CN114783162B - Alarm voting method for three-redundancy system of airplane - Google Patents
Alarm voting method for three-redundancy system of airplane Download PDFInfo
- Publication number
- CN114783162B CN114783162B CN202210694200.6A CN202210694200A CN114783162B CN 114783162 B CN114783162 B CN 114783162B CN 202210694200 A CN202210694200 A CN 202210694200A CN 114783162 B CN114783162 B CN 114783162B
- Authority
- CN
- China
- Prior art keywords
- signal
- value
- fault
- corresponding channel
- redundancy system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G08—SIGNALLING
- G08B—SIGNALLING OR CALLING SYSTEMS; ORDER TELEGRAPHS; ALARM SYSTEMS
- G08B29/00—Checking or monitoring of signalling or alarm systems; Prevention or correction of operating errors, e.g. preventing unauthorised operation
- G08B29/18—Prevention or correction of operating errors
- G08B29/185—Signal analysis techniques for reducing or preventing false alarms or for enhancing the reliability of the system
- G08B29/188—Data fusion; cooperative systems, e.g. voting among different detectors
-
- G—PHYSICS
- G08—SIGNALLING
- G08B—SIGNALLING OR CALLING SYSTEMS; ORDER TELEGRAPHS; ALARM SYSTEMS
- G08B21/00—Alarms responsive to a single specified undesired or abnormal condition and not otherwise provided for
- G08B21/18—Status alarms
- G08B21/185—Electrical failure alarms
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Engineering & Computer Science (AREA)
- Computer Security & Cryptography (AREA)
- Emergency Alarm Devices (AREA)
- Traffic Control Systems (AREA)
Abstract
The invention provides an alarm voting method for an aircraft three-redundancy system, which comprises the following steps: collecting and obtaining a maximum signal value, a middle signal value and a minimum signal value corresponding to each channel type; comparing the difference between the maximum signal value and the minimum signal value with a corresponding preset threshold value; when the signal is smaller than the threshold value, judging that the three channel signals corresponding to the channel categories are normal, and outputting an intermediate signal value, otherwise, performing the next step; predicting the data of the current sampling period by using a wiener filter, and calculating a predicted signal value of the current sampling period corresponding to the channel type; comparing the difference between the predicted signal value and the maximum signal value, the difference between the predicted signal value and the intermediate signal value and between the predicted signal value and the minimum signal value and the threshold value respectively; and judging that the corresponding channel signal of the corresponding channel type is normal. The invention introduces the signal predicted value, compares the signal of each channel with the signal predicted value respectively to calculate the difference, and then compares the difference with the threshold value, thereby realizing the accurate alarm of the signal fault.
Description
Technical Field
The invention relates to the technical field of civil aviation, in particular to an alarm voting method for an aircraft three-redundancy system.
Background
The aircraft warning system is used as a core system of the whole aircraft, the operating parameters of other systems are monitored in real time, when the monitored parameters of other systems are abnormal, warning information is sent out to prompt a driver of a fault part, a corresponding abnormal processing program is developed, and the aircraft can be ensured to be recovered to a safe flight state.
In order to ensure safety of modern airplanes, various systems mostly adopt a three-redundancy design. Now thatIn the prior art, a fault alarm voting method of an aircraft three-redundancy system mostly adopts a method shown in fig. 1, namely, signal values of three channels corresponding to each channel type in the aircraft three-redundancy system are collected, and the signal values of the three channels of each channel type are correspondingly sorted according to the magnitude to obtain a maximum signal value, a middle signal value and a minimum signal value corresponding to each channel type; separately determining the difference between the maximum signal value and the minimum signal value in each channel class
Difference between maximum signal value and intermediate signal value
Difference between intermediate signal value and minimum signal value
(ii) a Respectively correspond to
、
、
Corresponding to a threshold value preset in the aircraft tri-redundancy system
And (6) carrying out comparison. Comparing the relationship between the difference between the maximum value and the minimum value and a threshold value, wherein when the difference is smaller than the threshold value, the signals of the three channels are normal; if the difference between the maximum signal value and the minimum signal value
Greater than or equal to a threshold value
Then, the maximum signal value and the middle are compared in sequenceDifference between signal values
The difference between the intermediate signal value and the minimum signal value
And a threshold value
And finally determining the state decision fault channel of each redundancy signal.
The conventional signal voting method has the following problems: (1) The method adopts the intermediate value of the current sampling period as a reference value, and judges whether the signal is normal according to the condition whether the intermediate value of the current sampling period is discrete or not, and a quite large false alarm condition exists or a fault condition but a failure in immediate alarm is caused. (2) When the three difference values are all greater than the threshold value, there may be a case where three signals are all faulty or one is normal, two is faulty or two is normal, one is faulty. However, the traditional strategy can only alarm three paths of faults, and cannot accurately compete to distinguish specific situations. Particularly, when only one path of the three-redundancy signals is normal, the traditional strategy cannot effectively distinguish the corresponding normal signal, so that an alarm is triggered, and the attention of a pilot is dispersed. (3) The aircraft system is influenced by the external environment, the transient signal jump phenomenon (namely, when a certain transient fault occurs, the signal is recovered to be normal immediately, and the actual flight safety of the aircraft is not influenced) occurs, but the occurrence of one transient fault is usually accompanied by the update of a logic value corresponding to a certain channel signal in a voting algorithm, so that the output of the voting signal of the aircraft alarm system is influenced, and the aircraft alarm system is easily caused to send false alarm information.
With the development of artificial intelligence technology, based on the consideration of aviation safety and the operation efficiency of airlines, an aircraft triple-redundancy system alarm voting method capable of accurately positioning specific channel signal faults is urgently needed in the market.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides an alarm voting method for an aircraft three-redundancy system. According to the aircraft triple-redundancy system alarm voting method, signals of all the signal channels are compared with accurate signal predicted values respectively to obtain differences in a mode of introducing the signal predicted values, and then the differences are compared with the threshold values preset in the system, so that the problem that false alarms possibly exist in a voting mode of a traditional multi-redundancy system alarm reference current signal intermediate value is solved.
In order to achieve the purpose, the invention provides the following technical scheme: an aircraft three-redundancy system alarm voting method comprises the following steps:
step 1: collecting signal values of three channels corresponding to each channel type in the aircraft three-redundancy system, and correspondingly sequencing the signal values of the three channels of each channel type according to the magnitude to obtain a maximum signal value, a middle signal value and a minimum signal value corresponding to each channel type;
step 2: determining the difference between the maximum signal value and the minimum signal value in each channel class
Will be
Corresponding to a threshold value preset in the aircraft tri-redundancy system
Carrying out comparison; when in use
<
If so, judging that the three channel signals corresponding to the channel types are normal, and outputting an intermediate signal value, otherwise, carrying out the next step;
and step 3: predicting data of the current sampling period by using a wiener filter and calculating a predicted signal value of the current sampling period of the corresponding channel type by using effective signal values in the first n sampling periods of the corresponding channel type, wherein the value of n is more than or equal to three;
separately determining the difference between the predicted signal value and the maximum signal value in each channel class
Difference between predicted signal value and intermediate signal value
Predicting the difference between the signal value and the minimum signal value
；
Respectively correspond to
、
、
Corresponding to a threshold value preset in the aircraft tri-redundancy system
Carrying out comparison; when corresponding to
、
、
Is less than
If so, judging that the corresponding channel signal of the corresponding channel type is normal; otherwise, judging the corresponding channel of the corresponding channel typeAnd outputting a corresponding channel signal fault alarm for signal fault.
In a preferred technical solution, in the step 3, effective signal values in the first 10 sampling periods of the corresponding channel category are used.
In the preferred technical scheme, in the step 3, a minimum mean square error algorithm is adopted to perform iterative computation on the coefficients of the wiener filter, so as to obtain the coefficients of the optimal wiener filter, and calculate the predicted signal value of the current sampling period corresponding to the channel type.
In the preferred technical scheme, before outputting the corresponding channel signal fault alarm in step 3, a false alarm determination step is further provided, which specifically comprises the following steps:
when the corresponding channel of the corresponding channel type is judged to be a signal fault, timing the corresponding channel signal fault by adopting a timer, and when the corresponding channel signal fault duration of the corresponding channel type is less than a preset time value in the aircraft three-redundancy system, judging that the corresponding channel signal is an instantaneous fault, and not outputting a corresponding fault alarm; and when the fault duration time of the corresponding channel signal of the corresponding channel type is greater than or equal to a preset time value in the aircraft three-redundancy system, judging that the corresponding channel signal is a real fault, and outputting a corresponding channel signal fault alarm.
In the preferred technical scheme, before outputting the corresponding channel signal fault alarm in step 3, a false alarm determination step is further provided, which specifically comprises the following steps:
when the corresponding channel of the corresponding channel type is judged to be a signal fault, timing the corresponding channel signal fault by adopting a timer, when the corresponding channel signal fault duration time of the corresponding channel type is greater than or equal to a preset time value in the aircraft three-redundancy system, judging that the corresponding channel signal is a real fault, and outputting a corresponding channel signal fault alarm; when the corresponding channel signal fault duration time of the corresponding channel category is smaller than a preset time value in the airplane three-redundancy system, judging that the corresponding channel signal is an instantaneous fault, performing fault counting on the instantaneous fault of the corresponding channel by using a counter, when the corresponding fault counting is smaller than a preset counting value in the airplane three-redundancy system, not outputting a corresponding fault alarm, and when the corresponding fault counting is larger than or equal to the preset counting value in the airplane three-redundancy system, outputting a corresponding channel signal fault alarm.
In the preferred technical scheme, before outputting the corresponding channel signal fault alarm in step 3, a false alarm determination step is further provided, which specifically comprises the following steps:
when the corresponding channel of the corresponding channel type is judged to be a signal fault, timing the corresponding channel signal fault by adopting a timer, when the corresponding channel signal fault duration time of the corresponding channel type is greater than or equal to a preset time value in the aircraft three-redundancy system, judging that the corresponding channel signal is a real fault, and outputting a corresponding channel signal fault alarm; when the corresponding channel signal fault duration time of the corresponding channel type is smaller than a preset time value in the airplane three-redundancy system, judging that the corresponding channel signal is an instantaneous fault, performing fault counting on the instantaneous fault of the corresponding channel by using a counter, calculating the frequency of the corresponding instantaneous fault, outputting no corresponding fault alarm when the frequency of the corresponding instantaneous fault is smaller than a preset corresponding instantaneous fault frequency value in the airplane three-redundancy system, and outputting a corresponding channel signal fault alarm when the frequency of the corresponding instantaneous fault is greater than or equal to the preset corresponding instantaneous fault frequency value in the airplane three-redundancy system.
Compared with the prior art, the invention has the beneficial effects that:
(1) According to the aircraft triple redundancy system alarm voting method, signals of all paths of signal channels are compared with accurate signal predicted values respectively to obtain differences in a mode of introducing the signal predicted values, and then the differences are compared with the threshold values preset in the system, so that the problem that false alarms possibly exist in a voting mode of referring to the intermediate value of the current signal by the traditional multi-redundancy system alarm is solved; whether the specific channel signals of each channel type are normal or not can be judged quickly and accurately.
(2) The alarm voting method of the invention adopts the function of the timer, allows the fault of a certain channel to last for a certain time, and avoids the problem that the system still triggers unnecessary alarm when the system is recovered to be normal after the signal jumps for a certain moment (actually most of instantaneous faults can not affect the operation of the whole airplane) due to the influence of the external environment in most of the time. The robustness of fault alarm in the voting algorithm is improved, the pilot can concentrate on dealing with the real dangerous fault alarm, and the flight safety is improved.
(3) The alarm voting method also adopts the function of a counter, and through counting and judging instantaneous faults, when the instantaneous faults are accumulated to a certain number of times, particularly when the frequency of the instantaneous faults occurring in a short time is high, even the instantaneous faults caused by the jumping phenomenon trigger a system alarm to remind related personnel to pay attention, so that the flight safety is improved.
(4) Aiming at the specific situation that the traditional redundancy signal voter cannot identify two channel faults and three channel faults when working, voting errors are easily caused, a system outputs error signals or false alarms are caused, a prediction value algorithm is introduced to compare each channel of redundancy signals with prediction values, and when the three-redundancy system has single channel, two-channel and three-channel faults, the fault signals of the specific channels are accurately judged by judging the size of the difference value between each channel signal and the prediction values and the size relation between the difference value and a threshold value.
(5) The phenomenon of instantaneous signal jump can occur when an aircraft system is influenced by an external environment, so that an instantaneous fault can be called to occur, the occurrence of one instantaneous fault is usually accompanied by the update of a corresponding logic value of a certain channel signal in a voting algorithm, the output of the voting signal is influenced, and false warning information is easily caused. In the voting method, functions of a timer and a counter are added, a certain channel is allowed to have a fault for a period of time, the counter can record the frequency of the fault of one channel in a sampling step length, after the frequency exceeds a set upper limit value, a permanent fault is considered to occur, the corresponding channel is isolated, fault information is latched, and alarm information is sent.
Drawings
Fig. 1 is a flow diagram illustrating an aircraft triple redundancy system alarm voting method in the prior art.
Fig. 2 is a schematic flow chart of an aircraft triple redundancy system alarm voting method in embodiment 1.
Fig. 3 is a flow chart of an aircraft triple redundancy system alarm voting method in embodiment 2.
Fig. 4 is a flowchart illustrating an aircraft triple redundancy system alarm voting method according to embodiment 3.
Fig. 5 is a flowchart illustrating an aircraft triple redundancy system alarm voting method according to embodiment 4.
Detailed Description
Embodiment 1, as shown in fig. 2, an aircraft triple redundancy system alarm voting method includes the following steps:
collecting signal values of three channels corresponding to each channel type in the aircraft three-redundancy system, and correspondingly sequencing the signal values of the three channels of each channel type according to the magnitude to obtain a maximum signal value, a middle signal value and a minimum signal value corresponding to each channel type;
determining the difference between the maximum signal value and the minimum signal value in each channel class
Will be
Corresponding to a threshold value preset in the aircraft tri-redundancy system
Carrying out comparison; when in use
<
If so, judging that the three channel signals of the corresponding channel category are normal, voting and outputting an intermediate signal value (namely a mid value), and if not, performing the next step;
predicting the data of the current sampling period by using a wiener filter by using effective signal values in the first 3 sampling periods of the corresponding channel type, and calculating a predicted signal value of the current sampling period of the corresponding channel type; the coefficients of the wiener filter are subjected to iterative computation by using a Least mean square error algorithm (LMS) to obtain the coefficients of the optimal wiener filter, and then the prediction signal value of the current sampling period of the corresponding channel type is computed.
The LMS algorithm is to perform iterative computation on the wiener filter coefficients based on the minimum mean square error criterion between the predicted value and the expected value according to the change of the external environment to obtain the coefficients of the optimal wiener filter, so that the output of the wiener filter reaches the expected response signal. The principle of obtaining the prediction value by using the LMS algorithm is as follows:
is provided with
Representing the expected signal value, namely the known real value of the signal of the three-redundancy system;
representing a reference signal, namely an effective value of a three-redundancy system of last sampling periods;
a set of time-varying values representing the coefficients of the wiener filter;
the output value after passing through the wiener filter is
；
Represents
And
a difference in the signals; will be different value
Feeding into LMS algorithm, LMS adjusts coefficient value of filter continuously so that
The minimum value of (A) is obtained, the best output value, that is, the best predicted value is obtained
. The accuracy of the predicted value of the wiener filter is measured, and the objective and quantitative results are that the mean square error between the predicted value and the expected value is inspected. And if the mean square error is smaller, the predicted value precision is highest. And updating the coefficients of the wiener filter by using the mean square error as feedback. The method comprises the following steps:
(1) Initializing a set of reference signal settings
T represents the transpose of the matrix;
(2) Solving the root mean square error between the predicted value and the expected value:
and n represents the number of time periods, namely the number of sampling periods.
(3) Once updated
To the next generation:
，
the step length is represented, namely the sampling period, and the value is [0,1 ]]。
(4) Repeating the steps (2) and (3) until n time periods are obtained
Minimum value of (2)Is obtained by
Set of optimal coefficient values for wiener filter at minimum
Optimized by means of wiener filters
Will be
Carry in and obtain the best predicted value
. The wiener filter is a classical algorithm and will not be described here.
Separately determining the difference between the predicted signal value and the maximum signal value in each channel class
Difference between predicted signal value and intermediate signal value
Predicting the difference between the signal value and the minimum signal value
；
Respectively correspond to
、
、
Corresponding to a threshold value preset in the aircraft tri-redundancy system
Carrying out comparison; when corresponding to
、
、
Is less than
If so, judging that the corresponding channel signal of the corresponding channel type is normal, and voting to output an intermediate signal value (namely mid value); otherwise, judging the corresponding channel of the corresponding channel type as a signal fault, and outputting a corresponding channel signal fault alarm.
Embodiment 2, as shown in fig. 3, an aircraft triple redundancy system alarm voting method includes the following steps:
collecting signal values of three channels corresponding to each channel type in the aircraft three-redundancy system, and correspondingly sequencing the signal values of the three channels of each channel type according to the magnitude to obtain a maximum signal value, a middle signal value and a minimum signal value corresponding to each channel type;
determining the difference between the maximum signal value and the minimum signal value in each channel class
Will be
Corresponding to a threshold value preset in the aircraft tri-redundancy system
Carrying out comparison; when the temperature is higher than the set temperature
<
If so, judging that the three channel signals of the corresponding channel types are normal, and voting to output an intermediate signal value (namely a mid value); otherwise, carrying out the next step;
predicting the data of the current sampling period by using a wiener filter by using effective signal values in the first 10 sampling periods corresponding to the channel type, and calculating a predicted signal value of the current sampling period corresponding to the channel type; specifically, a Least mean square error algorithm (LMS) is used to perform iterative computation on the coefficients of the wiener filter to obtain the coefficients of the optimal wiener filter, and then the prediction signal value corresponding to the channel type in the current sampling period is computed.
Separately determining the difference between the predicted signal value and the maximum signal value in each channel class
Difference between predicted signal value and intermediate signal value
Predicting the difference between the signal value and the minimum signal value
；
Respectively correspond to
、
、
Corresponding to a threshold value preset in the aircraft tri-redundancy system
Carrying out comparison; when corresponding to
、
、
Is less than
If so, judging that the corresponding channel signal of the corresponding channel type is normal; otherwise, judging the corresponding channel of the corresponding channel type as a signal fault.
Judging false alarms, namely timing the corresponding channel signal faults by adopting a timer when the corresponding channels of the corresponding channel types are judged to be signal faults, judging the corresponding channel signals to be instantaneous faults when the corresponding channel signal fault duration time of the corresponding channel types is less than a preset time value in an airplane three-redundancy system, and not outputting corresponding fault alarms; and when the fault duration time of the corresponding channel signal of the corresponding channel type is greater than or equal to a preset time value in the aircraft three-redundancy system, judging that the corresponding channel signal is a real fault, and outputting a corresponding channel signal fault alarm.
Embodiment 3, as shown in fig. 4, an aircraft triple redundancy system alarm voting method includes the following steps:
collecting signal values of three channels corresponding to each channel type in the aircraft three-redundancy system, and correspondingly sequencing the signal values of the three channels of each channel type according to the magnitude to obtain a maximum signal value, a middle signal value and a minimum signal value corresponding to each channel type;
determining the difference between the maximum signal value and the minimum signal value in each channel class
Will be
Corresponding to a threshold value preset in the aircraft tri-redundancy system
Carrying out comparison; when in use
<
If so, judging that the three channel signals of the corresponding channel types are normal, and voting to output an intermediate signal value (namely a mid value); otherwise, carrying out the next step;
predicting the data of the current sampling period by using a wiener filter by using effective signal values in the first 10 sampling periods corresponding to the channel type, and calculating a predicted signal value of the current sampling period corresponding to the channel type; the coefficients of the wiener filter are subjected to iterative computation by using a Least mean square error algorithm (LMS) to obtain the coefficients of the optimal wiener filter, and then the prediction signal value of the current sampling period of the corresponding channel type is computed.
Separately determining the difference between the predicted signal value and the maximum signal value in each channel class
Difference between predicted signal value and intermediate signal value
Predicting the difference between the signal value and the minimum signal value
；
Respectively correspond to
、
、
With corresponding presets in aircraft tri-redundancy systemsThreshold value
Carrying out comparison; when corresponding to
、
、
Is less than
If so, judging that the corresponding channel signal of the corresponding channel type is normal; otherwise, judging that the corresponding channel of the corresponding channel type is a signal fault.
When the corresponding channel of the corresponding channel type is judged to be a signal fault, a timer is adopted to time the corresponding channel signal fault, when the corresponding channel signal fault duration of the corresponding channel type is greater than or equal to a preset time value in the aircraft three-redundancy system (for example, the preset time value can be 10 sampling periods), the corresponding channel signal is judged to be a real fault, and a corresponding channel signal fault alarm is output. When the fault duration time of the corresponding channel signal corresponding to the channel type is smaller than a preset time value in the airplane three-redundancy system, the corresponding channel signal is judged to be an instantaneous fault, a counter is adopted to count the instantaneous faults of the corresponding channel, when the corresponding fault count is smaller than a preset count value in the airplane three-redundancy system (the preset count value in the embodiment is 10), a corresponding fault alarm is not output, and when the corresponding fault count is larger than or equal to the preset count value in the airplane three-redundancy system, the corresponding channel signal fault alarm is output.
Embodiment 4, as shown in fig. 5, an aircraft triple redundancy system alarm voting method includes the following steps:
collecting signal values of three channels corresponding to each channel type in the aircraft three-redundancy system, and correspondingly sequencing the signal values of the three channels of each channel type according to the magnitude to obtain a maximum signal value, a middle signal value and a minimum signal value corresponding to each channel type;
determining the difference between the maximum signal value and the minimum signal value in each channel class
Will be
Corresponding to a threshold value preset in the aircraft tri-redundancy system
Carrying out comparison; when the temperature is higher than the set temperature
<
If so, judging that the three channel signals of the corresponding channel types are normal, and voting to output an intermediate signal value (namely a mid value); otherwise, carrying out the next step;
predicting the data of the current sampling period by using a wiener filter by using an effective signal value in the previous 10 sampling periods of the corresponding channel type, and calculating a predicted signal value of the current sampling period of the corresponding channel type; the coefficients of the wiener filter are subjected to iterative computation by using a Least mean square error algorithm (LMS) to obtain the coefficients of the optimal wiener filter, and then the prediction signal value of the current sampling period of the corresponding channel type is computed.
Separately determining the difference between the predicted signal value and the maximum signal value in each channel class
Difference between predicted signal value and intermediate signal value
Predicting the difference between the signal value and the minimum signal value
；
Respectively correspond to
、
、
Corresponding to a threshold value preset in the aircraft tri-redundancy system
Carrying out comparison; when corresponding to
、
、
Is less than
If so, judging that the corresponding channel signal of the corresponding channel type is normal; otherwise, judging the corresponding channel of the corresponding channel type as a signal fault.
When the corresponding channel of the corresponding channel type is judged to be a signal fault, timing the corresponding channel signal fault by using a timer, when the corresponding channel signal fault duration of the corresponding channel type is greater than or equal to a preset time value in an aircraft three-redundancy system (for example, the preset time value can be 10 sampling periods), judging that the corresponding channel signal is a real fault, and outputting a corresponding channel signal fault alarm; when the corresponding channel signal fault duration time of the corresponding channel type is smaller than a preset time value in the airplane three-redundancy system, judging that the corresponding channel signal is an instantaneous fault, performing fault counting on the instantaneous fault of the corresponding channel by using a counter, calculating the frequency of the corresponding instantaneous fault, outputting no corresponding fault alarm when the frequency of the corresponding instantaneous fault is smaller than a preset corresponding instantaneous fault frequency value in the airplane three-redundancy system, and outputting a corresponding channel signal fault alarm when the frequency of the corresponding instantaneous fault is greater than or equal to the preset corresponding instantaneous fault frequency value in the airplane three-redundancy system.
The present invention should be considered as limited only by the preferred embodiments of the invention, and not limited to the above embodiments, and it should be understood that any modifications, equivalents and improvements made within the spirit and principle of the invention are included in the scope of the invention.
Claims (5)
1. An aircraft three-redundancy system alarm voting method is characterized in that: which comprises the following steps:
step 1: collecting signal values of three channels corresponding to each channel type in the aircraft three-redundancy system, and correspondingly sequencing the signal values of the three channels of each channel type according to the magnitude to obtain a maximum signal value, a middle signal value and a minimum signal value corresponding to each channel type;
step 2: determining the difference between the maximum signal value and the minimum signal value in each channel class
Will be
Corresponding to a threshold value preset in the aircraft tri-redundancy system
Carrying out comparison; when in use
<
If so, judging that the three channel signals corresponding to the channel types are normal, and outputting an intermediate signal value, otherwise, carrying out the next step;
and 3, step 3: the method comprises the steps that effective signal values in the first n sampling periods of corresponding channel types are adopted, wherein the value of n is 10, a wiener filter is used for predicting data in the current sampling period, and the predicted signal value of the current sampling period of the corresponding channel type is calculated;
separately determining the difference between the predicted signal value and the maximum signal value in each channel class
Difference between predicted signal value and intermediate signal value
Predicting the difference between the signal value and the minimum signal value
；
Respectively correspond to
、
、
Corresponding to a threshold value preset in the aircraft tri-redundancy system
Carrying out comparison; when corresponding to
、
、
Is less than
If so, judging that the corresponding channel signal of the corresponding channel type is normal; otherwise, judging that the corresponding channel of the corresponding channel type is a signal fault, and outputting a corresponding channel signal fault alarm;
the specific process of calculating the predicted signal value of the current sampling period corresponding to the channel type is as follows:
is provided with
Representing the expected signal value, namely the known real value of the signal of the three-redundancy system;
representing a reference signal, namely an effective value of a three-redundancy system of last sampling periods;
a set of time-varying values representing the coefficients of the wiener filter;
the output value after passing through the wiener filter is
；
Represents
And
a difference in the signals; will be different value
Feeding into LMS algorithm, LMS adjusts coefficient value of filter continuously so that
The value of (A) is the smallest, the best output value, that is, the best predicted value, can be obtained
。
2. The aircraft triple redundancy system alarm voting method according to claim 1, wherein: and 3, performing iterative computation on the coefficients of the wiener filter by adopting a minimum mean square error algorithm to obtain the coefficients of the optimal wiener filter, and computing the predicted signal value of the current sampling period corresponding to the channel type.
3. The aircraft triple redundancy system alarm voting method according to claim 2, wherein: before outputting the corresponding channel signal fault alarm in the step 3, a false alarm determination step is further provided, which specifically comprises the following steps:
when the corresponding channel of the corresponding channel type is judged to be a signal fault, a timer is adopted to time the corresponding channel signal fault, when the corresponding channel signal fault duration of the corresponding channel type is less than a preset time value in the aircraft three-redundancy system, the corresponding channel signal is judged to be an instantaneous fault, and a corresponding fault alarm is not output; and when the corresponding channel signal fault duration time of the corresponding channel type is greater than or equal to a preset time value in the aircraft tri-redundancy system, judging that the corresponding channel signal is a real fault, and outputting a corresponding channel signal fault alarm.
4. The aircraft triple redundancy system alarm voting method according to claim 2, wherein: before outputting the corresponding channel signal fault alarm in the step 3, a false alarm determination step is further provided, which specifically comprises the following steps:
when the corresponding channel of the corresponding channel type is judged to be a signal fault, timing the corresponding channel signal fault by adopting a timer, when the corresponding channel signal fault duration time of the corresponding channel type is greater than or equal to a preset time value in the aircraft three-redundancy system, judging that the corresponding channel signal is a real fault, and outputting a corresponding channel signal fault alarm; when the corresponding channel signal fault duration time of the corresponding channel category is smaller than a preset time value in the airplane three-redundancy system, judging that the corresponding channel signal is an instantaneous fault, performing fault counting on the instantaneous fault of the corresponding channel by using a counter, when the corresponding fault counting is smaller than a preset counting value in the airplane three-redundancy system, not outputting a corresponding fault alarm, and when the corresponding fault counting is larger than or equal to the preset counting value in the airplane three-redundancy system, outputting a corresponding channel signal fault alarm.
5. The aircraft triple redundancy system alarm voting method according to claim 2, wherein: before outputting the corresponding channel signal fault alarm in the step 3, a false alarm determination step is further provided, which specifically comprises the following steps:
when the corresponding channel of the corresponding channel type is judged to be a signal fault, timing the corresponding channel signal fault by adopting a timer, when the corresponding channel signal fault duration time of the corresponding channel type is greater than or equal to a preset time value in the aircraft three-redundancy system, judging that the corresponding channel signal is a real fault, and outputting a corresponding channel signal fault alarm; when the corresponding channel signal fault duration time of the corresponding channel type is smaller than a preset time value in the airplane three-redundancy system, judging that the corresponding channel signal is an instantaneous fault, performing fault counting on the instantaneous fault of the corresponding channel by using a counter, calculating the frequency of the corresponding instantaneous fault, outputting no corresponding fault alarm when the frequency of the corresponding instantaneous fault is smaller than a preset corresponding instantaneous fault frequency value in the airplane three-redundancy system, and outputting a corresponding channel signal fault alarm when the frequency of the corresponding instantaneous fault is greater than or equal to the preset corresponding instantaneous fault frequency value in the airplane three-redundancy system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210694200.6A CN114783162B (en) | 2022-06-20 | 2022-06-20 | Alarm voting method for three-redundancy system of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210694200.6A CN114783162B (en) | 2022-06-20 | 2022-06-20 | Alarm voting method for three-redundancy system of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114783162A CN114783162A (en) | 2022-07-22 |
| CN114783162B true CN114783162B (en) | 2022-10-28 |
Family
ID=82420953
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210694200.6A Active CN114783162B (en) | 2022-06-20 | 2022-06-20 | Alarm voting method for three-redundancy system of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114783162B (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4916612A (en) * | 1987-11-02 | 1990-04-10 | The Boeing Company | Dual channel signal selection and fault detection system |
| JPH09312632A (en) * | 1996-05-23 | 1997-12-02 | Hitachi Commun Syst Inc | Fault monitor method and its circuit |
| CN1171180A (en) * | 1994-12-23 | 1998-01-21 | 英国电讯公司 | Fault monitoring |
| CN101236129A (en) * | 2007-01-30 | 2008-08-06 | 伊斯帕诺-絮扎公司 | Aircraft engine monitoring process |
| CN102768531A (en) * | 2012-06-11 | 2012-11-07 | 中国航空工业集团公司第六三一研究所 | Method for improving safety of automatic pilot system (APS) with uniprocessor structure |
| CN103823362A (en) * | 2014-02-17 | 2014-05-28 | 南京航空航天大学 | Arbitration mechanism-based similar dual-redundancy flight control computer and redundancy control method |
| CN105550053A (en) * | 2015-12-09 | 2016-05-04 | 中国航空工业集团公司西安航空计算技术研究所 | Redundancy management method for improving availability of monitoring pair based fault tolerant system |
| CN109635318A (en) * | 2018-11-01 | 2019-04-16 | 南京航空航天大学 | A kind of aero-engine sensor intelligent analytic redundancy design method based on KEOS-ELM algorithm |
| CN112833919A (en) * | 2021-03-25 | 2021-05-25 | 成都纵横自动化技术股份有限公司 | Management method and system for redundant inertial measurement data |
| CN113253157A (en) * | 2021-05-11 | 2021-08-13 | 上海三一重机股份有限公司 | Connector fault detection device and method |
| CN114490142A (en) * | 2021-12-29 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Method and system for monitoring triple-redundancy system |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8230279B2 (en) * | 1999-03-09 | 2012-07-24 | iRoctechnologies | Logic circuit protected against transient disturbances |
| GB2408355B (en) * | 2003-11-18 | 2007-02-14 | Ibm | A system for verifying a state of an environment |
| WO2008040066A1 (en) * | 2006-10-05 | 2008-04-10 | Waratek Pty Limited | Redundant multiple computer architecture |
| CN107807628B (en) * | 2017-10-16 | 2020-04-24 | 南京航空航天大学 | Performance degradation evaluation method for heat exchanger of civil aircraft air conditioning system |
| CN112703457A (en) * | 2018-05-07 | 2021-04-23 | 强力物联网投资组合2016有限公司 | Method and system for data collection, learning and machine signal streaming for analysis and maintenance using industrial internet of things |
-
2022
- 2022-06-20 CN CN202210694200.6A patent/CN114783162B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4916612A (en) * | 1987-11-02 | 1990-04-10 | The Boeing Company | Dual channel signal selection and fault detection system |
| CN1171180A (en) * | 1994-12-23 | 1998-01-21 | 英国电讯公司 | Fault monitoring |
| JPH09312632A (en) * | 1996-05-23 | 1997-12-02 | Hitachi Commun Syst Inc | Fault monitor method and its circuit |
| CN101236129A (en) * | 2007-01-30 | 2008-08-06 | 伊斯帕诺-絮扎公司 | Aircraft engine monitoring process |
| CN102768531A (en) * | 2012-06-11 | 2012-11-07 | 中国航空工业集团公司第六三一研究所 | Method for improving safety of automatic pilot system (APS) with uniprocessor structure |
| CN103823362A (en) * | 2014-02-17 | 2014-05-28 | 南京航空航天大学 | Arbitration mechanism-based similar dual-redundancy flight control computer and redundancy control method |
| CN105550053A (en) * | 2015-12-09 | 2016-05-04 | 中国航空工业集团公司西安航空计算技术研究所 | Redundancy management method for improving availability of monitoring pair based fault tolerant system |
| CN109635318A (en) * | 2018-11-01 | 2019-04-16 | 南京航空航天大学 | A kind of aero-engine sensor intelligent analytic redundancy design method based on KEOS-ELM algorithm |
| CN112833919A (en) * | 2021-03-25 | 2021-05-25 | 成都纵横自动化技术股份有限公司 | Management method and system for redundant inertial measurement data |
| CN113253157A (en) * | 2021-05-11 | 2021-08-13 | 上海三一重机股份有限公司 | Connector fault detection device and method |
| CN114490142A (en) * | 2021-12-29 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Method and system for monitoring triple-redundancy system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114783162A (en) | 2022-07-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1643332B1 (en) | Hybrid model based fault detection and isolation system | |
| CN105700518B (en) | A kind of industrial process method for diagnosing faults | |
| CN103140814B (en) | For detecting the system of the displacement in redundant sensor signal, method and apparatus | |
| Coble et al. | Applying the general path model to estimation of remaining useful life | |
| CN103140812B (en) | For fault detect based on signal processing, isolate and correct system, method and apparatus | |
| EP1416348B1 (en) | Methodology for temporal fault event isolation and identification | |
| JP4922597B2 (en) | Diagnostic method and diagnostic apparatus for fuel cell system | |
| CN110348150B (en) | Fault detection method based on correlation probability model | |
| CN103140813B (en) | For detecting system, the method and apparatus of irregular sensor signal noise | |
| WO1999064962A9 (en) | Neuro-parity pattern recognition system and method | |
| EP3250965B1 (en) | Methods and systems for detecting, classifying and/or mitigating sensor error | |
| CN104678764A (en) | Flight control system sensor hybrid redundancy method based on analytic reconstructed signal | |
| US11549611B2 (en) | Fault prediction in valve systems through Bayesian framework | |
| CN114139274B (en) | Health management system | |
| CN111208802A (en) | Intelligent diagnosis method and system for front-end redundancy of control system, memory and controller | |
| Hale et al. | Design of built-in tests for active fault detection and isolation of discrete faults | |
| CN114783162B (en) | Alarm voting method for three-redundancy system of airplane | |
| US8073587B2 (en) | Diagnostic method for locating a failure in a complex system, and a device for implementing said method | |
| CN113221096A (en) | Method and system for analyzing correlation of random events in chaotic engineering | |
| EP4062506A1 (en) | Machine learning based method and device for disturbance classification in a power trasmission line | |
| CN110362064B (en) | Fault diagnosis method for aero-engine exhaust temperature sensor | |
| CN116384526A (en) | Important parameter fault early warning method and system for nuclear power plant system or equipment | |
| CN112540974B (en) | Spacecraft telemetry data outlier point removing method based on second-order momentum | |
| EP2954580B1 (en) | Limit based threshold estimation for prognostics and health management | |
| US20220223053A1 (en) | Method and system for autonomously tracking distress events on an aircraft in real-time while in flight |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |