CN117933709A - Conversion risk assessment method for test mode of aviation turboshaft engine - Google Patents
Conversion risk assessment method for test mode of aviation turboshaft engine Download PDFInfo
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Abstract
The invention relates to the technical field of conversion of a test mode of an aviation turbine shaft engine, and discloses a conversion risk assessment method of the test mode of the aviation turbine shaft engine, which comprises the following steps: evaluating the risk of the testing process according to a first preset evaluating method, and calculating to obtain a risk index of the testing process; evaluating early risk of the outfield according to a second preset evaluation method, and calculating to obtain early risk indexes of the outfield; according to the risk index of the testing process and the early risk index of the external field, carrying out testing mode conversion risk, and calculating to obtain a testing mode conversion risk index; according to the test mode conversion risk index, the sampling proportion is determined, the risk of the test mode conversion of the aviation turbine shaft engine can be evaluated, whether the risk of the two-in-one test conversion is controllable or not is indicated, and whether the conversion of the test mode of the aviation turbine shaft engine is carried out or not is conveniently judged.
Description
Technical Field
The invention relates to the technical field of conversion of a test mode of an aviation turbine shaft engine, in particular to a conversion risk assessment method of the test mode of the aviation turbine shaft engine.
Background
With the increase of the number of in-service aviation turbine shaft engines, the reliability level is continuously improved, and the cost is reduced as a future development trend, so that the cost can be greatly reduced by converting the test mode of the aviation turbine shaft engine from two-package two-test to one-package one-test; however, the risk of the test mode of the aero-turbine shaft engine being converted from two-to-one test to one test cannot be determined, and the conversion of the test mode of the aero-turbine shaft engine is seriously affected.
Disclosure of Invention
In view of the above, the invention provides a conversion risk assessment method for a test mode of an aero-turbine shaft engine, which aims to solve the problem that the conversion risk of the test mode of the aero-turbine shaft engine from two-to-one test to one-to-one test cannot be determined, and the conversion of the test mode of the aero-turbine shaft engine is seriously influenced.
The invention provides a conversion risk assessment method of a test mode of an aviation turboshaft engine, which comprises the following steps of: evaluating the risk of the testing process according to a first preset evaluating method, and calculating to obtain a risk index of the testing process; evaluating early risk of the outfield according to a second preset evaluation method, and calculating to obtain early risk indexes of the outfield; according to the risk index of the testing process and the early risk index of the external field, carrying out testing mode conversion risk, and calculating to obtain a testing mode conversion risk index; and determining the sampling proportion according to the test mode conversion risk index.
The beneficial effects are that: the method has the advantages that the risk index of the test mode conversion is calculated through the risk index of the test process and the early-stage risk index of the external field, sampling is carried out according to the risk index of the test mode conversion, the proportion of the test mode of the aviation turbine shaft engine converted from two-to-one test to one-to-one test is determined, the risk of the test mode of the aviation turbine shaft engine converted from two-to-two test to one-to-one test is assessed, the risk of the test mode conversion of the aviation turbine shaft engine can be estimated, whether the risk of the two-to-two test conversion into one test is controllable or not is indicated, and whether the conversion of the test mode of the aviation turbine shaft engine is carried out or not is judged conveniently.
In an alternative embodiment, the first preset assessment method comprises the steps of: collecting problem data information; screening problem data and determining a first risk item; determining a severity level for each first risk item; determining the occurrence probability level of each first risk item outfield; according to the severity level of each first risk item and the occurrence probability level of each first risk item in the external field, calculating to obtain a risk index of each first risk item; and calculating to obtain the risk index of the testing process according to the risk index of each first risk item and the occurrence probability level of the external field of each first risk item.
The beneficial effects are that: the risk index of each first risk item is obtained through calculation through the severity level of each first risk item and the occurrence probability level of each first risk item in the external field, and the risk size of each first risk item can be quantitatively determined; according to the risk index of each first risk item and the occurrence probability level of the external field of each first risk item, calculating to obtain the risk index of the test process, and quantitatively determining the total risk of the initial decomposition problem in the test process of the aviation turboshaft engine.
In an alternative embodiment, said determining the severity level of each first risk item includes: judging whether the severity level of the first risk item is greater than or equal to 9, if so, stopping evaluation, and rectifying the first risk item; if not, continuing to determine the occurrence probability level of each first risk item.
The beneficial effects are that: the severity of each first risk item is quantitatively determined by determining the severity level of each first risk item, whether the next step is continued is judged by judging whether the severity level of the first risk item is greater than or equal to 9, and when the severity level of the first risk item is greater than or equal to 9, the assessment is stopped in time, so that time can be effectively saved, and the efficiency of conversion risk assessment of the test mode of the aero-turbine shaft engine can be improved.
In an alternative embodiment, the second preset assessment method comprises the steps of: collecting fault data information; screening fault data and determining a second risk item; determining a severity level for each second risk item; determining the occurrence probability level of each second risk item; according to the severity level of each second risk item and the occurrence probability level of each second risk item, calculating to obtain a risk index of each second risk item; and calculating to obtain the early-stage risk index of the outfield according to the risk index of each second risk item and the occurrence probability level of each second risk item.
The beneficial effects are that: the risk index of each second risk item is obtained through calculation through the severity level of each second risk item and the occurrence probability level of each second risk item, and the risk size of each second risk item can be quantitatively determined; and calculating to obtain an early-stage risk index of the outfield according to the risk index of each second risk item and the occurrence probability level of each second risk item, and quantitatively determining the total risk of early-stage faults of the outfield.
In an alternative embodiment, the algorithm formula of the risk indicator of each first risk item is:
R1i＝S1i×P1i
wherein: s 1i is the severity level of the ith first risk item;
p 1i is the i first risk item outfield occurrence probability level;
R 1i is the risk index of the ith first risk item.
The beneficial effects are that: through the algorithm formula of the risk index of each first risk item, the calculation of the risk index of each first risk item can be rapidly and accurately completed, and the conversion risk assessment efficiency of the test mode of the aviation turbine shaft engine is improved.
In an alternative embodiment, the algorithm formula of the test procedure risk indicator is:
Wherein R 1i is a risk index of the ith first risk item;
p 1i is the i first risk item outfield occurrence probability level;
R 1 is a risk index of the testing process.
The beneficial effects are that: the calculation of the risk index in the test process can be rapidly and accurately completed through the algorithm formula of the risk index in the test process, and the conversion risk assessment efficiency of the test mode of the aviation turbine shaft engine is improved.
In an alternative embodiment, the algorithm formula of the risk indicator of each of the second risk items is:
R2j＝S2j×P2j
Wherein: s 2j is the severity level of the j-th second risk item;
p 2j is the probability level of occurrence of the j-th second risk item;
R 2j is the risk index of the j second risk item.
The beneficial effects are that: through the algorithm formula of the risk index of each second risk item, the calculation of the risk index of each second risk item can be rapidly and accurately completed, and the conversion risk assessment efficiency of the test mode of the aviation turbine shaft engine is improved.
In an alternative embodiment, the algorithm formula of the outfield early risk index is:
Wherein: r 2j is a risk indicator of the j-th second risk item;
p 2j is the probability level of occurrence of the j-th second risk item;
R 2 is an early risk index of the outfield.
The beneficial effects are that: the calculation of the early risk index of the external field can be rapidly and accurately completed through an algorithm formula of the early risk index of the external field, and the conversion risk assessment efficiency of the test mode of the aviation turboshaft engine is improved.
In an alternative embodiment, the algorithm formula for the test mode conversion risk indicator is:
R＝a×R1+b×R2
Wherein: r 1 is a risk index in the testing process;
r 2 is an early risk index of the outfield;
a represents the duty ratio of the problem found after initial decomposition in two-pack two-test conversion into one-pack one-test;
b represents the duty ratio of the early failure of the external field converted into one-to-one test in two-to-two tests;
wherein 0.ltoreq.a, b.ltoreq.100%, and a+b=1.
The beneficial effects are that: the calculation of the test mode conversion risk index can be rapidly and accurately completed through an algorithm formula of the test mode conversion risk index, and the efficiency of conversion risk assessment of the test mode of the aviation turboshaft engine is improved.
In an alternative embodiment, the algorithm formula for converting the problem found after the initial decomposition into the duty ratio of one test to one test in two tests is as follows:
The algorithm formula of the external field early fault conversion into the duty ratio of one test in two tests is as follows:
wherein,
The beneficial effects are that: the calculation of the duty ratio of the problems found after the initial decomposition in the two-pack two-test conversion to one-pack one-test can be rapidly and accurately completed through an algorithm formula of the duty ratio of the problems found after the initial decomposition in the two-pack two-test conversion to one-pack one-test; the calculation of the duty ratio of the external field early fault converted into one-package-one-test in two-package two-test can be rapidly and accurately completed through the algorithm formula of the duty ratio of the external field early fault converted into one-package-one-test in two-package two-test, and the conversion risk assessment efficiency of the test mode of the aviation turbine shaft engine is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the related art, the drawings that are required to be used in the description of the embodiments or the related art will be briefly described, and it is apparent that the drawings in the description below are some embodiments of the present invention, and other drawings may be obtained according to the drawings without inventive effort for those skilled in the art.
FIG. 1 is a flow chart of a method for risk assessment of conversion in a test mode of an aero-turboshaft engine in accordance with an embodiment of the present invention;
FIG. 2 is a schematic flow chart of a two-pack two-test of an aero-turboshaft engine according to an embodiment of the present invention;
FIG. 3 is a schematic flow chart of a test-on-test of an aero-turboshaft engine according to an embodiment of the present invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The two-mounting and two-testing test mode of the aviation turbine shaft engine comprises the following steps: assembling an aviation turboshaft engine; performing preliminary operation test run of the aviation turboshaft engine; performing decomposition inspection; judging whether the replacement of the components is caused by the operation; if yes, assembling the aviation turboshaft engine; additional operations are performed as required; if not, assembling the aviation turboshaft engine again; performing final operation test run; and (5) performing function inspection on the aviation turbine shaft engine in a complete machine state, and finally ending and testing. The test mode of the aero turbine shaft engine in one test comprises the following steps: assembling an aviation turboshaft engine; performing operation test on the aviation turboshaft engine; checking the whole machine in situ; judging whether the replacement of the components is caused by the operation; if yes, assembling the aviation turboshaft engine; additional operations are performed as required; if not, the test is ended.
Embodiments of the present invention are described below with reference to fig. 1 to 3.
According to an embodiment of the invention, there is provided a conversion risk assessment method of a test mode of an aero-turbine shaft engine, comprising the steps of:
s1, evaluating the risk of the testing process according to a first preset evaluation method, and calculating to obtain a risk index of the testing process;
s2, evaluating early risk of the outfield according to a second preset evaluation method, and calculating to obtain early risk indexes of the outfield;
s3, carrying out test mode conversion risk according to the test process risk index and the outfield early risk index, and calculating to obtain a test mode conversion risk index;
s4, determining the sampling proportion according to the test mode conversion risk index.
The method has the advantages that the risk index of the test mode conversion is calculated through the risk index of the test process and the early-stage risk index of the external field, sampling is carried out according to the risk index of the test mode conversion, the proportion of the test mode of the aviation turbine shaft engine converted from two-to-one test to one-to-one test is determined, the risk of the test mode of the aviation turbine shaft engine converted from two-to-two test to one-to-one test is assessed, the risk of the test mode conversion of the aviation turbine shaft engine can be estimated, whether the risk of the two-to-two test conversion into one test is controllable or not is indicated, and whether the conversion of the test mode of the aviation turbine shaft engine is carried out or not is judged conveniently.
In one embodiment, the first preset assessment method comprises the following steps: collecting problem data information; screening problem data and determining a first risk item; determining a severity level for each first risk item; determining the occurrence probability level of each first risk item outfield; according to the severity level of each first risk item and the occurrence probability level of each first risk item in the external field, calculating to obtain a risk index of each first risk item; and calculating to obtain the risk index of the testing process according to the risk index of each first risk item and the occurrence probability level of the external field of each first risk item.
The risk index of each first risk item is obtained through calculation through the severity level of each first risk item and the occurrence probability level of each first risk item in the external field, and the risk size of each first risk item can be quantitatively determined; according to the risk index of each first risk item and the occurrence probability level of the external field of each first risk item, calculating to obtain the risk index of the test process, and quantitatively determining the total risk of the initial decomposition problem in the test process of the aviation turboshaft engine.
TABLE 1 Risk index evaluation Table for test procedure
In a specific embodiment, according to the two-pack two-test step of the aviation turbine shaft engine of fig. 2 and the one-pack one-test step of the aviation turbine shaft engine of fig. 3, analysis results that the two-pack two-test is different from the one-pack one-test mainly in that the two-pack two-test is added with a decomposition check step after preliminary operation than the one-pack one-test, and the problem found by the decomposition after the preliminary operation may not be found in the one-pack one-test. Therefore, a problem that can be found only by the preliminary post-operation decomposition inspection is taken as a problem term. And collecting data information of problems found by decomposing the aviation turbine shaft engine after the initial operation.
Table 2 table for collecting data of problems found by decomposing after initial operation of aero turboshaft engine
Specifically, the technical state of the aero turbine shaft engine in the table 2, which can be checked and found only after the initial operation of the aero turbine shaft engine, includes a new machine (first delivery), a first repair machine (first repair), a second repair machine (second repair), before comprehensive repair and after comprehensive repair.
In a specific embodiment, the problems found by screening out the satisfactory aviation turbine shaft engine after initial operation can be checked by decomposing the satisfactory aviation turbine shaft engine, and the problems are filled into three columns of a first risk item serial number, a first risk item part and a first risk item problem in table 1 as a first risk item.
Specifically, the data screening principle of the problem data is as follows: deleting secondary damage data caused by other parts; deleting damage data caused by the decomposition of the aviation turboshaft engine, such as loosening of a steel wire thread sleeve and the like; deleting damage data caused by non-use, such as part damage; deleting original material defect data of the part irrelevant to the conversion of the test mode; deleting the zeroed problem; deleting LRU (line replaceable unit) problems in the outfield data; deleting the problems caused by foreign object injury, foreign objects and other non-aviation turbine shaft engines in the early problems; deleting the problem items which can be detected by the inspection under the state of the whole machine in the external field; deleting the problem items which are not related to the conversion of the test modes, namely, the problem items which can be found by both the two-test-in-two test mode and the one-test-in-one test mode or can not be found by both the two-test-in-one test mode; and combining scraping damage data between the two parts, and calculating a fault.
In particular, severity ratings are used to assess the severity of potential problems or potential faults. The severity grade was classified into four grades I, II, III, IV, and the quantitative grade was classified into 1 to 10 grades, with the greater the score, the greater the severity.
Table 3 rating criteria for severity level
Specifically, the severity level of each first risk item is determined according to the scoring criteria of the severity level of Table 3.
Specifically, the probability of occurrence level is used to assess the likelihood that the risk actually occurs. The probability of occurrence level may be determined according to the occurrence frequency, and the quantitative probability of occurrence level may be classified into 1 to 10 levels, with the probability of occurrence being higher as the score is greater.
Table 4 scoring criteria for probability of occurrence level
In a specific embodiment, for each first risk item in table 1, a probability level of occurrence of the problem in the test is determined according to the scoring criteria of probability level of occurrence of table 4.
Preferably, in the case where the in-plant test detection means is different from the external field detection means, if the in-plant test detection means is different from the external field detection means, a problem such as hole detection or the like cannot be detected in the in-plant test, but can be detected in the external field, and further occurrence of the problem such as hole detection or the like as a failure can be avoided. In this case, the probability level of occurrence of the external field is low, so that the probability level of occurrence of the first risk item needs to be further reduced by one step from the probability level of occurrence in the in-factory test, considering whether the external field has a detection means to avoid the problem from being corrupted to a fault, and when the external field has a detection means to avoid the problem of hole detection or the like from occurring to a fault.
Specifically, if the problem of the detection means for external field is worsened, the "yes/no" is filled out for "if the problem of the detection means for external field is worsened" for the fault (yes/no) "in table 1; the absence of detection means in the outfield avoids the problem deterioration: the "no if there is a detection means for the presence or absence of the external field" of table 1 avoids the problem from deteriorating to a failure (yes/no) "is filled in.
In one embodiment, the determining the severity level for each first risk item includes: judging whether the severity level of the first risk item is greater than or equal to 9, if so, stopping evaluation, and rectifying the first risk item; if not, continuing to determine the occurrence probability level of each first risk item.
The severity of each first risk item is quantitatively determined by determining the severity level of each first risk item, whether the next step is continued is judged by judging whether the severity level of the first risk item is greater than or equal to 9, and when the severity level of the first risk item is greater than or equal to 9, the assessment is stopped in time, so that time can be effectively saved, and the efficiency of conversion risk assessment of the test mode of the aero-turbine shaft engine can be improved.
Specifically, when the severity level of the first risk item is greater than or equal to 9, the aviation turbine shaft engine keeps a two-pack two-test mode, quality improvement related to the severity level reduction of the first risk item is carried out, after the quality improvement, the risk of the test process is assessed again according to a first preset assessment method, and a risk index of the test process is calculated.
In one embodiment, the second preset assessment method comprises the steps of: collecting fault data information; screening fault data and determining a second risk item; determining a severity level for each second risk item; determining the occurrence probability level of each second risk item; according to the severity level of each second risk item and the occurrence probability level of each second risk item, calculating to obtain a risk index of each second risk item; and calculating to obtain the early-stage risk index of the outfield according to the risk index of each second risk item and the occurrence probability level of each second risk item.
The risk index of each second risk item is obtained through calculation through the severity level of each second risk item and the occurrence probability level of each second risk item, and the risk size of each second risk item can be quantitatively determined; and calculating to obtain an early-stage risk index of the outfield according to the risk index of each second risk item and the occurrence probability level of each second risk item, and quantitatively determining the total risk of early-stage faults of the outfield.
TABLE 5 early outfield risk index assessment Table
Specifically, fault data information of the outer field used for T hours after the delivery of the aero turboshaft engine is collected. The T hours of the external field use are determined by combining the test mode and the delivery test vehicle requirements of the aviation turbine shaft engine, and the longest delivery test vehicle of the aviation turbine shaft engine at present is 20 hours, 30 hours and the like.
Table 6 table for collecting fault data within T hours of outfield use of aero turboshaft engine
In a specific embodiment, screening out faults caused by the aero turbine shaft engine in the early use time T of the aero turbine shaft engine in the outer field according to a data screening principle, and filling the faults as a second risk item into three columns of a second risk item serial number, a second risk item part and a second risk item fault profile in the table 5; determining a severity level for each second risk item according to the scoring criteria of the severity level of table 3; the probability of occurrence level of each second risk item is determined according to the scoring criteria of the probability of occurrence level of table 4.
In one embodiment, the algorithm formula of the risk indicator of each first risk item is:
R1i＝S1i×P1i
wherein: s 1i is the severity level of the ith first risk item;
p 1i is the i first risk item outfield occurrence probability level;
R 1i is the risk index of the ith first risk item.
Through the algorithm formula of the risk index of each first risk item, the calculation of the risk index of each first risk item can be rapidly and accurately completed, and the conversion risk assessment efficiency of the test mode of the aviation turbine shaft engine is improved.
In one embodiment, the algorithm formula of the test procedure risk indicator is:
Wherein R 1i is a risk index of the ith first risk item;
p 1i is the i first risk item outfield occurrence probability level;
R 1 is a risk index of the testing process.
The calculation of the risk index in the test process can be rapidly and accurately completed through the algorithm formula of the risk index in the test process, and the conversion risk assessment efficiency of the test mode of the aviation turbine shaft engine is improved.
Specifically, when no problem related to the test mode occurs during the test, R 1 =0.
In one embodiment, the algorithm formula of the risk indicator of each of the second risk items is:
R2j＝S2j×P2j
Wherein: s 2j is the severity level of the j-th second risk item;
p 2j is the probability level of occurrence of the j-th second risk item;
R 2j is the risk index of the j second risk item.
Through the algorithm formula of the risk index of each second risk item, the calculation of the risk index of each second risk item can be rapidly and accurately completed, and the conversion risk assessment efficiency of the test mode of the aviation turbine shaft engine is improved.
In one embodiment, the algorithm formula of the outfield early risk index is:
Wherein: r 2j is a risk indicator of the j-th second risk item;
p 2j is the probability level of occurrence of the j-th second risk item;
R 2 is an early risk index of the outfield.
The calculation of the early risk index of the external field can be rapidly and accurately completed through an algorithm formula of the early risk index of the external field, and the conversion risk assessment efficiency of the test mode of the aviation turboshaft engine is improved.
Specifically, when no failure related to the test mode is found in the external field use, then R 2 =0.
In one embodiment, the algorithmic formula for the test pattern conversion risk indicator is:
R＝a×R1+b×R2
Wherein: r 1 is a risk index in the testing process;
r 2 is an early risk index of the outfield;
a represents the duty ratio of the problem found after initial decomposition in two-pack two-test conversion into one-pack one-test;
b represents the duty ratio of the early failure of the external field converted into one-to-one test in two-to-two tests;
wherein 0.ltoreq.a, b.ltoreq.100%, and a+b=1.
The calculation of the test mode conversion risk index can be rapidly and accurately completed through an algorithm formula of the test mode conversion risk index, and the efficiency of conversion risk assessment of the test mode of the aviation turboshaft engine is improved.
In a specific embodiment, the determination of the sampling ratio is performed according to the test mode conversion risk index R.
Table 7 determination of test sample ratio for aero turboshaft engine
Preferably, when the test mode conversion risk index is smaller than 6, the test mode conversion risk index indicates that the aero-turbine shaft engine has the capability of one test, but in actual operation, in order to find out batch or random problems in the manufacturing process in time, the problems related to the test mode conversion are avoided from being brought into an external field, and 100% of one test is realized by gradually extracting part of the aero-turbine shaft engine to develop two tests.
In one embodiment, the algorithm formula for converting the problem found after the initial decomposition into the duty ratio of one test to one test in two tests is as follows:
The algorithm formula of the external field early fault conversion into the duty ratio of one test in two tests is as follows:
wherein,
The calculation of the duty ratio of the problems found after the initial decomposition in the two-pack two-test conversion to one-pack one-test can be rapidly and accurately completed through an algorithm formula of the duty ratio of the problems found after the initial decomposition in the two-pack two-test conversion to one-pack one-test; the calculation of the duty ratio of the external field early fault converted into one-package-one-test in two-package two-test can be rapidly and accurately completed through the algorithm formula of the duty ratio of the external field early fault converted into one-package-one-test in two-package two-test, and the conversion risk assessment efficiency of the test mode of the aviation turbine shaft engine is improved.
Although embodiments of the present invention have been described in connection with the accompanying drawings, various modifications and variations may be made by those skilled in the art without departing from the spirit and scope of the invention, and such modifications and variations fall within the scope of the invention as defined by the appended claims.
Claims (10)
1. A method for assessing risk of conversion in a test mode of an aero turboshaft engine, comprising the steps of:
Evaluating the risk of the testing process according to a first preset evaluating method, and calculating to obtain a risk index of the testing process;
evaluating early risk of the outfield according to a second preset evaluation method, and calculating to obtain early risk indexes of the outfield;
According to the risk index of the testing process and the early risk index of the external field, carrying out testing mode conversion risk, and calculating to obtain a testing mode conversion risk index;
and determining the sampling proportion according to the test mode conversion risk index.
2. The conversion risk assessment method for a test mode of an aero-turboshaft engine according to claim 1, wherein the first preset assessment method comprises the steps of:
Collecting problem data information;
screening problem data and determining a first risk item;
Determining a severity level for each first risk item;
determining the occurrence probability level of each first risk item outfield;
according to the severity level of each first risk item and the occurrence probability level of each first risk item in the external field, calculating to obtain a risk index of each first risk item;
and calculating to obtain the risk index of the testing process according to the risk index of each first risk item and the occurrence probability level of the external field of each first risk item.
3. The method for risk assessment of conversion of a test mode of an aircraft turboshaft engine according to claim 2, wherein said determining the severity level of each first risk item comprises: judging whether the severity level of the first risk item is greater than or equal to 9, if so, stopping evaluation, and rectifying the first risk item; if not, continuing to determine the occurrence probability level of each first risk item.
4. A conversion risk assessment method for a test mode of an aero-turboshaft engine according to claim 2 or 3, characterised in that said second preset assessment method comprises the steps of:
collecting fault data information;
Screening fault data and determining a second risk item;
Determining a severity level for each second risk item;
determining the occurrence probability level of each second risk item;
According to the severity level of each second risk item and the occurrence probability level of each second risk item, calculating to obtain a risk index of each second risk item;
and calculating to obtain the early-stage risk index of the outfield according to the risk index of each second risk item and the occurrence probability level of each second risk item.
5. The method for risk assessment of a conversion of a test mode of an aero-turboshaft engine according to claim 4, wherein the algorithmic formula of the risk indicator for each of the first risk terms is:
R1i＝S1i×P1i
wherein: s 1i is the severity level of the ith first risk item;
p 1i is the i first risk item outfield occurrence probability level;
R 1i is the risk index of the ith first risk item.
6. The method for assessing the risk of conversion of a test mode of an aircraft turboshaft engine of claim 5 wherein the algorithmic formula of the test process risk indicator is:
Wherein R 1i is a risk index of the ith first risk item;
p 1i is the i first risk item outfield occurrence probability level;
R 1 is a risk index of the testing process.
7. The method for assessing the risk of conversion of a test mode of an aircraft turboshaft engine of claim 6 wherein the algorithm formula for the risk indicator for each of said second risk terms is:
R2j＝S2j×P2j
Wherein: s 2j is the severity level of the j-th second risk item;
p 2j is the probability level of occurrence of the j-th second risk item;
R 2j is the risk index of the j second risk item.
8. The method for assessing the risk of conversion of a test mode of an aircraft turboshaft engine of claim 7 wherein the algorithm formula for the outfield early risk indicator is:
Wherein: r 2j is a risk indicator of the j-th second risk item;
p 2j is the probability level of occurrence of the j-th second risk item;
R 2 is an early risk index of the outfield.
9. The method for assessing the risk of conversion in a test mode of an aircraft turboshaft engine of claim 8 wherein the algorithm formula for the test mode conversion risk indicator is:
R＝a×R1+b×R2
Wherein: r 1 is a risk index in the testing process;
r 2 is an early risk index of the outfield;
a represents the duty ratio of the problem found after initial decomposition in two-pack two-test conversion into one-pack one-test;
b represents the duty ratio of the early failure of the external field converted into one-to-one test in two-to-two tests;
wherein 0.ltoreq.a, b.ltoreq.100%, and a+b=1.
10. The method for assessing the risk of conversion in a test mode of an aircraft turboshaft engine according to claim 9, wherein the algorithm formula for converting the problem found after initial decomposition into a one-to-one-test duty cycle in two-to-two tests is:
The algorithm formula of the external field early fault conversion into the duty ratio of one test in two tests is as follows:
wherein,
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