Method and device for determining the minimum acceptable value of testability of an aeronautical product

Abstract

The application belongs to the technical field of aircraft test design, and particularly relates to a method and device for determining the minimum acceptable value of testability of an aviation product. The method comprises the following steps: S1, obtaining the testability specified value of a historical same-type product, the minimum acceptable value of testability of the historical same-type product, the state appraisal development time of the historical same-type product, and the deployment completion time of the historical same-type product; S2, determining the testability growth capability of the historical same-type product; S3, obtaining the testability index specified value of a newly developed aviation product, the state appraisal expected development time of the newly developed aviation product, and the deployment expected time of the newly developed aviation product; and S4, determining the minimum acceptable value of testability of the newly developed aviation product. The application can quickly calculate the minimum acceptable value of testability of the aviation product, and ensures the reliability and credibility of the test.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft test design, and particularly relates to a method and device for determining the minimum acceptable value of testability of an aviation product. BACKGROUND

[0002] In a development contract of an aviation product, testability indicators include specified values and minimum acceptable values. The minimum acceptable values are thresholds of actual use requirements, i.e. lower limit values, and are indicator requirement values that should be at least reached in a development process, and are the focus of testability test indicator evaluation and examination. The rationality of determination of the minimum acceptable value of testability directly affects the cycle and development pressure of a development task.

[0003] At present, in the field of testability of aviation products, there is no mature testability growth model to predict or evaluate the change process of the testability level of aviation products, and there is no related guidance document to guide the determination of the minimum acceptable value of testability. In this case, the determination of the minimum acceptable value of testability indicators mainly depends on the experience and ideas of designers, and when testability evaluation is performed at the end of development, there may be a situation that indicators do not meet requirements, for example, the initial indicator is set too high. At this time, the development cycle is extended or the reasons for not meeting the requirements are explained to the ordering party. Regardless of which case, the trust of the ordering party in the development capability of the contractor will be affected. SUMMARY

[0004] In order to solve the above problems, the first aspect of the application provides a method for determining the minimum acceptable value of testability of an aviation product, mainly comprising:

[0005] Step S1, acquiring the testability specified value of a historical same-type product of a newly developed aviation product, the testability minimum acceptable value of the historical same-type product, the state appraisal development time of the historical same-type product, and the deployment and finalization time of the historical same-type product;

[0006] Step S2, determining the testability growth capability of the historical same-type product;

[0007] Step S3, acquiring the testability indicator specified value of the newly developed aviation product, the state appraisal predicted development time of the newly developed aviation product, and the deployment predicted time of the newly developed aviation product;

[0008] Step S4, determining the minimum acceptable value of testability of the newly developed aviation product.

[0009] Preferably, step S1 further comprises determining the historical same-type product of the newly developed aviation product by the following manner:

[0010] Step S11, calculating a first coverage rate of a plurality of specified functions of a given newly developed aviation product being covered by each historical product, a second coverage rate of a plurality of specified systems of the given newly developed aviation product being covered by each historical product, and a third coverage rate of a plurality of parts of the given newly developed aviation product being covered by each historical product in terms of process technology;

[0011] Step S12, determining a historical same-type product of the newly developed aviation product based on the first coverage rate, the second coverage rate and the third coverage rate.

[0012] Preferably, in step S12, when a1*s1+a2*s2+a3*s3>85%, it is determined that the historical product is determined as the historical same-type product of the newly developed aviation product, wherein a1 is the first coverage rate, a2 is the second coverage rate, a3 is the third coverage rate, and s1, s2 and s3 are weighting coefficients.

[0013] Preferably, the weighting coefficient s1 of the first coverage rate is 0.5, the weighting coefficient s2 of the second coverage rate is 0.3, and the weighting coefficient s3 of the third coverage rate is 0.2.

[0014] Preferably, the minimum acceptable value of testability includes a minimum acceptable value of detection rate.

[0015] Preferably, the minimum acceptable value of testability includes a minimum acceptable value of isolation rate.

[0016] Preferably, the minimum acceptable value of testability includes a minimum acceptable value of false alarm rate.

[0017] Preferably, in step S2, the testability growth capability g of the historical same-type product is determined by the following formula:

[0018] ;

[0019] wherein, is a specified value of testability of the historical same-type product, is a minimum acceptable value of testability of the historical same-type product, is a state appraisal development time of the historical same-type product, is a deployment development time of the historical same-type product.

[0020] Preferably, in step S4, the minimum acceptable value of testability of the newly developed aviation product is determined by the following formula: :

[0021] ;

[0022] wherein, is a specified value of testability index of the newly developed aviation product, a development time of the new aircraft product for the state appraisal, an installation time of the new aircraft product for the state appraisal.

[0023] Preferably, the step S4 further comprises correcting the minimum acceptable value of the testability of the new aircraft product by a correction parameter α determined by the following formula: The correction is performed, and the correction parameter α is determined by the following formula:

[0024] α = λ (1 - β) ln (1 + tn0 / tn1) / K;

[0025] wherein λ is a technology maturity factor, and λ is 0.8-1.2, the higher the maturity, the smaller λ, β is a user risk rate, i.e. the probability of misjudging unqualified products as qualified for the user, and β is 0.05-0.20, and K is a confidence coefficient, and K is 0.8-1.2.

[0026] The second aspect of the present application provides a device for determining the minimum acceptable value of the testability of an aircraft product, mainly comprising:

[0027] a historical same-type product parameter acquisition module, configured to acquire a testability specified value of a historical same-type product of the new aircraft product, a minimum acceptable value of the testability of the historical same-type product, a development time of the historical same-type product for the state appraisal, and an installation time of the historical same-type product for the state appraisal;

[0028] a historical same-type product testability growth capability calculation module, configured to determine the testability growth capability of the historical same-type product;

[0029] a new aircraft product parameter acquisition module, configured to acquire a testability index specified value of the new aircraft product, a development time of the new aircraft product for the state appraisal, and an installation time of the new aircraft product for the state appraisal;

[0030] a new aircraft product testability minimum acceptable value calculation module, configured to determine the minimum acceptable value of the testability of the new aircraft product.

[0031] Preferably, the historical same-type product parameter acquisition module comprises:

[0032] a coverage calculation unit, configured to calculate a first coverage rate of a plurality of specified functions of a given new aircraft product covered by each historical product, a second coverage rate of a plurality of specified systems of the given new aircraft product covered by each historical product, and a third coverage rate of a plurality of parts of the given new aircraft product covered by each historical product;

[0033] a historical same-type product determination unit, configured to determine the historical same-type product of the new aircraft product based on the first coverage rate, the second coverage rate and the third coverage rate.

[0034] Preferably, in the historical same-type product determining unit, when a1*s1+a2*s2+a3*s3>85%, it is determined that the historical product is determined as the historical same-type product of the new aircraft product, wherein a1 is the first coverage rate, a2 is the second coverage rate, a3 is the third coverage rate, and s1, s2 and s3 are weighting coefficients.

[0035] Preferably, the weighting coefficient s1 of the first coverage rate is 0.5, the weighting coefficient s2 of the second coverage rate is 0.3, and the weighting coefficient s3 of the third coverage rate is 0.2.

[0036] Preferably, the testability minimum acceptable value includes a detection rate minimum acceptable value.

[0037] Preferably, the testability minimum acceptable value includes an isolation rate minimum acceptable value.

[0038] Preferably, the testability minimum acceptable value includes a false alarm rate minimum acceptable value.

[0039] Preferably, in the testability growth capability calculating module of the historical same-type product, the testability growth capability g of the historical same-type product is determined by the following formula:

[0040] ;

[0041] wherein, is a testability specified value of the historical same-type product, is a testability minimum acceptable value of the historical same-type product, is a state appraisal development time of the historical same-type product, is a deployment development time of the historical same-type product.

[0042] Preferably, in the testability minimum acceptable value calculating module of the new aircraft product, the testability minimum acceptable value of the new aircraft product is determined by the following formula:

[0043] ;

[0044] wherein, is a testability index specified value of the new aircraft product, is a state appraisal estimated development time of the new aircraft product, is a deployment estimated time of the new aircraft product.

[0045] Preferably, the testability minimum acceptable value calculating module of the new aircraft product further includes:

[0046] ​A correction unit is configured to correct the minimum acceptable value of the testability of the new aviation product by using a correction parameter The correction parameter a is determined by the following formula:

[0047] a = l(1 - b)ln(l + tn0 / tn1) / K;

[0048] wherein, l is a technical maturity factor, and is 0.8-1.2, the higher the maturity, the smaller the l, b is a user risk rate, i.e., the probability of misjudging unqualified products as qualified for users, and is 0.05-0.20, and K is a confidence coefficient, and is 0.8-1.2.

[0049] The application can quickly calculate the minimum acceptable value of the testability of the aviation product, and ensure the reliability and credibility of the test. BRIEF DESCRIPTION OF DRAWINGS

[0050] Figure 1 is a flowchart of a preferred embodiment of the method for determining the minimum acceptable value of the testability of the aviation product. DETAILED DESCRIPTION

[0051] In order to make the purpose, technical scheme and advantages of the application clearer, the technical scheme in the embodiments of the application will be described in more detail below with reference to the drawings. In the drawings, the same or similar notations represent the same or similar elements or elements with the same or similar functions throughout. The described embodiments are part of the embodiments of the application, not all of the embodiments. The embodiments described below with reference to the drawings are exemplary and are intended to explain the application, and cannot be understood as limiting the application. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the application. The embodiments of the application will be described in detail below with reference to the drawings.

[0052] The first aspect of the application provides a method for determining the minimum acceptable value of the testability of an aviation product, as shown in Figure 1 mainly includes:

[0053] Step S1, obtaining the testability specified value of the historical same type product of the new aviation product, the minimum acceptable value of the testability of the historical same type product, the state appraisal development time of the historical same type product and the installation and finalization time of the historical same type product;

[0054] Step S2, determining the testability growth capability of the historical same type product;

[0055] Step S3, obtaining the testability index specified value of the new aviation product, the state appraisal expected development time of the new aviation product, and the deployment expected time of the new aviation product.

[0056] Step S4, determining the testability minimum acceptable value of the new aviation product.

[0057] The application calculates the testability growth capability of the historical similar product of the new aviation product through the testability minimum acceptable value of the historical similar product, and takes the testability growth capability as the testability minimum acceptable value of the new aviation product, and then reversely obtains the testability minimum acceptable value of the new aviation product.

[0058] In some optional embodiments, step S1 further comprises determining the historical similar product of the new aviation product by the following manner:

[0059] Step S11, calculating a first coverage rate of a plurality of specified functions of a given new aviation product covered by each historical product, a second coverage rate of a plurality of specified systems of the given new aviation product covered by each historical product, and a third coverage rate of a plurality of parts of the given new aviation product covered by each historical product;

[0060] Step S12, determining the historical similar product of the new aviation product based on the first coverage rate, the second coverage rate, and the third coverage rate.

[0061] The historical similar product referred to in the embodiment generally refers to a historical product similar to the new aviation product, and the similarity of the product is characterized by functions, architectures, and processes, and it is considered that the products consistent in functions, architectures, and processes belong to similar products. For example, it is specified that the new aviation product should have the most important 30 functions, and if the 30 functions are all possessed in a historical product, the first coverage rate is 100%; for example, it is specified that the new aviation product should have the most important 50 systems, subsystems, or components, and if a historical product has 40 of them, the second coverage rate is 80%; for example, the manufacturing processes of 45 systems, subsystems, or components of the above new aviation product are the same as those of the same systems, subsystems, or components of a historical product, and the third coverage rate is 90%. The manufacturing processes herein are, for example, welding, casting, 3D printing, etc.

[0062] In some optional embodiments, in step S12, when a1*s1+a2*s2+a3*s3>85%, it is determined that the historical product is determined as the historical similar product of the new aviation product, wherein a1 is the first coverage rate, a2 is the second coverage rate, a3 is the third coverage rate, and s1, s2, and s3 are weighting coefficients.

[0063] In some optional embodiments, the weighting coefficient s1 of the first coverage rate is 0.5, the weighting coefficient s2 of the second coverage rate is 0.3, and the weighting coefficient s3 of the third coverage rate is 0.2.

[0064] In some optional embodiments, the minimum acceptable value of testability includes a minimum acceptable value of detection rate.

[0065] In some optional embodiments, the minimum acceptable value of testability includes a minimum acceptable value of isolation rate.

[0066] In some optional embodiments, the minimum acceptable value of testability includes a minimum acceptable value of false alarm rate.

[0067] The above embodiments cover general aviation product testability indicators, such as detection rate (FDR), isolation rate (FIR), and false alarm rate (FAR).

[0068] In some optional embodiments, in step S2, the testability growth capability g of the historical same-type product is determined by the following formula:

[0069] ;

[0070] wherein, is a testability specified value of the historical same-type product, is a minimum acceptable value of testability of the historical same-type product, is a state appraisal development time of the historical same-type product, is a deployment shaping time of the historical same-type product.

[0071] At present, there is no general testability growth model specification in the field of testability, but in the development process, the development capabilities of general quality characteristics are basically improved together, and therefore, the present application adopts an improved Duane model for the growth model of testability indicators. The model is as follows:

[0072] In the development process of equipment, it is assumed that the relationship between the number of successfully detected faults in testability test and the cumulative test time is as follows:

[0073] .

[0074] In the above formula, is the number of faults correctly detected at the cumulative time t, and a is a model coefficient.

[0075] Define the total number of injected faults in testability test as , and the detection rate can be expressed as:

[0076] .

[0077] In the above formula, The number of faults injected per unit test time. The data in step S1 is brought into to obtain:

[0078] .

[0079] Slightly changing the above formula, we obtain:

[0080] .

[0081] From this, the expression of the testability growth capability g of the same type of historical products in step S2 of the present application can be derived.

[0082] In some optional embodiments, in step S4, the minimum acceptable value of the testability of the newly developed aviation product is determined by the following formula :

[0083] ;

[0084] wherein, is the specified value of the testability index of the newly developed aviation product, is the state appraisal expected development time of the newly developed aviation product, is the deployment expected time of the newly developed aviation product.

[0085] As mentioned above, the testability growth capability g of the newly developed aviation product also satisfies the above relationship, and thus the testability growth capability g of the same type of historical products calculated in step S2 can be taken as the testability growth capability of the newly developed aviation product, and then the minimum acceptable value of the testability of the newly developed aviation product is inversely deduced according to the parameters in step S3.

[0086] In some optional embodiments, step S4 further comprises correcting the minimum acceptable value of the testability of the newly developed aviation product by a correction parameter, and the correction parameter a is determined by the following formula:

[0087] a = l (1 - b) ln (1 + tno / tn1) / K;

[0088] wherein, l is a technical maturity factor, taking a value of 0.8-1.2, the higher the maturity, the smaller the l, b is a user risk rate, i.e. the probability of misjudging unqualified products as qualified for the user, taking a value of 0.05-0.20, and K is a confidence coefficient, taking a value of 0.8-1.2.

[0089] For a mature technology, for example, more than 3 generations of application, lambda can take the value of 0.8, for an improved technology, for example, with partial innovation, lambda can take the value of 1.0, and for a completely new technology, lambda can take the value of 1.2. The evaluation of the improved technology or the completely new technology can refer to the first coverage rate, the second coverage rate and the third coverage rate calculated as described above. For example, the parameter a1*s1+a2*s2+a3*s3, which is the comprehensive calculation of the first coverage rate, the second coverage rate and the third coverage rate, is directly mapped to the value range of lambda when the value of the parameter a1*s1+a2*s2+a3*s3 is 100%, that is, when the value of the parameter a1*s1+a2*s2+a3*s3 is 100%, the corresponding lambda is 0.8.

[0090] The present application provides a reasonable and efficient calculation for determining the minimum acceptable value of testability of an aviation product, and provides an effective theoretical basis for the development of testability of a new aviation product.

[0091] The second aspect of the present application provides a device for determining the minimum acceptable value of testability of an aviation product corresponding to the above method, mainly comprising:

[0092] The historical same-type product parameter acquisition module is configured to acquire the testability specified value of the historical same-type product of the new aviation product, the minimum acceptable value of testability of the historical same-type product, the state appraisal development time of the historical same-type product and the deployment and finalization time of the historical same-type product.

[0093] The historical same-type product testability growth capability calculation module is configured to determine the testability growth capability of the historical same-type product.

[0094] The new aviation product parameter acquisition module is configured to acquire the testability index specified value of the new aviation product, the state appraisal expected development time of the new aviation product and the deployment expected time of the new aviation product.

[0095] The new aviation product testability minimum acceptable value calculation module is configured to determine the minimum acceptable value of testability of the new aviation product.

[0096] In some optional embodiments, the historical same-type product parameter acquisition module comprises:

[0097] The coverage rate calculation unit is configured to calculate the first coverage rate of a plurality of specified functions of a given new aviation product covered by each historical product, the second coverage rate of a plurality of specified systems of the given new aviation product covered by each historical product, and the third coverage rate of the process technology of a plurality of parts of the given new aviation product covered by each historical product.

[0098] The historical same-type product determination unit is configured to determine the historical same-type product of the new aviation product based on the first coverage rate, the second coverage rate and the third coverage rate.

[0099] In some optional embodiments, in the historical same-type product determination unit, when a1*s1+a2*s2+a3*s3>85%, it is determined that the historical product is determined as the historical same-type product of the new aircraft product, wherein a1 is the first coverage rate, a2 is the second coverage rate, a3 is the third coverage rate, and s1, s2 and s3 are weighting coefficients.

[0100] In some optional embodiments, the weighting coefficient s1 of the first coverage rate is 0.5, the weighting coefficient s2 of the second coverage rate is 0.3, and the weighting coefficient s3 of the third coverage rate is 0.2.

[0101] In some optional embodiments, the testability minimum acceptable value includes a detection rate minimum acceptable value.

[0102] In some optional embodiments, the testability minimum acceptable value includes an isolation rate minimum acceptable value.

[0103] In some optional embodiments, the testability minimum acceptable value includes a false alarm rate minimum acceptable value.

[0104] In some optional embodiments, in the testability growth capability calculation module of the historical same-type product, the testability growth capability g of the historical same-type product is determined by the following formula:

[0105] ;

[0106] wherein, is a testability specified value of the historical same-type product, is a testability minimum acceptable value of the historical same-type product, is a state appraisal development time of the historical same-type product, is a deployment development time of the historical same-type product.

[0107] In some optional embodiments, in the new aircraft product testability minimum acceptable value calculation module, the testability minimum acceptable value of the new aircraft product is determined by the following formula:

[0108] ;

[0109] wherein, is a testability index specified value of the new aircraft product, is a state appraisal estimated development time of the new aircraft product, is a deployment estimated time of the new aircraft product.

[0110] In some optional embodiments, the new aircraft product testability minimum acceptable value calculation module further comprises:​

[0111] a correction unit for correcting the minimum acceptable value of the testability of the new aircraft product by a correction parameter The correction parameter α is determined by the following formula:

[0112] α = λ (1-β) ln (1+tn0 / tn1) / K;

[0113] Wherein, λ is the technology maturity factor, the value is 0.8-1.2, the higher the maturity, the smaller λ, β is the user risk rate, that is, for the user, the probability of misjudging unqualified products as qualified, the value is 0.05-0.20, K is the confidence coefficient, the value is 0.8-1.2.

[0114] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited to this, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A method for determining the minimum acceptable value for testability of aviation products, characterized in that, include: Step S1: Obtain the testability requirements, minimum acceptable testability values, status qualification development time, and type approval time of the new aviation product; Step S2: Determine the testable growth capability of similar products in the past; Step S3: Obtain the testability index specifications for the newly developed aviation product, the estimated development time for the status qualification of the newly developed aviation product, and the estimated deployment time for the newly developed aviation product; Step S4: Determine the minimum acceptable testability value for the newly developed aviation product; Step S1 further includes identifying historical similar products of the newly developed aviation product through the following methods: Step S11: Calculate the first coverage rate of multiple specified functions of a given new aerospace product being covered by each historical product, the second coverage rate of multiple specified systems of a given new aerospace product being covered by each historical product, and the third coverage rate of the process technology of multiple parts of a given new aerospace product being covered by each historical product. Step S12: Determine the historical similar products of the newly developed aviation product based on the first coverage rate, the second coverage rate, and the third coverage rate; In step S12, when a1*s1+a2*s2+a3*s3>85%, the historical product is determined to be a historical product of the same type as the newly developed aviation product. Here, a1 is the first coverage rate, a2 is the second coverage rate, a3 is the third coverage rate, and s1, s2 and s3 are weighting coefficients. The minimum acceptable testability value includes one of the minimum acceptable detection rate, the minimum acceptable isolation rate, and the minimum acceptable false alarm rate. In step S2, the testability growth capability g of historically similar products is determined using the following formula: ； in, These are the test specifications for similar products in the past. This represents the lowest acceptable testability value for similar products in the past. The development time was used to assess the condition of similar products in the past. The timeframe for the standardization and deployment of similar products in the past; In step S4, the minimum acceptable testability value for the newly developed aerospace product is determined using the following formula. : ； in, These are the test performance specifications for newly developed aviation products. The estimated development time for the status qualification of newly developed aviation products. The estimated time for the deployment of newly developed aviation products.

2. The method for determining the minimum acceptable testability value of aviation products as described in claim 1, characterized in that, The weighting coefficient s1 for the first coverage rate is 0.5, the weighting coefficient s2 for the second coverage rate is 0.3, and the weighting coefficient s3 for the third coverage rate is 0.

2.

3. The method for determining the minimum acceptable testability value of aviation products as described in claim 1, characterized in that, Step S4 further includes adjusting the minimum acceptable testability value of the newly developed aerospace product by correcting the parameters. The correction parameter α is determined by the following formula: α=λ(1−β)ln(1+tn0 / tn1) / K; Wherein, λ is the technology maturity factor, with a value of 0.8-1.

2. The higher the maturity, the smaller λ is. β is the user risk rate, which is the probability that a non-conforming product is mistakenly judged as a qualified product for the user, with a value of 0.05-0.

20. K is the confidence coefficient, with a value of 0.8-1.

2.

4. A device for determining the minimum acceptable testability value of an aviation product, characterized in that, For implementing the method for determining the minimum acceptable value for testability of aviation products as described in claim 1, the apparatus comprises: The historical similar product parameter acquisition module is used to obtain the testability specification values, minimum acceptable testability values, status qualification development time, and type approval time of historical similar products for newly developed aviation products. The testable growth capability calculation module for similar products in history is used to determine the testable growth capability of similar products in history. The new aviation product parameter acquisition module is used to acquire the testability index specified values ​​of the new aviation product, the expected development time for the status qualification of the new aviation product, and the expected time for the deployment of the new aviation product. The module for calculating the minimum acceptable testability value of newly developed aviation products is used to determine the minimum acceptable testability value of newly developed aviation products.

5. The apparatus for determining the minimum acceptable testability value of aviation products as described in claim 4, characterized in that, The module for acquiring parameters of historical similar products includes: The coverage calculation unit is used to calculate the first coverage rate of multiple specified functions of a given new aerospace product being covered by each historical product, the second coverage rate of multiple specified systems of a given new aerospace product being covered by each historical product, and the third coverage rate of the process technology of multiple parts of a given new aerospace product being covered by each historical product. The historical similar product identification unit is used to identify historical similar products of newly developed aviation products based on the first coverage rate, the second coverage rate, and the third coverage rate.

6. The apparatus for determining the minimum acceptable testability value of aviation products as described in claim 5, characterized in that, In the historical similar product determination unit, when a1*s1+a2*s2+a3*s3>85%, the historical product is determined to be a historical similar product of the newly developed aviation product. Here, a1 is the first coverage rate, a2 is the second coverage rate, a3 is the third coverage rate, and s1, s2 and s3 are weighting coefficients.

7. The apparatus for determining the minimum acceptable testability value of aviation products as described in claim 6, characterized in that, The weighting coefficient s1 for the first coverage rate is 0.5, the weighting coefficient s2 for the second coverage rate is 0.3, and the weighting coefficient s3 for the third coverage rate is 0.

2.

8. The apparatus for determining the minimum acceptable testability value of aviation products as described in claim 4, characterized in that, The minimum acceptable testability includes the minimum acceptable detection rate.

9. The apparatus for determining the minimum acceptable testability value of aviation products as described in claim 4, characterized in that, The minimum acceptable testability includes the minimum acceptable isolation rate.

10. The apparatus for determining the minimum acceptable testability value of aviation products as described in claim 4, characterized in that, The minimum acceptable testability includes the minimum acceptable false alarm rate.

11. The apparatus for determining the minimum acceptable testability value of aviation products as described in claim 4, characterized in that, In the testability growth capability calculation module for historical similar products, the testability growth capability g of historical similar products is determined by the following formula: ； in, These are the test specifications for similar products in the past. This represents the lowest acceptable testability value for similar products in the past. The development time was used to assess the condition of similar products in the past. This is the timeframe for the standardization and deployment of similar products in the past.

12. The apparatus for determining the minimum acceptable testability value of aviation products as described in claim 4, characterized in that, In the module for calculating the minimum acceptable testability value of newly developed aviation products, the minimum acceptable testability value of the newly developed aviation products is determined by the following formula. : ； in, These are the test performance specifications for newly developed aviation products. The estimated development time for the status qualification of newly developed aviation products. The estimated time for the deployment of newly developed aviation products.

13. The apparatus for determining the minimum acceptable testability value of aviation products as described in claim 12, characterized in that, The module for calculating the minimum acceptable testability value of newly developed aviation products also includes: A calibration unit is used to determine the minimum acceptable testability of the newly developed aerospace product using calibration parameters. The correction parameter α is determined by the following formula: α=λ(1−β)ln(1+tn0 / tn1) / K; Wherein, λ is the technology maturity factor, with a value of 0.8-1.

2. The higher the maturity, the smaller λ is. β is the user risk rate, which is the probability that a non-conforming product is mistakenly judged as a qualified product for the user, with a value of 0.05-0.

20. K is the confidence coefficient, with a value of 0.8-1.2.

Images