JPWO2019054236A1 - Training system - Google Patents

Abstract

It can grasp the situation of the aircraft as a sign before an abnormality occurs, and provide technology to assist the pilot in preparing for the response. In the aircraft operation system 1, the display 50 acquires and displays the status from the radio 30 and the navigation device 10, and displays that there is an abnormality or change in the aircraft from the information of each device and navigation information. In addition, the display 50 monitors each navigation information during the flight other than the information of the abnormal range output by each device (radio 30, display 50), and sudden changes, previous values (average, etc.). It is displayed to the pilot when there is a discrepancy with or when it does not fall within the data range predicted from other navigation information.

Description

The present invention relates to an operation system for displaying an abnormality in aircraft navigation information on an in-aircraft display.

The display system installed in the aircraft displays the status information (normal / abnormal (malfunction) / power off, etc.) output by each device regarding the information output from each radio and navigation device connected to the display. To do. In addition, navigation information (speed information, altitude information, aircraft traveling direction, engine speed, etc.) from each device is basically displayed on the display as it is.

In addition, an analysis method capable of analyzing an abnormality that is not expected in advance has also been proposed (see, for example, Patent Document 1).

Japanese Unexamined Patent Publication No. 2014-144718

By the way, even if there is an error or information leakage in the navigation information from each device, if the status of the device is normal, it is displayed as it is. In addition, if the engine speed is within the predetermined range, it is difficult to recognize a normal one until it is out of the predetermined range even if it is significantly different from the normal one (immediately after the flight).

The present invention has been made in view of such a situation, and an object of the present invention is to solve the above problems.

The present invention is an operation system including a display device for displaying information acquired from a radio and a navigation system in an aircraft, and the display device is said to be based on the information acquired from the radio and the navigation device. The control unit has a control unit for determining the occurrence of an abnormality in an aircraft, a display unit for displaying the determination result by the control unit, and a storage unit for recording the determination criteria by the control unit and the acquired information. Even if the information is not in the range of abnormality output by the radio or navigation system, it is predicted from other navigation information when a sudden change occurs or when there is a deviation from the previous value. When the data does not fall within the data range, the display unit is controlled to display a warning.
In addition, the control unit extracts data of deviations from the previous navigation within a predetermined range, data of sudden changes within a predetermined time, and data of changes of preset predetermined navigation information beyond a predetermined range. Then, depending on the combination of the extracted data, the abnormality information may be output based on the predetermined combination and controlled to be displayed on the display unit.
Further, the control unit may display the display unit in a priority order when there are a plurality of items to be displayed when the display unit is displayed to call attention.

According to the present invention, the information that is not judged to be abnormal by each device can be consistent with the data of other devices when the change starts to occur or when the situation changes from normal time or immediately after flight. It is possible to quickly inform the pilot that there is no such thing, grasp the situation of the aircraft as a sign before an abnormality occurs, and realize a technology that assists the pilot in preparing for the response.

It is a schematic block diagram of the aircraft operation system which concerns on 1st Embodiment. It is a flowchart which shows the comparison process with normal change which concerns on 1st Embodiment. It is a flowchart which shows the comparison process with sudden change which concerns on 1st Embodiment. FIG. 5 is a flowchart showing a comparison process with comparison processing prediction data calculated from other navigation information according to the first embodiment. It is a flowchart which shows the display process which concerns on 1st Embodiment. It is a figure which shows the example of the priority table which concerns on 1st Embodiment. It is a figure which shows the schematic structure of the training system which concerns on 2nd Embodiment. It is a figure which shows the example of the simulated data edit screen which concerns on 2nd Embodiment. It is a figure which shows the example of the measurement value change screen which concerns on 2nd Embodiment. It is a figure which shows the example of the simulated data file setting screen which concerns on 2nd Embodiment. It is a flowchart of the measurement process which concerns on 2nd Embodiment. It is a figure which shows the example of the training result reference screen which concerns on 2nd Embodiment. It is a figure which shows the example of the test result which concerns on 2nd Embodiment. It is a figure which shows the example of the selection confirmation screen in the simulation setting PC which concerns on 2nd Embodiment.

Next, an embodiment for carrying out the present invention (hereinafter, simply referred to as “embodiment”) will be specifically described with reference to the drawings. The outline of this embodiment is as follows.

<First Embodiment>
FIG. 1 is a diagram showing a schematic configuration of an aircraft operation system 1 according to the present embodiment. The aircraft operation system 1 is mounted on the aircraft and notifies the pilot of the state of the aircraft. Specifically, the aircraft operation system 1 includes a plurality of navigation devices 10a, 10b, ..., a plurality of radios 30a, 30b, ..., And a display 50, which are a multiplex data bus or the like. It is connected by a network 90 composed of.

Navigation devices 10a, 10b, ... Are units driven to fly an aircraft, such as, for example, engines, transmissions, and flaps of an aircraft. When these plurality of navigation devices 10a, 10b, ... Are not distinguished, the description will be simply referred to as "navigation device 10".

The navigation device 10 outputs information corresponding to the function of the status information of the device and the navigation information of the aircraft to the display 50. The navigation information includes, for example, speed information, altitude information, information on the direction of travel of the aircraft, information on engine speed, and the like.

The radios 30a, 30b, ... Output the status information and setting information of each device to the display 50. The status information is, for example, information such as normal / abnormal (failure) / power off. When these plurality of radios 30a, 30b, ... Are not distinguished, the description will be simply referred to as "radio 30".

The display 50 includes a display unit 51, a control unit 52, and a storage unit 53.
The display unit 51 displays the status information and navigation information acquired from the navigation device 10, and the status information and setting information acquired from the radio 30.

In addition, the display unit 51 visually displays the information acquired from the navigation device 10 and the radio device 30 so that the pilot can see it. Further, the display unit 51 determines whether or not an abnormality has occurred based on the information, and displays according to the determination result. That is, when it is determined that an abnormality has occurred, the display unit 51 displays and outputs in a predetermined mode so that the pilot can easily recognize the occurrence of the abnormality.

Further, as a feature of the present embodiment, even if the information is not judged to be abnormal, when the change is starting to occur, that is, when there is a possibility that trouble is starting to occur, or when the situation is normal or immediately after the flight. If it has changed (for example, if the engine temperature is not outlier but is higher than usual, or if the engine speed is flying at a value close to the outlier), it will be different from the data of other equipment. Promptly tell the pilot that there is no consistency.

For items that do not normally change much, such as engine temperature and engine speed, a caution is displayed when a certain deviation occurs from the start-up value or the average value of each time. In addition, the same caution message is displayed for sudden changes in a short period of time. That is, even when the predicted navigation data prediction range is calculated from a sudden change or other navigation information and the prediction range deviates from the prediction range, the information is extracted and displayed as an alarm on the display unit 51. In addition, information that should be emphasized in terms of operation and aircraft characteristics is arbitrarily displayed at the top.

With regard to navigation information, it is difficult to respond promptly to maneuvering by displaying after an outlier, especially because it may affect the safe operation of the aircraft. Therefore, as described above, since the display is displayed on the display unit 51 as a sign before a real abnormality occurs, the pilot can appropriately grasp the situation of the aircraft and is ready to deal with it.

Specifically, the target of the information extraction process to be notified to the pilot is as follows, and the navigation information having an impact on the operation of the aircraft is extracted.
・ Engine speed information ・ Engine temperature information ・ Aircraft speed information ・ Aircraft altitude information ・ Aircraft attitude information (pitch, roll)

In addition, the pilot can arbitrarily select and set the navigation information item and adjust the reference value of advance notification. For example, it can be optimized to the pilot's ability by adjusting the reference value or the like according to the pilot's ability, carrier, or the like.

The control unit 52 performs various controls related to the operation of the aircraft. For example, the control unit 52 receives the operation of the pilot by a predetermined operation means, determines the control content by referring to the operation and the output values of the navigation device 10 and the radio 30, and corresponds to the device (navigation device 10). And radio 30 etc.).

The storage unit 53 has a storage medium such as a hard disk drive, and records information acquired from the navigation device 10 and the radio device 30.

Not only the information of each device on the display 50 and the abnormal value exceeding the condition set as the conventional abnormality to detect the change of the aircraft in advance, but the information of the aircraft that usually does not change much. With regard to such things, it is judged whether the current value deviates based on the difference from the data immediately after the flight and the average value within a certain period of time during the flight.

FIG. 2 is a flowchart showing an example of comparison processing with a normal change. In this process, data is acquired for the extracted navigation information, the average for a certain period of time immediately after the flight, and the average value for each fixed time thereafter are updated, and the comparison with the currently acquired navigation information is performed to create a deviation (difference). It is determined whether or not there is a difference of 5% or more), and if there is a difference, it is displayed.

The value of the deviation determination can be set arbitrarily. In addition, the average value of past information (previous flight) will be saved and comparisons will be made so that abnormalities due to aging deterioration can be estimated.

A specific processing flow will be described. The display unit 51 acquires data such as status information and navigation information from the navigation device 10 and the radio 30 (S10), and determines whether or not the flight has just been completed (S12). Specifically, the flight time is measured, and if the flight time is less than 30 minutes, it is determined that the flight has just been completed.

Unless immediately after the flight (N in S12), the display unit 51 compares the average data with the acquired data (S14). The average data is recorded in the storage unit 53.

As a result of the comparison, if there is a discrepancy (Y in S16), the display unit 51 performs the display process described later in FIG. 5 to notify the pilot of the sign of the occurrence of an abnormality (S18). When there is no deviation (N in S16) or after the above display process (S18), the display unit 51 performs an operation to reflect the acquired data in the average value data and stores it in the storage unit 53 (S20). ..

Subsequently, the display unit 51 performs a comparison process with a sudden change (S22). The details will be described later in FIG. 3, but the display unit 51 compares the acquired data with the previous value for the extracted navigation information to see if there is a sudden change (for example, a difference of 20% or more). Judgment is performed and if there is a change, display is performed. The value of the sudden change determination can be set arbitrarily.

Next, the display unit 51 performs a comparison process with the prediction data (S24). Details will be described later in FIG. 4, but the display unit 51 performs comparison processing with the corresponding navigation data range from other navigation information, and data acquisition of the extracted navigation information is predicted from a plurality of other navigation data. Judge whether it is out of the range and display if there is a change. The navigation information for calculating the predicted range can be specified arbitrarily.

On the other hand, in the case immediately after the flight (Y in S12), the display unit 51 compares the average data immediately after the flight with the acquired data (S26). The average data immediately after the flight is recorded in the storage unit 53.

As a result of the comparison, if there is a discrepancy (Y in S28), the display unit 51 performs the display process described later in FIG. 5 to notify the pilot of the sign of the occurrence of an abnormality (S30). When there is no deviation (N in S28), or after the above display process (S30), the display unit 51 performs an operation to reflect the acquired data in the average data immediately after the flight and stores it in the storage unit 53 (S32). ..

Then, after the comparison processing with the prediction data (S24) or the reflection processing in the average data immediately after the flight (S32), the display unit 51 determines whether or not the flight has ended (S34), and the flight ends. For example (Y in S34), the average data and the average data immediately after the flight are recorded in the storage unit 53 (S36), and the process ends. If the flight is not completed (N in S34), the process returns to the data acquisition process (S10).

FIG. 3 is a flowchart showing the details of the comparison process (S22) with the sudden change. In the process, first, the display unit 51 compares the previously acquired data with the current acquired data (S40).

As a result of comparison, when there is a discrepancy (Y in S42), the display process shown in FIG. 5 is performed as a sign of abnormality (S44). After the display processing (S44) or when there is no deviation (N in S42), the acquired data is calculated as the previously acquired data and stored in the storage unit 53 (S46), the processing of the flow is completed, and the data is different from the above-mentioned predicted data. The process proceeds to the comparison process (S24).

FIG. 4 is a flowchart showing the details of the comparison process with the prediction data. In this process, first, the display unit 51 acquires the navigation information used for the prediction range calculation (S50). Which navigation information is to be acquired is predetermined, and here, for example, the navigation information A of the navigation device 10a is used.

Next, the display unit 51 calculates the predicted data range using the navigation information A (S52). When the acquired data is out of the prediction range (N in S54), the display process shown in FIG. 5 is performed as a sign of abnormality (S56). After the display process (S56) or within the predicted range (Y in S54), the process of the flow is terminated and the process proceeds to the above-mentioned flight end determination process (S34) in FIG.

FIG. 5 is a flowchart showing details of the display process (S18, S30 in FIG. 2, S44 in FIG. 3, and S56 in FIG. 4).

In this process, the display unit 51 confirms whether the navigation information associated with the acquired data determined to have a sign of abnormality, that is, the navigation information to be displayed has been displayed (S60). If it has already been displayed (Y in S62), no particular processing is performed here and the process ends. If it is not displayed (N in S62), the display unit 51 compares the priority with the information currently displayed (S64).

FIG. 6 is a table showing the priority of navigation information. For example, the priority 1 is navigation information A (aircraft altitude), and the priority 2 is navigation information B (aircraft speed). The display unit 51 displays the navigation information in the order of priority described in the table (S66). It should be noted that it is sufficient that the order of priority can be clearly recognized by displaying with a number, and the purpose is not necessarily limited to arranging in order of priority.

When a sign of abnormality appears in the acquired data in the processes of FIG. 2, FIG. 3 and FIG. 4 described above, the target item can be displayed in advance by performing such display processing. The pilot can be made aware of this. If there are many extracted items, the display area can be determined and the display priority can be set arbitrarily.

As described above, according to the present embodiment, in the aircraft operation system 1 of the aircraft, the display 50 capable of acquiring and displaying the status from each radio 30 and the navigation device 10 is an aircraft based on the information of the radio 30 and the navigation device 10. It is possible to display that there is an abnormality or change in. In particular, it monitors each navigation information during flight other than the information of the abnormal range output by each device, and predicts when sudden changes, deviations from previous values (average, etc.) occur or from other navigation information. If it does not fall within the data range, the pilot can be notified in a timely manner.

In addition, in the navigation information monitoring of each device, (a) data extraction of deviation (for example, 5%) or more from the previous navigation (conventional flight) or more, and (b) sudden change within a predetermined time (for example). It is possible to output abnormal information based on a predetermined combination according to a combination of (20%) or more data extraction, (c) data extraction of a predetermined or more change of a predetermined navigation information, and the like.

<Second embodiment>
In this embodiment, a test device for automatically measuring the performance of a test device such as the radio device 30 and the navigation device 10 of the first embodiment will be described. Here, in such a test device, even if there is no actual test device, connection cable, measuring device, etc., a pseudo test can be performed with the test device, and a training function that enables learning how to use the test device. Attached test technology (test equipment and test method) Equipment will be described.

In particular, it is a test device that automatically or manually measures the performance of the device under test, has a training function to learn how to replace the module according to the contents set by the instructor, and confirms the process leading to the selection of the replacement module. Can be done.

In the conventional test apparatus, as shown in Japanese Patent Application Laid-Open No. 2008-175681, the practitioner is practicing how to use the test apparatus by operating the test PC in accordance with the instructions of the test PC. The training results were only the saved test results and the contents described in the remarks column, and when I checked them later, I could not know how the test results came about. Therefore, in the embodiment described below, a practical training function that enables confirmation of the process leading to the stored test results is realized.

FIG. 7 is a diagram showing a schematic configuration of the training system 101 of the present embodiment. As shown in the figure, the training system 101 includes a simulated data setting PC 110 and a test PC 120 connected by a network (here, LAN 102). The simulated data setting PC 110 functions as an instructor PC. Further, the test PC 120 functions as a training PC.

The test device 170 is connected to the test PC 120 via the measurement path switcher 150. The measurement path switcher 150 and the test PC 120 are connected by a predetermined connection IF103 such as RS-232C. The general-purpose measuring instrument 180 and the test PC 120 are connected by a predetermined connection IF104 such as GP-IB or RS-232C. The measurement path switcher 150 and the general-purpose measuring instrument 180 are connected so that test signals can be transmitted and received. Similarly, the measurement path switcher 150 and the test device 170 are connected so that test signals can be transmitted and received.

The simulated data setting PC 110 has a mode setting (normal test, simulated test) of the test PC 120, a function of setting a simulated value of the test data, and a function of referring to the test result of the test PC 120.

The test PC 120 holds the test application executably, and at the time of performing the test, is connected to the test device 170 via the measurement path switch 150 to execute a predetermined test.

Further, in the test PC 120, as a test result when the general-purpose measuring device 180 is used in the measurement actually performed in the past, various actual measurement test data of the test result of the actual test device 170 is collected in the terminal. It is stored and stored in the storage device inside. The test PC 120 controls the measurement path switch 150 and the general-purpose measuring device 180. Specifically, the test PC 120 transmits a measurement path switching signal to the measurement path switcher 150, and switches the measurement path so as to input the test signal to the general-purpose measuring device 180 to be used according to the test content. ..

On the other hand, the simulated data setting PC 110 temporarily takes in the measured test data stored in the test PC 120 into the memory contained in the simulated data setting PC 110 via the LAN 102 and stores it. The simulated data setting PC 110 has an operation screen for data editing, and the instructor can edit each measurement item and tailor it to the simulated test data for training.

In addition, in the simulated data setting PC 110, data can be edited by reading the simulated test data file created / registered in the past for training on this terminal and stored / saved in the memory of the terminal. It is possible.

Furthermore, the simulated data setting PC 110 does not use the past data stored and saved in the memories of the test PC 120 and the simulated data setting PC 110, and all items can be created as new simulated test data this time. is there.

The measurement path switch 150 includes a low frequency signal switch 151, a high frequency signal switch 152, and a discrete signal setting unit 153. A measurement path switching signal is output from the test PC 120 to the measurement path switcher 150 according to the test item selected by the test PC 120.

In the measurement path switch 150, the low frequency signal switch 151, the high frequency signal switch 152, and the discrete signal setting unit 153 are used to set the low frequency signal, the high frequency signal connection path, and the discrete signal path setting at the CMOS or TTL level. Is done.

Measuring instrument setting signals are output from the test PC 120 to various general-purpose measuring instruments 180, and measurement conditions such as frequency are set for various general-purpose measuring instruments 180.

After the settings of the measurement path switcher 150 and various general-purpose measuring instruments 180 are completed, the low frequency output from the signal generator of the general-purpose measuring instrument 180 and the low frequency output from the signal generator of the general-purpose measuring instrument 180 with respect to the test device 170 connected to the measurement path switcher 150. A test signal such as high frequency is input, and the performance measurement test is started.

Next, the test device 170 transmits the transmission output or the reception output to the general-purpose measuring device 180 such as a spectrum analyzer via the measurement path switcher 150 in response to the input signal as the test device data. Forward.

The general-purpose measuring instrument 180 assigned as a measurement system for measuring the transmission output or the reception output performs a predetermined measurement, and the output of the measurement result is sent to the test PC 120 as measurement result data (measurement data). Forward.

The test PC 120 that has acquired the measurement data calculates the difference value from the required standard, determines the quality thereof, edits the result into a list of data as the test result, and edits this into a display unit of the test PC 120. It is displayed in and stored in the memory as measurement data. These test results are stored and stored in the memory under date and time management for each data each time the test is performed.

The data stored in the test PC 120 as the actual measurement test data is output according to the transfer request of the LAN-connected simulated data setting PC 110.

Next, simulated data editing in the simulated data setting PC 110, which is one of the characteristic processes in the present embodiment, will be described. FIG. 8 is an example of the simulated data editing screen A1.

On the simulated data editing screen A1, the user selects a desired tab from the power-on test tab A21, the self-diagnosis tab A22, and the function confirmation tab A23 included in the item selection tab A20. Here, the function confirmation tab A23 is selected.

On the screen of the function confirmation tab A23, in the file operation area A30 assigned to various file operations, the desired test simulation data is specified in the test simulation data file selection area A31. Here, "DATA1" is specified.

The detailed data display area A40 is provided with a measurement item area A41, a requirement reference area A42, a measurement value area A43 this time, and a determination area A44.

In the measurement item area A41, a list of measurement items included in the test simulation data is shown. In the requirement reference area A42, the requirement criteria for each of these measurement items are shown. In the measured value area A43 this time, the measured values in the file selected by the test simulation data file selection are shown. In the determination area A44, the quality determination of each measured value is shown.

In the SRA name area A70 at the bottom of the screen, the failure-corresponding modules when the test result is "No" are shown together with the order of their possibilities. Here, the "A3 signal processing unit" is shown as a failure-corresponding module of rank "1".

In the simulated data setting PC 110, data can be edited from the test results measured by the test PC 120 and the simulated test data file created and saved by the simulated data setting PC 110.

By manipulating the desired cell (measured value column) in the measured value area A43 this time, the measured value can be arbitrarily changed. That is, for the setting of the measured value in the simulation, the measured value change screen B1 shown in FIG. 9 is displayed by selecting the measured value column of the arbitrary test item line in the measured value area A43. The measurement value change screen B1 is provided with a request reference value area B11, a measurement value area B12, a change button B13, and a stop button B14.

The measured value can be arbitrarily changed in the measured value area B12, and when the change button B13 is pressed to close the measured value change screen B1, it is automatically determined whether or not the set value satisfies the required standard. , Good or bad is displayed in the judgment area A44, or good and bad are alternately switched each time the judgment area A44 is clicked, and the value of the measured value area B12 can be changed with the default data at the time of good and bad.

In addition, as shown in the SRA name area A70, by displaying the module part that is presumed to be the cause of failure when the test item is defective, the defective part is set in consideration of the test item to be replaced. Is possible.

FIG. 10 shows a simulated data file setting screen C1. Here, a computer name area C11 to be set, an actual machine mode setting area C12, a simulated data file history area C13, a setting button C14, and a cancel button C15 are provided.

The test PC 120 is usually connected to the test device 170, and measurement is performed using a general-purpose measuring device 180 or the like. However, by displaying the simulated data file setting screen C1 using the simulated data setting PC 110 and pressing the setting button 14, the test PC 120 is notified via the LAN 102 that the test is to be performed using the simulated data. , The measurement is performed as a mock test.

FIG. 11 is a flowchart of the measurement process. First, in the measurement process, the simulated data setting PC 110 determines whether or not it is in the simulated mode (S110). Normally (N of S110), the measurement path of the corresponding test item is set by the measurement path switcher 150, the general-purpose measuring instrument 180 is controlled by GP-IB or the like (S112), and the measurement is performed using an existing device. The measured value is acquired (S114).

In the simulated mode (Y in S110), the simulated data setting PC 110 acquires the test result (measured value) of the corresponding test item from the test PC 120 (S116).

Next, the simulated data setting PC 110 determines whether or not the measured value is within the required standard (S118), and if it is within the required standard (Y in S118), determines that it is "good" (S120). If it is out of the required standard (N in S118), it is determined to be "defective" (S122). After the determination, the simulated data setting PC 110 displays the measured value and the pass / fail determination (S124).

In this way, by performing the same processing except for acquiring the measured value from the simulated data, the operator of the test apparatus can perform the same operation as when using the actual machine even in the simulated mode. In addition, the measurement results can be saved in the same manner as the actual machine.

FIG. 12 is an example of the training result reference screen D1. In the simulated data setting PC 110, the measurement result can be referred to via the LAN 102, and the details of the measurement result can be displayed as shown in the training result reference screen D1.

In the conventional training device, the measurement result can be referred to by the simulated data setting PC 110, but it is not possible to confirm what kind of selection is made and the fault module of the test device 170 is identified.

When conducting a test with a test device, the test is performed according to a test program that describes the test procedure. As for the test program, the test program to be executed is decided for each test item, and since the test program is given a line number, if it is possible to save what kind of selection was made in which line of the test program, it will be done later. It becomes possible to confirm from.

Therefore, when the test result is saved in the test PC 120, as shown in FIG. 13, the line number of the test program and the selected contents can be saved together with the test result. The content that can be saved may be not only the selected content but also the key input content and information such as test cancellation. Further, the content that can be saved in one test is not limited to one, and a plurality of contents can be saved.

As shown, in the operation content column, a row of test parameters and their selections are shown. If there are more than one, they are separated by "/". For example, regarding the third measured value from the top, there are two operations, the first operation is "test parameter: 23 lines operation content: YES", and the next operation is "test parameter: 45 lines operation content: YES". ".

On the simulated data setting PC 110, by selecting the test result on the training result reference screen D1 and pressing the "play" button displayed at that time, the same screen as the test PC 120 is displayed and the selected content of the test result is displayed. By reading and playing back the selected screen, it is possible to confirm what kind of selection was made and the faulty module was identified.

FIG. 14 is an example of a selection confirmation screen on the simulated data setting PC 110, and the playback display can be confirmed. Here, it can be seen that the confirmation screen (function confirmation test screen) E1 and the confirmation screen (power lamp lighting confirmation screen) F1 are displayed in this order on the training result reference screen D1, and the display order overlaps.

In this way, even in the absence of the test device 170, it is possible to practice how to operate the test device and how to search for a failure of the test device 170, and it is possible to practice even events that are unlikely to occur in the actual machine. You can learn the operation of.

The present invention has been described above based on the embodiments. This embodiment is an example, and it will be understood by those skilled in the art that various modifications are possible for the combination of each of these components, and that such modifications are also within the scope of the present invention. This application claims the benefit of priority on the basis of Japanese application Japanese Patent Application No. 2017-177480 filed on September 15, 2017, the entire disclosure of which is incorporated herein by reference.

1 Aircraft operation system 10, 10a, 10b, 10c, 10d Navigation device 30, 30a, 30b, 30c, 30d Radio 50 Display 51 Display 52 Control 53 Storage 90 Network 101 Training system 102 LAN103, 104 Connection IF110 Simulation Data setting PC120 Test PC150 Measurement path switcher 151 Low frequency signal switcher 152 High frequency signal switcher 153 Discrete signal setting unit 170 Tested device 180 General-purpose measuring device

The present invention relates to a training system that allows a trainee to learn matters related to operation of a test machine and quality determination .

The present invention uses actual measurement test data including quantified test results for a test machine and simulated data created by an instructor corresponding to the actual measurement test data to determine the quality of the test results. It is a training system that allows trainees to learn about the test machine, and obtains and stores the measured test data by executing the test application, and obtains it from the test computer. A computer for setting simulated data for creating and storing the simulated data obtained by editing the test results in the measured test data is provided, and in the normal mode, the quality determination for the test results in the measured test data is performed. Then, in the simulated mode, the quality determination for the test result in the simulated data is performed.
Further, the test computer includes the setting of the application when the test result is obtained in the actual measurement test data and stores it, and the simulated data setting computer edits the test result in the actual measurement test data. At that time, the setting of the corresponding application is displayed.
Further, the simulated data setting computer displays a candidate module in which an abnormality has occurred in the test machine when the pass / fail judgment corresponding to the test result is negative.
The machine under test is a device related to the operation of an aircraft.

According to the present invention, since it is possible to practice even an event that is unlikely to occur in an actual machine, it is possible to more appropriately notify an abnormality of the device .

Claims (3)

An aircraft operating system equipped with a display device that displays information acquired from radios and navigation systems.
The display device is
A control unit that determines the occurrence of an abnormality in the aircraft based on the information acquired from the radio and the navigation system.
A display unit that displays the judgment result by the control unit and
It has a judgment standard by the control unit and a storage unit for recording the acquired information.
The control unit has other information other than the information of the range of abnormality output by the radio or navigation system, when a sudden change occurs or a deviation from the previous value occurs. An operation system characterized in that when the data does not fall within the data range predicted from the navigation information, the display is controlled to call attention. The control unit extracts data of deviations from the previous navigation by a predetermined range or more, data of abrupt changes within a predetermined time, and data of changes of a predetermined navigation information set in advance by a predetermined range or more. The operation system according to claim 1, wherein abnormal information is output based on a predetermined combination according to the combination of the extracted data, and control is performed so that the information is displayed on the display unit. The first or second aspect of the present invention, wherein the control unit displays in order of priority when there are a plurality of items to be displayed when displaying a display to call attention to the display unit. Operation system.

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