored by the distributed data center server in the plurality of terminals so that the plurality of terminals can store the analysis signals.
Further, the control module comprises an upper computer.
In summary, in the present embodiment, through the combined action of the control module, the simulator interface control module, the signal acquisition and simulation data structure management module and the redundant cloud data synchronous display control module, the problem that the test system in the prior art is in the later functional test after the aircraft assembly is completed and is not suitable for the earlier stage research of the assembly functional test is solved, the development of the functional test program and the actual application condition of the simulator are experimentally verified, the automation application scenario is reproduced, and the reliability of the functional test automation test and the production efficiency are improved.
Drawings
Fig. 1 is an avionics functional test system provided in an embodiment of the present invention;
FIG. 2 is a schematic diagram of another test system for avionics functional tests according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a test system for an avionics function test provided in accordance with an embodiment of the present invention;
fig. 4 is a schematic diagram of another avionics function test system according to an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some of the structures related to the present invention are shown in the drawings, not all of the structures.
Fig. 1 is a schematic diagram of an avionics function test system according to an embodiment of the present invention, where the avionics function test system includes: the system comprises a control module 10, a simulator 20, a simulator interface control module 30, a signal acquisition and simulation data structure management module 40 and a redundant cloud data synchronous display control module 50; the output end OUT12 of the control module 10 is connected with the input end IN21 of the simulator 20, and is used for sending a control instruction to the simulator 20; the output end OUT22 of the simulator 20 is connected with the input end IN31 of the simulator interface control module 30, and is configured to generate an analog signal according to the control instruction, and send the analog signal to the simulator interface control module 30; the output end OUT32 of the simulator interface control module 30 is connected with the input end IN41 of the signal acquisition and simulation data structure management module 40, and is used for collecting analog signals to form a collected signal, converting the collected signal into a digital string, packaging the digital string into a program flow packet according to a timestamp, and sending the program flow packet to the signal acquisition and simulation data structure management module; the first output end OUT42 of the signal acquisition and simulation data structure management module 40 is connected with the input end IN51 of the redundant cloud data synchronization display and control module 50, and the second output end OUT43 of the signal acquisition and simulation data structure management module 40 is connected with the receiving end IN11 of the control module 10, and is used for analyzing the program flow packet to form an analysis signal, sending the analysis signal to the control module 10 and sending the analysis signal to the redundant cloud data synchronization display and control module 50 according to the timestamp; the redundant cloud data synchronous display and control module 50 is used for storing and displaying the analytic signals; the control module 10 is further configured to adjust the control instruction according to a difference between the analytic signal and the preset analytic signal when the difference between the analytic signal and the preset analytic signal is greater than a preset value, so that the difference between the analytic signal and the preset analytic signal is smaller than the preset value; the analog signals include control signals, fault signals, and status signals.
The simulator interface control module 30 may be composed of an industrial personal computer and various boards (bus signals, analog signals, discrete signals, etc.), or may be constructed together with the control module 10. The signal acquisition and simulation data structure management module 40 may be composed of an industrial personal computer and various bus signal boards (ARINC 429, ARINC664, ARINC825, etc.) used in the simulator interface control module 30, or an acquisition-side industrial control system combined with the control module 10 is separately built.
Specifically, the simulator 20 generates an analog signal according to a control instruction sent by the control module, and sends the analog signal to the simulator interface control module 30, the analog signal is collected into a collected signal through the simulator interface control module 30, the collected signal is converted into a digital string, the digital string is packed into a program flow packet according to a timestamp and sent to the signal collection and simulation data structure management module 40, the program flow packet is analyzed by the signal collection and simulation data structure management module 40, the analyzed signal is sent to the control module 10, and the analyzed signal is sent to the redundant cloud data synchronization display control module 50 according to the timestamp, so that the redundant cloud data synchronization display control module 50 stores and displays the analyzed signal. In addition, the control module 10 compares the received analyzed signal with a preset analysis signal, and adjusts the control command according to the difference between the analyzed signal and the preset analysis signal when the difference between the analyzed signal and the preset analysis signal is greater than the preset value, so that the difference between the analyzed signal and the preset analysis signal is smaller than the preset value.
For understanding, the following description exemplifies the whole operation process of the avionics functional test system by taking the landing gear test in the aircraft functional test as an example, but the present application is not limited thereto.
Before describing this example in detail, a brief description will be given of the state of the aircraft after obtaining an instruction to lower. After the airplane obtains an instruction of needing to descend, under the condition of automatic driving, a flap is required to be released and a speed reducing plate is required to be opened according to the speed requirement in a descending stage, and then an airspeed signal is one; after obtaining the indication of the descending height, the horizontal tail wing and the aileron need to be continuously adjusted so that the descending height of the airplane meets the requirement, and the required height is fed back and is a product obtained by integrating various signals of a GPS (global positioning system), a radar and air pressure; when the speed reaches below a certain limit, allowing the undercarriage to be released; when the undercarriage is grounded, the proximity sensors sense signals and feed the signals back to the avionic system, so that the airplane wheel is allowed to brake. A series of signals have a certain logical relationship with each other, and after the signals are transmitted to the avionic system, the signals are logically judged by an analysis unit in the avionic system, so that corresponding actions are started, and the safe operation of the airplane is ensured.
In this example, the simulator 20 generates an analog signal according to a control instruction sent by the control module 10, where the analog signal may include, for example, a signal indicating whether the airplane wheel is on the ground (a signal corresponding to each proximity sensor), and the simulator interface control module 30 collects the analog signal and analyzes the physical meaning of the collected signal at the same time, because the signal sending required by the test is time-sequential and logical, the collected signal needs to be converted into a digital string by the simulator interface control module, and the digital string is packed into a program flow packet according to a timestamp and sent to the signal acquisition and simulation data structure management module 40. The signal acquisition and simulation data structure management module 40 acts like a virtual landing gear in the execution of this test case. When a program flow package is received through the signal acquisition and simulation data structure management module 40, the program flow package is analyzed into values corresponding to the sensors, and after the values are judged through the combined action with the control module 10 (namely, an approaching state is given), if the parameter requirement of the test is met, a signal that the undercarriage is located and locked is fed back to the control module 10, and meanwhile, the state and related signals are sent to the redundant cloud data synchronous display control module according to the time stamp to be stored and displayed. When the feedback meets the judgment condition (that the undercarriage has fallen in place) in the automatic test case, the undercarriage lifting process is continuously executed, at this time, the simulator 20 sends a signal on the ground as a premise of lifting the wheel, and then the similar process is automatically executed. If the parameter requirement of the test is not met, the control module 10 resends the control instruction according to the received signal, so that the simulator 20 further generates a corresponding simulation signal according to the control instruction of course, and the response of the simulator to the signal at this time is further verified through the avionics function test system. All the processes and states can be monitored and recorded through the control module 10, and the states can be observed in the redundant cloud data synchronous display and control module 50. Therefore, a complete test management platform for optimizing, searching, intelligently compiling, automatically loading and verifying the avionics and related system function test schemes in real time is realized, and the construction of a core architecture platform of the full-machine integrated avionics function test intelligent test system is realized.
In summary, in the embodiment, through the combined action of the control module, the simulator interface control module, the signal acquisition and simulation data structure management module and the redundant cloud data synchronous display and control module, the problem that a test system in the prior art is in later functional test after the aircraft assembly is completed and cannot be applied to early-stage research of the assembly functional test is solved, the development of a functional test program and the actual application condition of the simulator are experimentally verified, the automatic application scene is reproduced, and the reliability of the functional test automatic test and the production efficiency are improved.
Fig. 2 is a schematic diagram of another avionics function test system according to an embodiment of the present invention. On the basis of the above scheme, optionally, referring to fig. 2, the simulator interface control module 30 includes: a multi-bus data transmission management submodule 31, a first document management submodule 32, a data bus simulation technology submodule 33 and a test execution submodule 34; the input end IN311 of the multi-bus data transmission management submodule 31 is connected with the output end OUT22 of the simulator 20, and the output end OUT312 of the multi-bus data transmission management submodule 31 is connected with the input end IN313 of the first document management submodule 32, so that analog signals are collected to form a collected signal, and the collected signal is sent to the first document management submodule 32; the data bus simulation technology submodule 33 is connected with a receiving end IN314 of the first document management submodule 32, an output end OUT315 of the first document management submodule 32 is connected with an input end IN315 of the test execution submodule 34, and the data bus simulation technology submodule 33 is used for controlling the first document management submodule 32 so that the first document management submodule 32 converts the collected signal into a digital string and sends the digital string to the test execution submodule 34; the output end OUT316 of the test execution submodule 34 is connected to the input end IN41 of the signal acquisition and simulation data structure management module 40, and is configured to package the digital strings into a program flow packet according to the time stamp and send the program flow packet to the signal acquisition and simulation data structure management module 40.
The first document management submodule 32 may include, for example, an ICD document management submodule.
Specifically, the multi-bus data transmission management sub-module 31 collects and summarizes the signals generated by the simulator 20, and performs physical meaning analysis of the signals through the first document management sub-module 32, because the signal transmission required by the test is time-sequential and logical, that is, which signal is transmitted when, so that the test execution sub-module 34 needs to intervene, and transmits the time-sequential test signals to the simulation data structure management module 40 on the bus (here, this is also equivalent to simulating the flow of the real aircraft sensors processing and transmitting instructions through the avionic system). That is, when an automatic test flow is formulated, the signals generated by the simulator 20 of the specific system are controlled and collected according to the test flow and the management requirements of the ICD document, target address information is loaded, the signals are converted into specific time-sequential bus data streams according to the data bus simulation technology and the requirements of time sequence, a test execution strategy is established in the test execution system, and finally, signal excitation output is performed in the form of the time-sequential bus data streams through the bus data board card.
Fig. 3 is a schematic diagram of another test system for avionics function tests according to an embodiment of the present invention. On the basis of the above scheme, optionally, referring to fig. 3, the signal acquisition and simulation data structure management module 40 includes: a signal real-time acquisition interface sub-module 41, a data analysis and simulation signal interface sub-module 42 and a second document management sub-module 43; the input end IN411 of the signal real-time acquisition interface submodule 41 is connected with the output end OUT32 of the simulator interface control module 30, and the output end OUT412 of the signal real-time acquisition interface submodule 41 is respectively connected with the second document management submodule 43 and the input end IN413 of the data analysis and simulation signal interface submodule 42, and is used for receiving a program flow package and sending the program flow package to the data analysis and simulation signal interface submodule 42; a first output end OUT414 of the data analysis and simulation signal interface submodule 42 is connected with an input end IN51 of the redundant cloud data synchronous display and control module 50, and a second output end OUT415 of the data analysis and simulation signal interface submodule 42 is connected with a receiving end IN11 of the control module 10; the second document management sub-module 43 is configured to control the data parsing and simulation signal interface sub-module 42, so that the data parsing and simulation signal interface sub-module 42 parses the program flow packet to form a parsing signal, sends the parsing signal to the control module 10, and sends the parsing signal to the redundant cloud data synchronization display and control module 50 according to the timestamp.
The second document management submodule 43 may include, for example, an ICD document management submodule.
Specifically, the signal real-time acquisition interface sub-module 41 functions as a receiving end of the display control network, and is configured to perform real-time signal acquisition on an automated test flow sent by the simulator interface control module 30, and the data analysis and simulation signal interface sub-module 42 performs real-time analysis on information such as system parameters and states of the acquired time-sequenced bus data stream by loading the ICD document management sub-module, sends the analyzed data stream to the redundant cloud data synchronization display control module 50 in the form of a data packet with a timestamp, and stores and calls the analyzed data stream through the redundant cloud data synchronization display control module 50.
Fig. 4 is a schematic diagram of another avionics function test system according to an embodiment of the present invention. On the basis of the above scheme, optionally, referring to fig. 4, the redundant cloud data synchronization display and control module includes: a distributed data center server 51, a general aircraft flight simulation data server 52 and a simulation cockpit display control console 53; an input end IN511 of the distributed data center server 51 is connected with an output end OUT42 of the signal acquisition and simulation data structure management module 40, an acquisition end IN512 of the distributed data center server 51 is connected with the general airplane flight simulation data server 52, and an output end OUT513 of the distributed data center server 51 is connected with an input end IN514 of the simulation cockpit display and control console 53; the general airplane flight simulation data server 52 is used for generating airplane model parameters and sending the airplane model parameters to the distributed data center server 51; the distributed data center server 51 is used for storing the analytic signals and the airplane model parameters, and sending the analytic signals and the airplane model parameters to the display control console 53 of the simulated cockpit when judging that the analytic signals and the airplane model parameters are preset signals; the simulated cockpit display and control console 53 is used for displaying the analytic signals and the airplane model parameters.
The distributed data center server 51 is configured to perform multi-parameter arrangement, data fusion, and distributed storage among the data center servers on various system parameters received from the signal acquisition and simulation data structure management module 40, general flight model parameters (parameters sent by the general aircraft flight simulation data server 52) acquired from the cloud data network, and various system feedbacks received from the cockpit display control, and meanwhile, update data of the data center in real time according to the timestamp definition, and feed the state back to the control module 10. The general aircraft flight simulation data server 52 specifically provides various system parameters and corresponding logics based on a general aircraft model, and is used for matching with the acquired system parameters of the supplementary distributed data center server 51 so as to be beneficial to displaying various parameters required by display control of the complete simulation cockpit. The simulation cockpit display and control console 53 is built in a generalized simulation cockpit mode and used for displaying various system parameters and information which can be obtained in the whole cloud data synchronization network in the cockpit after a model is loaded. Namely, the redundant cloud data synchronous display and control module performs distributed storage on the analyzed data stream; in addition, the missing parameters can be supplemented by the general airplane flight simulation data server 52; meanwhile, the data and command lines stored through the cloud are sent to the simulation cockpit display and control console 53 and displayed in the simulation cockpit display and control console 53. However, the test system in the prior art is used for the later-stage function test after the assembly of the airplane is completed, and cannot be applied to the early-stage research of the assembly function test, and particularly, when part of the signal types to be simulated cannot be provided or are lost, the operation of the whole system cannot be realized.
Illustratively, parameters of 5 systems need to be displayed in the cockpit to form a complete state display of the aircraft cockpit, and then one of the systems simulates a signal generation parameter through the simulator 20, and if the other 4 system parameters are not supplemented completely, the parameter logic determination function in the distributed data center server 51 has no way to send data to the simulated cockpit display and control console 53, and if the complete aircraft state cannot be seen on the cockpit display and control platform, the 4 system parameters to be supplemented are provided through the simulated cockpit display and control console 53. That is, the data in the simulated cockpit display console 53 is displayed as completely and logically related as possible.
On the basis of the above scheme, optionally, with continued reference to fig. 4, the analog cockpit display and control console 53 further includes an output terminal OUT515; the distributed data center server 51 further comprises a feedback terminal IN516; the output end OUT515 of the simulation cockpit display and control console 53 is connected with the feedback end IN516 of the distributed data center server 51, and the simulation cockpit display and control console 53 is used for sending the state change instruction of the simulation cockpit display and control console to the distributed data center server so that the distributed data center server stores the state change instruction.
The display console 53 of the analog cockpit is provided with a display panel and an instrument, and operable parts such as a button, a knob, a steering column and an accelerator push rod, which can feed back some state change instructions to the distributed data center server 51, and the distributed data center server 51 can update the state data synchronously.
On the basis of the above scheme, optionally, the simulation cockpit display and control console 53 includes: a control unit, a display panel, a meter, a button, and a steering column (not shown in the figure); the control unit is respectively connected with the display panel, the instrument, the button and the steering column, and is used for receiving the analytic signal and the airplane model parameter, changing the current states of the display panel, the instrument, the button and the steering column according to the analytic signal and the airplane model parameter, acquiring a state change instruction and sending the state change instruction to the distributed data center server; the state change instruction is a change instruction between the state of the display panel, the instrument, the button and the steering column after being changed according to the analytic signal and the parameters of the airplane model and the current state. Optionally, the distributed data center server 51 is further configured to store the state change instruction.
On the basis of the above scheme, optionally, the control end OUT13 of the control module 10 is connected with the control end IN52 of the redundant cloud data synchronous display and control module 50, and the control module 10 is further configured to call an analysis signal stored IN the redundant cloud data synchronous display and control module 50, and control the state of the aircraft according to the called analysis signal.
On the basis of the above scheme, optionally, the redundant cloud data synchronization display and control module 50 further includes: a cloud data network building device and a plurality of terminals (not shown in the figure); the cloud data network building equipment is respectively connected with the distributed data center server and the plurality of terminals; the cloud data network building equipment is used for storing the analysis signals stored by the distributed data center server in the plurality of terminals respectively, so that the plurality of terminals store the analysis signals.
The distributed data center server 51 realizes multi-terminal storage of data by using a distributed mechanism, realizes redundant backup, and realizes verification, sharing and service centralized management of redundant networked data through network equipment. The distributed data center server 51 utilizes a distributed mechanism to store the avionic data to be displayed in a distributed storage mode, so that the key data are stored in a large amount and called in real time, and the problems that the function test cannot be carried out and the display control platform cannot normally display the data due to the data loss caused by the failure of a single storage server are prevented; the content of the redundant cloud storage is divided into redundant storage and data cloud calling, so that real-time synchronous backup of data in different places is realized, and safer transmission and calling of the data are realized through a cloud storage technology. Meanwhile, the hardware scale of laboratory stored data can be simplified, the storage resources of different places are fully utilized, and the network architecture is simplified. And meanwhile, the problem of data reading congestion is solved. Because the avionics system needs to call a large amount of data in real time and each instrument and display in the cockpit display, when one channel reads a large amount of data, the other large amount of data can be read from the redundant data stored in a distributed mode in other channels, and the possibility of data congestion of a single channel is overcome.
On the basis of the scheme, optionally, the control module comprises an upper computer.
The upper computer system is used for managing the simulator interface control module 30, internal functions, the signal acquisition and simulation data structure management module 40, the redundant cloud data synchronous display and control module 50, terminals and the like, and comprises functions of terminal electrification, system state monitoring and diagnosis, parameter online management in a network, networked service driving and the like.
In summary, the avionics function test system provided by the embodiment of the invention builds a core platform for the comprehensive test of the final assembly function test, provides a foundation and a universal interface, can effectively perform experiment verification on the actual application condition of each system simulator, reproduces the automatic application situation, and improves the reliability and the production efficiency of the automatic test of the function test.
It is to be noted that the foregoing description is only exemplary of the invention and that the principles of the technology may be employed. Those skilled in the art will appreciate that the present invention is not limited to the particular embodiments described herein, and that various obvious changes, rearrangements and substitutions will now be apparent to those skilled in the art without departing from the scope of the invention. Therefore, although the present invention has been described in some detail by the above embodiments, the invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the invention, and the scope of the invention is determined by the scope of the appended claims.
Claims (9)
1. An avionics functional test testing system, comprising: the system comprises a control module, a simulator interface control module, a signal acquisition and simulation data structure management module and a redundant cloud data synchronous display control module;
the output end of the control module is connected with the input end of the simulator and used for sending a control instruction to the simulator;
the output end of the simulator is connected with the input end of the simulator interface control module and used for generating a simulation signal according to the control instruction and sending the simulation signal to the simulator interface control module;
the output end of the simulator interface control module is connected with the input end of the signal acquisition and simulation data structure management module and is used for collecting the analog signals to form a collected signal, converting the collected signal into a digital string, and packaging the digital string into a program flow packet according to a timestamp to be sent to the signal acquisition and simulation data structure management module;
a first output end of the signal acquisition and simulation data structure management module is connected with an input end of the redundant cloud data synchronous display and control module, and a second output end of the signal acquisition and simulation data structure management module is connected with a receiving end of the control module, so that the program flow packet is analyzed to form an analysis signal, the analysis signal is sent to the control module, and the analysis signal is sent to the redundant cloud data synchronous display and control module according to the timestamp;
the redundant cloud data synchronous display and control module is used for storing and displaying the analytic signals;
the control module is further used for adjusting the control instruction according to the difference value between the analytic signal and a preset analytic signal when the difference value between the analytic signal and the preset analytic signal is larger than a preset value, so that the difference value between the analytic signal and the preset analytic signal is smaller than the preset value;
the analog signals comprise control signals, fault signals and state signals;
the control end of the control module is connected with the control end of the redundant cloud data synchronous display and control module, and the control module is further used for calling the analysis signal stored by the redundant cloud data synchronous display and control module and controlling the state of the airplane according to the called analysis signal.
2. The avionics functionality test testing system of claim 1, wherein the simulator interface control module comprises: the system comprises a multi-bus data transmission management submodule, a first document management submodule, a data bus simulation technology submodule and a test execution submodule;
the input end of the multi-bus data transmission management submodule is connected with the output end of the simulator, and the output end of the multi-bus data transmission management submodule is connected with the input end of the first document management submodule and used for collecting the analog signals to form a collected signal and sending the collected signal to the first document management submodule;
the data bus simulation technology submodule is connected with a receiving end of the first document management submodule, an output end of the first document management submodule is connected with an input end of the test execution submodule, and the data bus simulation technology submodule is used for controlling the first document management submodule so that the first document management submodule converts the collected signal into a digital string and sends the digital string to the test execution submodule;
and the output end of the test execution submodule is connected with the input end of the signal acquisition and simulation data structure management module and is used for packaging the digital strings into a program flow packet according to a timestamp and sending the program flow packet to the signal acquisition and simulation data structure management module.
3. The avionics functional test testing system of claim 1, wherein the signal acquisition and simulation data structure management module comprises: the system comprises a signal real-time acquisition interface sub-module, a data analysis and simulation signal interface sub-module and a second document management sub-module;
the input end of the signal real-time acquisition interface sub-module is connected with the output end of the simulator interface control module, and the output end of the signal real-time acquisition interface sub-module is respectively connected with the input end of the second document management sub-module and the input end of the data analysis and simulation signal interface sub-module, and is used for receiving the program flow package and sending the program flow package to the data analysis and simulation signal interface sub-module;
a first output end of the data analysis and simulation signal interface sub-module is connected with an input end of the redundant cloud data synchronous display control module, and a second output end of the data analysis and simulation signal interface sub-module is connected with a receiving end of the control module;
the second document management submodule is used for controlling the data analysis and simulation signal interface submodule so that the data analysis and simulation signal interface submodule analyzes the program flow packet to form an analysis signal, sends the analysis signal to the control module and sends the analysis signal to the redundant cloud data synchronous display and control module according to the timestamp.
4. The avionics function test testing system according to claim 1, wherein the redundant cloud data synchronous display and control module comprises: the system comprises a distributed data center server, a general aircraft flight simulation data server and a simulation cockpit display and control console;
the input end of the distributed data center server is connected with the output end of the signal acquisition and simulation data structure management module, the acquisition end of the distributed data center server is connected with the general aircraft flight simulation data server, and the output end of the distributed data center server is connected with the input end of the display and control console of the simulation cockpit;
the general airplane flight simulation data server is used for generating airplane model parameters and sending the airplane model parameters to the distributed data center server;
the distributed data center server is used for storing the analysis signal and the airplane model parameter, and sending the analysis signal and the airplane model parameter to the simulation cockpit display and control console when judging that the analysis signal and the airplane model parameter are preset signals;
and the simulation cockpit display and control console is used for displaying the analysis signal and the airplane model parameter.
5. The avionics functional test testing system according to claim 4, wherein the simulated cockpit display console further comprises an output; the distributed data center server also comprises a feedback end; the output end of the simulation cockpit display and control console is connected with the feedback end of the distributed data center server, and the simulation cockpit display and control console is used for sending the state change instruction of the simulation cockpit display and control console to the distributed data center server so that the distributed data center server stores the state change instruction.
6. The avionics functional test testing system of claim 5, wherein the simulated cockpit display console comprises: the control unit, the display panel, the instrument, the button and the steering column;
the control unit is respectively connected with a display panel, an instrument, a button and a steering column, and is used for receiving the analysis signal and the airplane model parameter, changing the current states of the display panel, the instrument, the button and the steering column according to the analysis signal and the airplane model parameter, acquiring a state change instruction and sending the state change instruction to the distributed data center server;
and the state change instruction is a change instruction between the state of the display panel, the instrument, the button and the steering column after the change of the parameters of the airplane model and the current state according to the analytic signal.
7. The avionics functional test testing system of claim 6, wherein the distributed data center server is further configured to store the state change instructions.
8. The avionics function test testing system according to claim 4, wherein the redundant cloud data synchronous display and control module further comprises: the method comprises the steps that a cloud data network building device and a plurality of terminals are arranged; the cloud data network building equipment is respectively connected with the distributed data center server and the plurality of terminals;
the cloud data network building equipment is used for respectively storing the analysis signals stored by the distributed data center server in the plurality of terminals so that the plurality of terminals can store the analysis signals.
9. The avionics functional test testing system of claim 1, wherein the control module comprises an upper computer.
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