CN106872172B - Real-time discrimination method and system for monitoring safety parameters of aero-engine test - Google Patents
Real-time discrimination method and system for monitoring safety parameters of aero-engine test Download PDFInfo
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Abstract
The invention relates to a real-time discrimination method and a system for monitoring safety parameters of an aircraft engine test, wherein the method comprises the following steps: establishing a multi-dimensional steady-state rated data table for key parameters related to engine safety; updating the rated value of the safety parameter in the steady-state process in real time by using the steady-state rated data table; on the basis of a steady-state rated data table, determining the safety upper limit and the safety lower limit of each parameter under the corresponding conditions; giving a value rule of an upper limit and a lower limit of a real-time safety parameter in a transition process; carrying out engine test safety judgment of multi-parameter correlation analysis; judging the fault of the test channel with the out-of-limit single-test point; calculating rated values of safety parameters in the transition process in real time; and iteratively updating the two-dimensional rated value data table of the safety parameter in the transition process. The system comprises a steady-state safety parameter table building function module, a transition-state safety parameter table building function module and a real-time monitoring alarm function module. The invention can effectively give an alarm or pre-alarm for the faults of the aero-engine.
Description
Technical Field
The invention relates to the technical field of engine testing, in particular to a real-time judgment method and a real-time judgment system for monitoring safety parameters of an aircraft engine test.
Background
The whole machine test is an important process for developing the engine. There are several classification methods for the whole machine test. The method can be divided into the following stages according to the development stage of the whole machine: principle prototype test, proof machine test, model machine test, and the like. In the test process, the test device comprises a ground examination test, and a high-altitude platform performance debugging and examination test. However, it is extremely difficult to ensure engine safety during testing because of the uncertainties in testing, particularly in principle prototyping, many characteristics of the engine are not fully digitally modelled prior to engine testing, and many of the intensity, stress, transmission, and control problems may not have been fully exposed. However, one principle prototype has huge research and development cost, and once the test is damaged, the loss is also heavy, so that the safety of the tested engine is ensured while various tests are carried out, which is of great significance.
Disclosure of Invention
Aiming at the problems, the invention provides the real-time judgment method and the real-time judgment system for the test safety parameter monitoring of the aero-engine, which have ingenious and reasonable conception, can be used for alarming or pre-alarming the engine fault in the ground or high-altitude simulation test of the engine, further warns the suspected fault section and the fault parameter to the testee, draws the attention of the testee as soon as possible and ensures the safety of the tested engine.
The technical scheme of the invention is as follows:
the real-time discrimination method for monitoring the test safety parameters of the aircraft engine comprises the following specific processes: (1) establishing a multi-dimensional steady-state rated data table for key parameters related to engine safety; (2) updating the rated value of the safety parameter in the steady-state process in real time by a multi-dimensional steady-state rated data table; (3) on the basis of a multi-dimensional steady-state rated data table, determining the safety upper limit and the safety lower limit of each parameter under corresponding conditions; (4) giving a value rule of an upper limit and a lower limit of a real-time safety parameter in a transition process; (5) carrying out engine test safety judgment of multi-parameter correlation analysis; (6) and judging the fault of the test channel with the out-of-limit single-test point.
The real-time judgment method for monitoring the test safety parameters of the aero-engine is characterized in that the engine test safety judgment in the step (5) is specifically as follows: and judging whether the test engine enters an unsafe working state or not in real time according to the given or calculated and determined safety parameter upper limit and lower limit.
The real-time discrimination method for monitoring the test safety parameters of the aero-engine comprises the following steps: and (5) judging the safety of the engine test in the step (5) based on a multi-parameter correlation method, namely, reporting an abnormal section and possible faults immediately when two or more parameters of different types are abnormal or the same type of parameters are all over limited in the same section.
The real-time judgment method for monitoring the safety parameters of the aero-engine test comprises the following steps of (6), specifically, judging the fault of the test channel with the single-test-point overrun: and reporting the fault of the measurement channel of the over-limit measurement point if the value of the measurement point exceeds the limit and the measurement point is in the safety limit and the associated parameter is not abnormal in a plurality of measurement points with the same cross section and the same parameter.
The real-time discrimination method for monitoring the test safety parameters of the aero-engine comprises the following steps: the multi-dimensional steady-state rated data table in the step (1) mainly comprises inlet temperature, inlet pressure, environmental pressure, section parameters and rated rotating speed.
The real-time discrimination method for monitoring the test safety parameters of the aero-engine comprises the following steps: and (4) the value of the step (4) is obtained by calculating the rated value of the safety parameter in the transition process in real time.
A real-time discrimination system for monitoring safety parameters of an aircraft engine test is a real-time discrimination method based on the monitoring of the safety parameters of the aircraft engine test, and comprises a steady-state safety parameter table building function module, a transition-state safety parameter table building function module and a real-time monitoring alarm function module; the steady-state safety parameter table building function module is used for building a parameter value of a key variable which is particularly concerned by a user under a nominal steady-state condition for real-time monitoring and alarm function steady-state safety judgment; the transition state safety parameter table building function module is used for building key parameter values aiming at safety parameters of the transition state operation of the engine and is used for judging the transition state safety of the real-time monitoring alarm function; the real-time monitoring alarm function module is used for testing safety monitoring, real-time distinguishing and alarming for steady-state or transition-state operation in the testing process.
The real-time discrimination system for monitoring the test safety parameters of the aero-engine is characterized in that the operation flow of the steady-state safety parameter table building functional module is as follows: firstly, a table number is given, then the running state parameters of the engine are input, then a section or a unit is given, and finally all monitored parameters on the section and warning upper and lower limits and fault upper and lower limits of corresponding parameters are input.
The real-time discrimination system for monitoring the test safety parameters of the aero-engine is characterized in that the operation flow of the transition state safety parameter table building functional module is as follows: during the first operation, giving the upper and lower warning limits and the upper and lower fault limits of each key operation state parameter from one steady state to another, wherein the upper and lower warning limits or the upper and lower fault limits are percentages related to rated values; in the operation process, if the upper and lower warning limits and the upper and lower fault limits are not reached, or the upper and lower warning limits and the upper and lower fault limits are reached but the safety of the judged parameters is confirmed through keys, the rated values of the judged parameters are continuously updated through iterative calculation.
The real-time judging system for monitoring the test safety parameters of the aero-engine is characterized in that the operation flow of the real-time monitoring alarm function module comprises a real-time monitoring steady-state flow and a real-time monitoring transition-state flow, namely after the real-time judging system enters a real-time monitoring alarm function, the flow is selected firstly, whether the steady-state test real-time monitoring flow is entered or not is judged, if yes, the real-time monitoring steady-state flow is executed, and if not, the real-time monitoring transition-state flow is entered; the real-time monitoring steady-state process is judged by directly comparing the measured value of the steady-state safety parameter with the rated value in the steady-state parameter table; the real-time monitoring transition state process compares the measured value of the transition state safety parameter with the calculated rated value to judge whether the safety is ensured, meanwhile, the calculated rated value is iterated by a given rule, and finally, a rated value data table is formed and is matched by the data table.
The real-time discrimination system for monitoring the test safety parameters of the aero-engine is characterized in that the updating method of the rated values of the safety parameters to be discriminated in the steady-state safety parameter discrimination comprises the following steps: the new rating is the product of the current rating and the genetic factor of the current rating plus 1 minus the product of the difference of this genetic factor and the filtered value of the measured data prior to the current time.
The real-time discrimination system for monitoring the test safety parameters of the aero-engine is characterized in that the updating method of the rated value data table of the compared variable in the transition state flow of the real-time monitoring comprises the following steps: when the measured value of the compared variable is judged to be normal, updating the two-dimensional rated value data table of the compared variable; firstly, calculating a current rated value of a reference variable, wherein the current rated value is smooth filtering of a plurality of measured values before a current measured value; then, the calculated rated value of the compared variable is calculated according to the current rated value of the reference variable, three pairs of data pairs of the reference variable and the compared variable near the current rated value of the reference variable in the two-dimensional rated value data table; finally, the nominal value of the variable to be compared under the condition of the specific reference variable value is calculated by calculating the nominal value, the genetic factor and the original nominal value, and the data table is updated.
The real-time discrimination system for monitoring the test safety parameters of the aero-engine is characterized in that the selection method of the rated value of the compared variable in the transition state safety parameter discrimination comprises the following steps: the current rated value of the compared variable in the transition state is obtained by linear interpolation calculation of the initial value and the final value of the reference variable, the initial value and the final value of the compared variable and the current measured value of the reference variable.
Has the advantages that:
the real-time discrimination method for monitoring the test safety parameters of the aircraft engine has reasonable and ingenious conception, and can automatically discriminate whether the engine is in a safety state or not according to the state of the tested engine and the monitored parameters; meanwhile, the method can be used for monitoring the transition state and the steady state, and the monitored parameters can be various parameters such as gas path parameters, oil path parameters, vibration parameters, stress parameters, surge parameters and the like.
The real-time discrimination system for monitoring the test safety parameters of the aero-engine has simple and reasonable structural design, can be used for various tests of the aero-engine, and particularly can be applied to safety monitoring of early tests in the development of the aero-engine, such as the development stage of a principle prototype; the data obtained in the experimental process also has potential value in health state monitoring after the engine is installed. The rated value of the safety parameter formed in the long-term use process, which is generated by the real-time discrimination system for monitoring the test safety parameter of the aero-engine, can also be used in the related application of the on-condition maintenance of the engine; compared with the pure maximum and minimum value monitoring or the segmented monitoring, the method has obvious advantages.
Drawings
FIG. 1 is a block diagram of a real-time identification system for monitoring safety parameters in an aircraft engine test according to the present invention;
FIG. 2 is a flow chart of the operation of the steady state safety parameter tabulation function module of the real-time discrimination system for aircraft engine test safety parameter monitoring of the present invention;
FIG. 3 is a flow chart of the operation of the transition state safety parameter tabulation function module of the real-time discrimination system for monitoring the test safety parameters of the aero-engine of the present invention;
FIG. 4 is a flow chart of the operation of the real-time monitoring alarm function module of the real-time discrimination system for monitoring the test safety parameters of the aero-engine according to the present invention;
FIG. 5 is a steady-state flow chart of the operation flow of the real-time monitoring alarm function module of the real-time discrimination system for monitoring the test safety parameters of the aero-engine of the present invention;
FIG. 6 is a transition state flow chart of the operation flow of the real-time monitoring alarm function module of the real-time identification system for monitoring the test safety parameters of the aero-engine of the present invention.
Detailed Description
The invention discloses a real-time discrimination method for monitoring safety parameters of an aircraft engine test, which comprises the following specific processes:
s010, establishing a multi-dimensional steady-state rated data table according to key parameters related to engine safety; the multidimensional steady-state rated data table comprises inlet temperature, inlet pressure, environmental pressure, section parameters, rated rotating speed, variables, rated values and the like.
S020, calculating rated values of safety parameters in a transition process in real time according to a certain calculation method by a multi-dimensional steady-state rated data table;
s030, determining the safety upper limit and the safety lower limit of each parameter under the corresponding conditions on the basis of the multidimensional steady-state rated data table;
and S040, providing a value rule of the upper limit and the lower limit of the real-time safety parameter in the transition process, wherein the value is obtained from the rated value of the safety parameter in the transition process through real-time calculation.
S050, engine test safety judgment of multi-parameter correlation analysis, namely judging whether the test engine enters an unsafe working state in real time according to the given or calculated and determined safety parameter upper limit and lower limit; the discrimination is based on a multi-parameter association method, namely, the same section is judged, and when two or more parameters of different types are abnormal or the same type of parameter is completely exceeded, the abnormal section and possible faults are reported immediately.
And S060 judging whether the single-measuring-point overrun test channel has an overrun, namely, if the measuring point value is overrun and the measuring point is in the safety limit and the associated parameter is not abnormal in a plurality of measuring points with the same cross section and the same parameter, reporting the fault of the measurement channel of the overrun measuring point.
The invention relates to a real-time discrimination system for monitoring safety parameters of an aircraft engine test, which is based on the real-time discrimination method for monitoring the safety parameters of the aircraft engine test and is a real-time automatic discrimination system for testing safety, the discrimination is based on a steady-state safety parameter table and a transition-state safety parameter table, and the discriminated parameters can be any parameters which are considered to have close influence on the test safety.
As shown in figure 1, the real-time discrimination system for monitoring the test safety parameters of the aero-engine comprises a steady-state safety parameter table building functional module 1, a transition-state safety parameter table building functional module 2 and a real-time monitoring alarm functional module 3.
The steady-state safety parameter table building function module 1 is used for establishing parameter values of the key variables (such as air compressor inlet pressure, air compressor outlet pressure, combustion chamber inlet temperature, combustion chamber outlet temperature and the like) which are particularly concerned by a user under the condition of a nominal steady state (such as steady running states of slow vehicles, 85% rotating speed, first performance and the like) for the steady-state safety judgment of the real-time monitoring alarm function. Because the test is composed of a plurality of steady-state and a plurality of transition-state processes of the engine, the steady-state safety parameter table building function module 1 and the transition-state safety parameter table building function module 2 can build safety parameter distinguishing standards of different steady-state or different transition states, different steady-state or different transition-state processes are distinguished by different table numbers, and for convenience of identification, different naming methods for the steady-state and transition-state table numbers are considered to show the difference.
As shown in fig. 2, the operation flow of the steady-state safety parameter table building function module 1 is as follows: firstly, a table number is given, then the running state parameters of the engine parameters, such as relative rotating speed, air inlet temperature, air inlet pressure, environmental pressure and the like, are input, then a section is given, and finally all monitored parameters on the section and the warning upper limit and the fault lower limit of the corresponding parameters are input. The upper and lower warning limits are values for alerting the tester of the change when the measured value of the monitored parameter is greater than the upper warning limit or less than the lower warning limit, the tester should pay attention to it. And once the measured value of the monitored parameter is greater than the upper fault limit or less than the lower fault limit, the parameter is judged to reach the fault range.
The function of the transitional state safety parameter table building functional module 2 is to build key parameter values for safety parameters of the transitional state operation of the engine (namely, the process from one stable state to another stable state is the transitional state operation) and to be used for the transitional state safety judgment of the real-time monitoring alarm function.
As shown in fig. 3, the operation flow of the transition state security parameter table building function module 2 is as follows: during the first operation, the upper and lower warning limits and the upper and lower fault limits of each key operation state parameter from one steady state to another are given, and the upper and lower warning limits and the upper and lower fault limits can be derived from calculated values or empirical values. The warning or fault limits are a percentage of the rated value. The initial nominal value is obtained by calculation or is given by a formula. In the actual test process, if the upper and lower warning limits or the upper and lower fault limits are reached, the indication interface displays warning or fault and is matched with sound for alarm. In the operation process, if the upper and lower warning limits and the upper and lower fault limits are not reached, or the upper and lower warning limits and the upper and lower fault limits are reached but the safety of the judged parameter is confirmed by an operator through a key, the rated value of the parameter is continuously updated through iterative calculation. Such iterations may allow the rating of a model or engine to become more and more accurate as the running time accumulates.
The real-time monitoring and alarming function module 3 is used for carrying out test safety monitoring, real-time discrimination, alarming or fault reporting on the aircraft engine running in a steady state or a transition state in the test process.
As shown in fig. 4, the operation flow of the real-time monitoring alarm function module 3 includes a steady-state flow of real-time monitoring and a transition-state flow of real-time monitoring. The operation flow of the real-time monitoring alarm function module 3 is as follows: after the real-time judging system enters a real-time monitoring alarm function, firstly, selecting a sub-process, and judging whether to enter a steady-state test real-time monitoring process; if so, the steady state real time monitoring sub-process shown in FIG. 5 is performed; if not, the transition state real-time monitoring sub-process shown in FIG. 6 is entered. The real-time monitoring steady-state process is judged by directly comparing the measured value of the safety parameter with the given value in the steady-state parameter table; the real-time monitoring transition state flow compares the measured value of the transition state parameter with the calculated rated value to judge whether the process is safe or not; and iterating the calculated rated values by a given rule, and finally forming a rated value data table which is matched by the data table.
As shown in fig. 5, the steady-state process of the real-time monitoring alarm function module 3 specifically includes: after the program enters a steady-state real-time safety monitoring program, firstly, a safety parameter table is read in according to a given safety parameter table number and is used as a basis for real-time judgment. Then, the section number of the engine measurement parameter is read in, and then the current measurement value of the next variable is read in. And then compared with the rated values of the safety parameters stored in the parameter table to judge whether the safety parameters are within the warning limit. If the current engine is within the warning limit, the judged parameter value is normal when the current engine runs in a steady state, the normal recording is carried out, and the execution is continued; if the warning limit is exceeded, it is determined whether the measured value has reached a fault limit. If the fault limit is reached, recording the fault, and then continuing to execute; if the fault limit has not been reached, a warning is recorded and execution continues. And after the judgment of whether the judged parameter is normal or not is finished, storing the measured value and the judgment result in a disk, and then iteratively calculating the rated value of the judged parameter and storing the rated value in the disk.
Rated value x of safety parameter i to be determinedciThe iterative calculation method of (2) is as follows:
xci＝αx'ci+(1-α)mci(1)；
wherein x isci: the current rated value of the judged safety parameter i; x'ciThe method comprises the steps of judging a previous rated value of a safety parameter i, α, judging a genetic factor of the previous rated value of the safety parameter i, wherein the α value of the genetic factor is between 0 and 1, the α value method should consider the tested times of the tested engine, for the engine which just starts to be tested, the α value can be smaller, the α value can be gradually increased along with the increase of the test times, and the m value can be gradually increasedci: filtered values of (n-1) data, m, preceding the current time of the security parameter i being determinedciObtained by calculation of formula (2):
mci＝w1xi,0+w2xi,-1+…+wnxi,-(n-1)(2)；
wherein x isi,0、xi,-1、……、xi,-(n-1)Respectively is the current measured value of the judged safety parameter i, the measured value of the previous time of the current measured value, … … and the measured value of the previous (n-1) time of the current measured value; w is a1、w2、……、wnAre filtered weight vectors that satisfy relation (3):
w1+w2+…+wn＝1 (3)；
next, it is judged whether or not the measured values of all the parameters of the section are subjected to safety judgment. If the parameters are not judged to be safe, returning, continuously reading the current measured value of the next variable, and repeating the process; if all the parameters of the section are judged to be safe, the next step is carried out. The next step is to judge whether the measured values of a plurality of measuring points of more than two types of parameters or a certain type of parameters of the section reach the warning limit or not. If yes, the measured value of the section has safety threat, and an alarm needs to be given or an engine test needs to be stopped; if not, the description is that the measurement of a certain parameter or the sensor is faulty, and the sensor is alarmed to be faulty. After the step is completed, judging whether all the sections are judged, if all the sections are not judged, returning, reading in the next section, and continuing to judge; and if all the sections are judged to be finished, the next step is carried out. Now, it is determined whether there is a key input request to change the test state, that is: a change from steady state testing to transition state testing is required. If the key input exists, transition state real-time monitoring is carried out on the sub-process; if not, whether the test is continued is judged, if the test is confirmed to be continued, the next section is read back, and the judgment is continued. If there is an input button to request no further testing, the process ends.
As shown in fig. 6, the transition state flow of the real-time monitoring alarm function module 3 specifically includes: firstly, reading in a transition state safety parameter table number, and then reading in a current measured value of a reference variable; then judging whether the reference variable exceeds a limit value of a rated initial value and a rated final value or whether the change rate of the reference variable exceeds a limit; the change rate of the reference variable refers to the ratio of the change amount of the reference variable to the change time, and is used for measuring whether the change of the reference variable is too fast (actually, the rotating speed is a common reference variable after the aeroengine enters a slow vehicle state). If yes, reporting a reference variable fault, requesting to stop the test, and waiting for the key to confirm to stop the test; if not, storing the current measured value, change rate and discrimination result of the reference variable. If the key confirms that the test is stopped, the system confirms that the program stops running after the test is stopped; if the key does not confirm the test, the system returns to the flow position for storing the current measured value, the change rate and the judgment result of the reference variable, completes the corresponding action and continues to execute.
Then, the rated initial value and the rated end value of the next variable are read, and then the rated value of the corresponding variable under the current value of the reference variable is searched in the transition state safety parameter table. If the reference variable is initially used, the rated value is given by a formula in a transition state safety parameter table, and the current measured value of the reference variable is substituted into the calculation. Since the nominal values of the stored variables are stored in the form of two-dimensional data tables whose values are always limited, it is tricky to perform the comparison of the measured values with the nominal values and the iterative calculation of the nominal values.
Method for finding a target value for comparison: looking up the table of the measured value of the reference variable in the two-dimensional rated value data table, finding the value of the reference variable in the two-dimensional table, and calculating the rated value of the compared variable by interpolation, namely calculating the rated value x of the compared variable x by using a formula (4)c：
Wherein s ist: a current measured value of a reference variable s; sH、sL: current measured value s of reference variabletTwo values s of a reference variable in a two-dimensional nominal value data sheetHAnd sLS betweenHIs the large value, sLIs the small value; x is the number ofH、xLRespectively, the variable x to be compared corresponds to the reference variable s in the two-dimensional rated value data tableHAnd sLThe lower nominal value.
And calculating values of the warning upper limit and the warning lower limit and the fault upper limit and the fault lower limit according to the rated value of the compared variable and the proportion of the warning upper limit and the warning lower limit and the fault upper limit and the fault lower limit. The measured value of the compared variable is read again, and then the warning limit is judged. If the measured value is within the warning limit, the measured value is normal, the engine is safe, and the record is normal; if the measured value is not within the warning limit, it is determined whether the measured value is within the fault limit. If the measured value is within the fault limit, indicating that the measured value exceeds the warning limit but has not reached the level at which a fault is reported, then recording a warning; if the measured value is not within the fault limit, the measured value is judged to reach the fault reporting degree, and the fault needs to be recorded.
When the measured value of the compared variable is judged to be normal and recorded to be normal, iterative calculation is needed, and the value in the two-dimensional rated value data table is updated. The calculation and the updating are divided into two steps:
in the first step, the current nominal value of the reference variable is calculated. The current measured value of the reference variable is smoothed to find the nominal value of the updated reference variable. Obtaining the current calculated nominal value s of the updated reference variablecThe method comprises the following steps:
sc＝g1s0+g2s-1+…+gns-(n-1)(5)；
wherein s isc: a current calculated nominal value of the reference variable s; s0、s-1、……、s-(n-1): respectively the current measured value of the reference variable s, the first measured value before the current measured value, … …, the (n-1) th measured value before the current measured value. If the number of previously measured values is insufficient, the measured values at the instant of time may be substituted. g1、g2、……、gn: are respectively s0、s-1、……、s-(n-1)And satisfies the following:
g1+g2+…+gn＝1 (6)；
and secondly, updating the rated value of the judged variable. If calculated scS between reference variables s in a two-dimensional reference tableLAnd sHS betweenHIs the large value, sLIs the small value, s'LIs ratio ofLThe smaller value. x'L、xL、xHRespectively, s 'corresponding to the reference variable in the two-dimensional nominal value parameter table'L、sL、sHValue of the compared variable of time, xtIf it is the current measured value, s is updatedLCorresponding target value xL. When updated, is first made of (s'L,x'L)、(sc,xt)、(sH,xH) Three points establish an equation, calculated from equation (7) at the input sLOutput x of timeLt：
Then, a target value x is calculatedLUpdated nominal value x ofLnew：
xLnew＝β·xL+(1-β)·xLt(8)；
Where β is the genetic element of the nominal value, then x is usedLnewReplacing the original xLStored into a two-dimensional rating data table.
The following processing procedures are similar to the corresponding processing procedures in the steady-state monitoring sub-flow, and are not described again.
After all the sections are circularly compared once, a judgment whether the engine is in the transition operation state or not is set, namely whether the operation state of the engine is to be changed from the transition state to the steady state or not is judged.
The real-time discrimination method for monitoring the test safety parameters of the aero-engine has reasonable and ingenious conception, and can be used for monitoring the transition state and the steady state; the monitored parameters can be various parameters such as gas path parameters, oil path parameters, vibration parameters, stress parameters, surge parameters and the like.
The real-time distinguishing system for monitoring the safety parameters of the test of the aero-engine has simple and reasonable structural design, and can automatically distinguish whether the engine is in a safe state or not according to the state of the tested engine and the monitored parameters.
Claims (8)
1. A real-time discrimination method for monitoring safety parameters of an aircraft engine test is characterized by comprising the following specific processes:
(1) establishing a multi-dimensional steady-state rated data table for key parameters related to engine safety;
(2) updating the rated value of the safety parameter in the steady-state process in real time by a multi-dimensional steady-state rated data table; the multi-dimensional steady-state rated data table mainly comprises inlet temperature, inlet pressure, environmental pressure, section parameters and rated rotating speed;
(3) on the basis of a multi-dimensional steady-state rated data table, determining the safety upper limit and the safety lower limit of each parameter under corresponding conditions;
(4) giving a value rule of an upper limit and a lower limit of a real-time safety parameter in a transition process;
(5) carrying out engine test safety judgment of multi-parameter correlation analysis;
(6) judging the fault of the test channel with the out-of-limit single-test point; the judgment of the fault of the test channel with the single-test-point overrun is specifically as follows: and reporting the fault of the measurement channel of the over-limit measurement point if the value of the measurement point exceeds the limit and the measurement point is in the safety limit and the associated parameter is not abnormal in a plurality of measurement points with the same cross section and the same parameter.
2. The method for real-time discrimination of monitoring of safety parameters of an aircraft engine test as claimed in claim 1, wherein the engine test safety discrimination in the step (5) is specifically: and judging whether the test engine enters an unsafe working state or not in real time according to the given or calculated and determined safety parameter upper limit and lower limit.
3. The method for real-time discrimination of the monitoring of the safety parameters of the test of the aircraft engine as claimed in claim 1, characterized in that: and (5) judging the safety of the engine test in the step (5) based on a multi-parameter correlation method, namely, reporting an abnormal section and possible faults immediately when two or more parameters of different types are abnormal or the same type of parameters are all over limited in the same section.
4. The method for real-time discrimination of the monitoring of the safety parameters of the test of the aircraft engine as claimed in claim 1, characterized in that: and (4) the value of the step (4) is obtained by calculating the rated value of the safety parameter in the transition process in real time.
5. A real-time discrimination system for monitoring safety parameters of an aircraft engine test is based on the real-time discrimination method for monitoring the safety parameters of the aircraft engine test of any one of claims 1 to 4, and is characterized in that: the system comprises a steady-state safety parameter table building function module, a transition-state safety parameter table building function module and a real-time monitoring alarm function module;
the steady-state safety parameter table building function module is used for building a parameter value of a key variable which is particularly concerned by a user under a nominal steady-state condition for real-time monitoring and alarm function steady-state safety judgment;
the transition state safety parameter table building function module is used for building key parameter values aiming at safety parameters of the transition state operation of the engine and is used for judging the transition state safety of the real-time monitoring alarm function;
the real-time monitoring alarm function module is used for testing safety monitoring, real-time discrimination and alarm of steady-state or transition-state operation in the testing process;
the operation process of the real-time monitoring alarm function module comprises a real-time monitoring steady-state process and a real-time monitoring transition-state process, namely, after the real-time judging system enters the real-time monitoring alarm function, the process is selected firstly to judge whether to enter the steady-state test real-time monitoring process, if so, the real-time monitoring steady-state process is executed, and if not, the real-time monitoring transition-state process is entered;
the real-time monitoring steady-state process is judged by directly comparing the measured value of the steady-state safety parameter with the rated value in the steady-state parameter table; the real-time monitoring transition state flow compares the measured value of the transition state safety parameter with the calculated rated value to judge whether the safety is ensured, meanwhile, the calculated rated value is iterated by a given rule, and finally, a rated value data table is formed and is matched by the data table;
the updating method of the rated value data table of the compared variable in the real-time monitoring transition state process comprises the following steps: when the measured value of the compared variable is judged to be normal, updating the two-dimensional rated value data table of the compared variable; firstly, calculating a current rated value of a reference variable, wherein the current rated value is smooth filtering of a plurality of measured values before a current measured value; then, the calculated rated value of the compared variable is calculated according to the current rated value of the reference variable, three pairs of data pairs of the reference variable and the compared variable near the current rated value of the reference variable in the two-dimensional rated value data table; finally, calculating the rated value of the compared variable under the condition of the specific reference variable value by calculating the rated value, the genetic factor and the original rated value, and updating the data table;
the selection method of the rated value of the compared variable in the transition state safety parameter judgment comprises the following steps: the current rated value of the compared variable in the transition state is obtained by linear interpolation calculation of the initial value and the final value of the reference variable, the initial value and the final value of the compared variable and the current measured value of the reference variable.
6. The system of claim 5, wherein the steady state safety parameter tabulation function module is operated by the following steps: firstly, a table number is given, then the running state parameters of the engine are input, then a section or a unit is given, and finally all monitored parameters on the section and warning upper and lower limits and fault upper and lower limits of corresponding parameters are input.
7. The system for real-time discrimination of aircraft engine test safety parameter monitoring of claim 5, wherein the operational flow of the transition state safety parameter tabulation function module is: during the first operation, giving the upper and lower warning limits and the upper and lower fault limits of each key operation state parameter from one steady state to another, wherein the upper and lower warning limits or the upper and lower fault limits are percentages related to rated values; in the operation process, if the upper and lower warning limits and the upper and lower fault limits are not reached, or the upper and lower warning limits and the upper and lower fault limits are reached but the safety of the judged parameters is confirmed through keys, the rated values of the judged parameters are continuously updated through iterative calculation.
8. The system of claim 5, wherein the updating method of the rated value of the safety parameter to be judged in the steady-state safety parameter judgment is as follows: the new rating is the product of the current rating and the genetic factor of the current rating plus 1 minus the product of the difference of this genetic factor and the filtered value of the measured data prior to the current time.
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