CN111332484A - Management system and method for aircraft instrument display data - Google Patents
Management system and method for aircraft instrument display data Download PDFInfo
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Abstract
The invention discloses a management system for aircraft instrument display data, which comprises a sensor conditioning unit, a processor unit, a dynamic comparison module, a display module and a plurality of sensor modules connected with the outside, wherein the sensor conditioning unit is connected with the plurality of outside sensor modules.
Description
Technical Field
The invention belongs to the field of aviation flight, and particularly relates to a management system and a management method for aircraft instrument display data.
Background
In the field of avionics, the reliable sampling of instrument data is determined by comparing data acquired by two or more groups of sensor units with the same or similar functions; such as: these data input into the Primary Flight Display (PFD) come from two or more atmospheric data computing systems, two aircraft transmitter management systems, two or more attitude reference systems. If there is a significant difference in data between systems of the same function, at least one of the systems providing meter data is problematic, in which case the avionic computer cannot rely on the processing of the problematic data-related system data for display; when data inconsistency (exceeding a specified threshold) occurs, an alarm message is given, the pilot inquires other instrument data to evaluate whether suspicious instrument data is reliable, and if the pilot judges that the suspicious instrument data is unreliable, the data source can be removed from a main flight display (PFD).
In the prior art, alarms can be sent to the condition that instrument data are not matched in various modes; for example, the flight attitude indicator is typically displayed on the primary flight display; if the pitch data of the flight attitude changes in x degrees, when the absolute value of the change of x is larger than a set threshold value, displaying a yellow 'PIT' indicator on the primary flight display, wherein the yellow 'PIT' indicator is used for indicating that instrument data of the displayed pitch angle are inconsistent, and if the roll angle data of the flight attitude (another attitude measurement) changes along with y degrees, wherein the absolute value of y is larger than the set threshold value, displaying a yellow 'ROL' indicator on the primary flight display, wherein the yellow 'ROL' indicator is used for indicating that instrument data of the displayed pitch angle are inconsistent; the pitch angle data and roll data of the flight attitude both vary in x and y degrees, where the absolute values of x and y are both greater than respective thresholds, the attitude indicator displays a yellow alert identifier "ATT" indicating that a mismatch between the two sets of instrument data has occurred at the same time.
Disclosure of Invention
The invention aims to provide a management system and a method for aircraft instrument display data.
In order to achieve the purpose, the invention adopts the technical scheme that:
a management system for aircraft instrument display data comprises a sensor conditioning unit, a processor unit, a dynamic comparison module, a display module and a plurality of sensor modules connected with the outside, wherein the signal input end of the sensor conditioning unit is electrically connected with the signal output ends of the plurality of external sensor modules, the signal output end of the sensor conditioning unit is in communication connection with the signal input end of the processor unit so as to receive data collected by a plurality of different external inductive sensors and transmit the data to a flight display system according to a specific data communication protocol, the data is transmitted to the dynamic comparison module through the processor unit in the flight display system, signals processed by the sensor conditioning unit and received by the processor unit interact with the dynamic comparison module, the signal input end of the display module is connected with the signal output end of the processor through the dynamic comparison module, the data output after the comparison of the processor unit is received and converted into electric signals to be transmitted to the display module.
The invention discloses a management system for aircraft instrument display data, wherein a signal input end of a display module is connected with a signal output end of a processor unit so as to receive a sensor signal output by the processor unit, convert the sensor signal into an electric signal and transmit the electric signal to a display.
The invention discloses a management method for aircraft instrument display data, which comprises the following steps:
s1, the sensor conditioning unit receives external information through a plurality of external sensors and inputs the external information into the processor unit and the dynamic comparison module;
s2, the dynamic comparison module calculates the difference between the input data of a plurality of external sensors, compares the input data of two adjacent external sensors according to the difference between the input data of the two adjacent external sensors, and compares the data difference of the previous sensor through the data of the sensor input later;
s3, the dynamic comparison module calculates and obtains the variation of the data received by the sensor along with the time according to the data difference in the sensor;
s4, comparing the corresponding sensor with the difference value generated by the sensor data with the variation generated by the received data over time calculated in the step S2 by a dynamic comparison module; if the absolute value of the calculated difference is larger than the sum of the threshold and the variation generated by the sensor receiving data along with the time, the information of the sensor data inconsistency is transmitted to the processor unit;
otherwise, if the absolute value of the calculated difference is smaller than the sum of the threshold and the variation of the sensor receiving data generated along with the time, the information of the sensor data consistency is transmitted to the processor unit.
The invention discloses a management method for aircraft instrument display data, wherein the threshold obtained in the step S4 comprises two thresholds, one threshold is a constant which is fixed and invariable, the constant threshold is set according to known errors of instrument errors, and the errors do not change along with the change of flight conditions; the second is based on the dynamically changing threshold value calculated in step S2, which dynamically follows the change of flight parameters.
In the method for managing the display data of the aircraft instrument, the difference calculated in the step S4 is further determined by the variation of the measured data of the plurality of sensors.
The invention discloses a management method for aircraft instrument display data, wherein a dynamic comparison module comprises a sensor data acquisition and receiving module, a difference value calculation module, a variation quantity measurement calculation module, a comparison module and an indicator display module, wherein the acquisition and receiving module is connected with a plurality of external sensors and receives input data from the sensors, and comprises a first acquisition channel and a second acquisition channel, wherein the first acquisition channel and the second acquisition channel are respectively in communication connection with the variation quantity measurement calculation module and the difference value calculation module; the variation quantity measuring and calculating module calculates variation quantity generated by sensor receiving data transmitted by the first acquisition channel along with time, and the difference value calculating module receives the difference value of the sensing data input in the second acquisition channel for calculation; the comparison module compares the calculated difference of the data of the plurality of instruments with the sum of the sensor test threshold and the measurement variation; the judgment and indication module finishes the comparison of the difference values, when the calculated difference value exceeds the sum of the measured variable quantity and the threshold value, the judgment and indication module displays the display and sets the flag bit, and the display module is responsible for displaying the indicator information with inconsistent sensor data.
By adopting the technical scheme, the received sensor information is classified by adopting the sensor conditioning module, and the calculated difference values of the data of the plurality of instruments are compared with the sum of the test threshold value of the sensor and the measurement variable quantity by the comparison module; the judgment and indication module finishes difference comparison, the change quantity measurement and calculation module calculates the change quantity of the sensor receiving data transmitted by the first acquisition channel along with time, the difference value calculation module receives the difference value of the sensing data input in the second acquisition channel to calculate, therefore, the calculation result is relatively accurate, when the aircraft gradually ascends or descends, the pitching attitude of the aircraft slightly changes in a long period of time due to the slow change of the altitude, the information acquired by the sensor can be more accurately analyzed through the method, the change of a pilot on the flight dynamic state in the flight process is more facilitated, the system can calculate the proportion of the space-time offset generated by the difference value through the ratio relation between the difference value and the threshold value, therefore, part of the difference value can be filtered out, and accurate sensing information can be obtained.
The invention will be explained in more detail below with reference to the drawings and examples.
Drawings
The contents of the description and the references in the drawings are briefly described as follows:
FIG. 1 is a block diagram of a system module of the present invention;
FIG. 2 is a flow chart of a dynamic comparison module of the present invention;
fig. 3 is a block diagram of a compare message indicator in the present invention.
Detailed Description
The following description of the embodiments of the present invention, with reference to the accompanying drawings, will be made in further detail for the purpose of providing a more complete, accurate and thorough understanding of the inventive concepts and technical solutions of the present invention, including the shapes of the components, the structures, the mutual positions and connection relationships of the components, the functions and operating principles of the components, the manufacturing processes, the operation and use methods, and the like.
FIG. 1 is a block diagram of a system module according to the present invention, which is a management system for aircraft instrument display data as shown in the figure, and the system includes a sensor conditioning unit, a processor unit, a dynamic comparison module, a display module, and a plurality of sensor modules connected to the outside, wherein a signal input end of the sensor conditioning unit is electrically connected to signal output ends of the plurality of external sensor modules, and a signal output end of the sensor conditioning unit is communicatively connected to a signal input end of the processor unit to receive data collected by a plurality of different external sensors and transmit the data to a flight display system according to a specific protocol format, and the data is transmitted to the dynamic comparison module through the processor unit in the flight display system, a signal processed by the sensor conditioning unit received by the processor unit interacts with the dynamic comparison module, a signal input end of the display module is connected to a signal output end of the processor through the dynamic comparison module, the data output after the comparison of the receiving processor unit is converted into electric signals to be transmitted to the display module, the signal input end of the display module is connected with the signal output end of the processor through the dynamic comparison module, and the data output after the comparison of the receiving processor unit is converted into the electric signals to be transmitted to the display module.
The dynamic comparison module disclosed by the scheme is used for dynamically comparing data through the operation of an embedded processor unit and software developed based on C + +.
The precondition for the former to evaluate whether the instrument data is reliable is: the pilot first needs to determine if there is a discrepancy between the data provided by two or more functionally similar systems. If there is a difference, it can then be determined whether the data provided by the instrument is reliable. According to the technical background description above, yellow indicates that there is a condition of data inconsistency, and when the pilot receives the warning information of instrument data inconsistency of the main flight display, the pilot cannot judge which instrument data triggers the condition of alarm inconsistency, that is, the pilot does not know which instrument data cannot be used, and needs to further identify by the pilot. According to the example in the technical background, the operator must know that "PIT" in yellow indicates that there is a case where the instrument data in pitch data is inconsistent, and "ROL" in yellow indicates that there is a case where the instrument data in roll data is inconsistent. In addition, the operator must know that the yellow "ATT" indicator indicates that there is an instrument data inconsistency in both pitch and roll data. Therefore, the pilot can judge whether the instrument data is reliable according to the indication information of the alarm indicator. Typically, an operator may perform such a task: such indicators are identified as a matter of convention, even as a reflection. However, when faced with a large amount of both indicator and meter data being provided on the PFD, the operator may be overwhelmed and unable to effectively identify each indicator. The ability of the operator to obtain a valid indication of the indicator may be further limited when multiple indications are inconsistent. Thus, the operator's ability to react to the error condition may be compromised.
In contrast, in accordance with the principles of the present invention, the inventive design dynamic miscompare module indicates to the pilot that the instrument data is inconsistent in a more deterministic algorithm, easier to understand, and easier to discern than previous designs. The invention provides a method and a device for indicating instrument data. The method according to one embodiment of the invention comprises:
1. the avionic computer is responsible for receiving data of a plurality of instruments;
2. calculating a difference value of the received plurality of instrument data by the avionic computer;
3. calculating the variation of the instrument receiving data along with the time by the avionic computer;
4. the avionic computer will compare the difference between the difference of the plurality of instrument data and the sum of the time-varying amount of received data and a threshold;
5. when the difference between the plurality of instrument data exceeds the sum of the time-varying amount of received data and the threshold, an indicator is displayed on the primary flight display indicating that the instrument data is inconsistent.
FIG. 2 is a flow chart of a dynamic comparison module of the present invention, wherein the system shown in the figure comprises a dynamic miscompare module with inconsistent instrument data according to the present invention, comprising the following steps:
s1, the sensor conditioning unit receives external information through a plurality of external sensors and inputs the external information into the processor unit and the dynamic comparison module;
s2, the dynamic comparison module calculates the difference between the input data of a plurality of external sensors, compares the input data of two adjacent external sensors according to the difference between the input data of the two adjacent external sensors, and compares the data difference of the previous sensor through the data of the sensor input later;
s3, the dynamic comparison module calculates and obtains the variation of the data received by the sensor along with the time according to the data difference in the sensor;
s4, comparing the corresponding sensor with the difference value generated by the sensor data with the variation generated by the received data over time calculated in the step S2 by a dynamic comparison module; if the absolute value of the calculated difference is larger than the sum of the threshold and the variation generated by the sensor receiving data along with the time, the information of the sensor data inconsistency is transmitted to the processor unit;
otherwise, if the absolute value of the calculated difference is smaller than the sum of the threshold and the variation of the sensor receiving data generated along with the time, the information of the sensor data consistency is transmitted to the processor unit.
Fig. 3 is a block diagram of a comparison message indicator according to the present invention, where the dynamic comparison module as shown in the figure includes a sensor data acquisition and reception module, a difference calculation module, a variation amount measurement calculation module, a comparison module, and an indicator display module, the acquisition and reception module is connected to a plurality of external sensors and receives input data from the sensors, and the acquisition and reception module includes a first acquisition Channel (Channel a) and a second acquisition Channel (Channel B), where the first acquisition Channel and the second acquisition Channel are respectively connected to the variation amount measurement calculation module and the difference calculation module in a communication manner; the variation quantity measuring and calculating module calculates variation quantity generated by sensor receiving data transmitted by the first acquisition channel along with time, and the difference value calculating module receives the difference value of the sensing data input in the second acquisition channel for calculation; the comparison module compares the calculated difference of the data of the plurality of instruments with the sum of the test threshold of the sensor and the measurement variation; the judgment indicating module finishes the comparison of the difference values, when the calculated difference value exceeds the sum of the measured variable quantity and the threshold value, the judgment indicating module sets the display flag bit of the message indicator, and the display module is responsible for displaying the indicator information with inconsistent sensor data.
Example one
The method comprises the following steps:
the dynamic comparison module receives data from the sensor. For example, the dynamic comparison module receives first pitch data from a first gyro sensor, second pitch data from a second gyro sensor, and third pitch data from a third gyro sensor. Therefore, the received data of the plurality of meters is composed of the data collected by the three sensors. Besides the pitch data in the flight attitude, the received instrument data also correspond to other flight parameters, such as airspeed, roll data, magnetic heading and barometric altitude, and can be processed by the method and the device.
Step two:
and (3) transmitting the data received in the step 1 to a dynamic comparison module, and calculating the difference value among the data of the instruments by the dynamic comparison module. For example, a difference in the first pitch attitude is calculated based on the first pitch data and the second pitch data. Similarly, a second difference indicative of the pitch attitude is calculated based on the second pitch data and the third pitch data.
Step three:
the dynamic comparison module with inconsistent instrument data calculates the variation of the instrument receiving data generated along with the time.
Step four:
and (3) comparing the difference value of the plurality of instrument data calculated in the step (2) with the variation quantity of the plurality of received instrument data over time measured in the step (3) by the dynamic comparison module with inconsistent instrument data.
If the absolute value of the calculated difference is greater than the sum of the threshold and the amount of change in the instrument received data over time, the message indicator of instrument data inconsistency is indicating a flag bit is set, and if the absolute value of the calculated difference is less than the sum of the threshold and the amount of change in the instrument received data over time, the message indicator of instrument data inconsistency is indicating a flag bit is not set.
The thresholds used in step 4 are divided into two types: one is a constant that is fixed, e.g., the threshold is set based on known errors in instrument error, which do not change as flight conditions change. The second is a dynamically varying threshold value calculated from theory, which varies with one or more flight parameters. For example, the threshold for air pressure altitude data is 50 feet in height below 5000 feet and 150 feet in height above 30000 feet. For heights between 5000 feet and 30000 feet, the threshold varies linearly between 50 feet and 150 feet.
The step 4 result depends not only on the calculated difference of the received plurality of instrument data, but also on the measured variation of the received plurality of instrument data. For example, a dynamic comparison message indicator of roll attitude data may be displayed when the known roll attitude data changes significantly, even though the calculated roll attitude data difference exceeds the roll attitude measurement threshold. Further illustrating this problem;
when the aircraft is flying horizontally (i.e. the pitch attitude of the aircraft does not change with time, i.e. the pitch rate or pitch rate of the aircraft is 0 degrees per second), however, when the aircraft is making a climb maneuver in the upward direction, the pitch attitude of the aircraft changes greatly in a short time, in which case the pitch rate of the aircraft is large, and conversely, when the aircraft is gradually ascending or descending, the pitch attitude of the aircraft changes slightly over a long period of time with a slow change in altitude, and therefore when the aircraft is gradually ascending or descending, the pitch rate of the aircraft is small.
Example two
And whether the absolute difference value of the dynamic comparison module with inconsistent instrument data is greater than 3.0 degrees or not and whether the absolute pitch rate is multiplied by 0.3 second or not. For example, assume that the pitch rate of the aircraft is 30 degrees/second on steep uphill grades and 3 degrees/second on progressive uphill grades. Thus, when the aircraft is climbing a steep slope, the absolute difference in pitch data is greater than 12 degrees, and a dynamic comparison message indicator is displayed. Conversely, when the aircraft is gradually climbing, a dynamic comparison message indicator is displayed when the absolute difference in pitch data is greater than 3.9 degrees. As shown in the above example, when the detection data is largely changed, a large difference in the detection data is acceptable. Conversely, when the amount of change in the detection data is small, a small difference in the detection data is acceptable.
By adopting the technical scheme, the received sensor information is classified by adopting the sensor conditioning module, and the calculated difference values of the data of the plurality of instruments are compared with the sum of the test threshold value of the sensor and the measurement variable quantity by the comparison module; the judgment and indication module finishes difference comparison, the change quantity measurement and calculation module calculates the change quantity of the sensor receiving data transmitted by the first acquisition channel along with time, the difference value calculation module receives the difference value of the sensing data input in the second acquisition channel to calculate, therefore, the calculation result is relatively accurate, when the aircraft gradually ascends or descends, the pitching attitude of the aircraft slightly changes in a long period of time due to the slow change of the altitude, the information acquired by the sensor can be more accurately analyzed through the method, the change of a pilot on the flight dynamic state in the flight process is more facilitated, the system can calculate the proportion of the space-time offset generated by the difference value through the ratio relation between the difference value and the threshold value, therefore, part of the difference value can be filtered out, and accurate sensing information can be obtained.
The invention has been described above with reference to the accompanying drawings, it is obvious that the invention is not limited to the specific implementation in the above-described manner, and it is within the scope of the invention to apply the inventive concept and solution to other applications without substantial modification.
Claims (6)
1. A management system for aircraft instrument display data, characterized by: the system comprises a sensor conditioning unit, a processor unit, a dynamic comparison module, a display module and a plurality of sensor modules connected with the outside, wherein the signal input end of the sensor conditioning unit is electrically connected with the signal output ends of the plurality of outside sensor modules, and the signal output end of the sensor conditioning unit is in communication connection with the signal input end of the processor unit, to receive data collected by a plurality of different externally-sensed sensors and communicate it to the flight display system according to a particular data communication protocol, the signals processed by the sensor conditioning unit and received by the processor unit interact with the dynamic comparison module, the signal input end of the display module is connected with the signal output end of the processor through the dynamic comparison module, the data output after the comparison of the processor unit is received and converted into electric signals to be transmitted to the display module.
2. A management system for aircraft instrument display data according to claim 1, wherein the signal input of the display module is connected to the signal output of the processor unit to receive the sensor signal output by the processor unit and convert it into an electrical signal for transmission to the display.
3. A method for managing aircraft instrumentation display data, comprising a management system for aircraft instrumentation display data according to any one of claims 1 to 2, characterized in that it comprises the following steps:
s1, the sensor conditioning unit receives external information through a plurality of external sensors and inputs the external information into the processor unit and the dynamic comparison module;
s2, the dynamic comparison module calculates the difference between the input data of a plurality of external sensors, compares the input data of two adjacent external sensors according to the difference between the input data of the two adjacent external sensors, and compares the data difference of the previous sensor through the data of the sensor input later;
s3, the dynamic comparison module calculates and obtains the variation of the data received by the sensor along with the time according to the data difference in the sensor;
s4, comparing the corresponding sensor with the difference value generated by the sensor data with the variation generated by the received data over time calculated in the step S2 by a dynamic comparison module; if the absolute value of the calculated difference is larger than the sum of the threshold and the variation generated by the sensor receiving data along with the time, the information of the sensor data inconsistency is transmitted to the processor unit;
otherwise, if the absolute value of the calculated difference is smaller than the sum of the threshold and the variation of the sensor receiving data generated along with the time, the information of the sensor data consistency is transmitted to the processor unit.
4. A method for managing aircraft instrument display data according to claim 3, wherein said threshold values of step S4 include two threshold values, one of which is a constant fixed value and the constant threshold value is set according to known errors of instrument errors that do not vary with flight conditions; the second is based on the dynamically changing threshold value calculated in step S2, which dynamically follows the change of flight parameters.
5. A method for managing aircraft instrument display data according to claim 3, wherein said step of calculating the difference at S4 is further dependent on the amount of change in the plurality of sensor measurement data.
6. The method as claimed in claim 3, wherein the dynamic comparison module comprises a sensor data collecting and receiving module, a difference value calculating module, a variation quantity measuring and calculating module, a comparison module and an indicator display module, the collecting and receiving module is connected with a plurality of external sensors and receives input data from the sensors, the collecting and receiving module comprises a first collecting channel and a second collecting channel, and the first collecting channel and the second collecting channel are respectively connected with the variation quantity measuring and calculating module and the difference value calculating module in a communication mode; the variation quantity measuring and calculating module calculates variation quantity generated by sensor receiving data transmitted by the first acquisition channel along with time, and the difference value calculating module receives the difference value of the sensing data input in the second acquisition channel for calculation; the comparison module compares the calculated difference of the data of the plurality of instruments with the sum of the sensor test threshold and the measurement variation; the judgment indicating module finishes the comparison of the difference values, when the calculated difference value exceeds the sum of the measured variable quantity and the threshold value, the judgment indicating module displays the indicator and sets the flag bit, and the display module is responsible for displaying the indicator information with inconsistent sensor data.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113124916A (en) * | 2021-04-10 | 2021-07-16 | 珠海市岭南大数据研究院 | Converter for industrial traditional pointer instrument |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113124916A (en) * | 2021-04-10 | 2021-07-16 | 珠海市岭南大数据研究院 | Converter for industrial traditional pointer instrument |
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