Aviation product testability minimum acceptable value determination method and device

Abstract

The invention belongs to the technical field of aircraft test design, and particularly relates to an aviation product testability minimum acceptable value determination method and device. The method comprises the following steps: S1, obtaining a testability specified value of a historical same-type product of a newly researched aviation product, a lowest testability acceptable value of the historical same-type product, state identification research time of the historical same-type product and column installation shaping time of the historical same-type product; s2, determining the testability growth ability of historical products of the same type; s3, obtaining a testability index specified value of the newly researched aviation product, state identification predicted development time of the newly researched aviation product and column installation predicted time of the newly researched aviation product; and S4, determining the lowest testability acceptable value of the newly researched aviation product. According to the method, the minimum acceptable value of the testability of the aviation product can be quickly calculated, and the reliability and credibility of the test are ensured.

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, in which case 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 of determining the minimum acceptable value of an airborne product testability, characterized in that, The method comprises the following steps: Step S1, obtaining the testability specified value of the historical same-type product of the 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; Step S2, determining the testability growth capability of the historical same-type product; Step S3, obtaining the testability index specified value of the 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; Step S4, determining the testability minimum acceptable value of the newly-developed aviation product.

2. The method of determining the minimum acceptable value of testability for an aerospace product according to claim 1, wherein, Step S1 further comprises determining the historical same-type product of the newly-developed aviation product by the following steps: Step S11, calculating the first coverage rate of a plurality of specified functions of a given newly-developed aviation product covered by each historical product, the second coverage rate of a plurality of specified systems of the given newly-developed aviation product covered by each historical product, and the third coverage rate of the process technology of a plurality of parts of the given newly-developed aviation product covered by each historical product; Step S12, determining the 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.

3. The method of determining the minimum acceptable value of the air product of claim 2, wherein, 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.

4. The method of determining the minimum acceptable value of the air product of claim 3, wherein, 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.

5. The method of determining the minimum acceptable value of the air product of claim 1, wherein, The testability minimum acceptable value comprises a detection rate minimum acceptable value.

6. The method of determining the minimum acceptable value of the air product of claim 1, wherein, The testability minimum acceptable value comprises an isolation rate minimum acceptable value.

7. The method of determining the minimum acceptable value of the air product of claim 1, wherein, The testability minimum acceptable value comprises a false alarm rate minimum acceptable value.

8. The method of determining the minimum acceptable value of testability for an aerospace product according to claim 1, wherein, In step S2, the testability growth capability g of the historical same-type product is determined by the following formula: ； wherein, a testability specified value for historical similar products, a testability minimum acceptable value for historical similar products, a state qualification development time for historical similar products, a fielding qualification time for historical similar products.

9. The method of determining the minimum acceptable value of the air product of claim 1, wherein, In step S4, the minimum acceptable value of testability for the new aircraft product is determined by the following equation : ； wherein, a value of the testability index of a newly developed aviation product, a predicted development time of the condition identification of a newly developed aviation product, a predicted time of the deployment of a newly developed aviation product.

10. The method of determining the minimum acceptable value of airworthiness product testability according to claim 9, wherein, Step S4 further comprises determining a minimum acceptable value of testability of the new aircraft product by correcting the parameter The correction parameter a is determined by the following formula: α=λ(1-β)ln(1+tn0 / tn1) / K; Wherein, λ is a technology maturity factor, the value is 0.8-1.2, the higher the maturity, the smaller λ, β is a 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 a confidence coefficient, the value is 0.8-1.

2.

11. An airborne product testability minimum acceptable value determination apparatus characterized by, The method comprises the following steps: The historical same-type product parameter acquisition module is configured to obtain the testability specified value of the historical same-type product of the 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; The historical same-type product testability growth capability calculation module is configured to determine the testability growth capability of the historical same-type product; The newly-developed aviation product parameter acquisition module is configured to obtain the testability index specified value of the 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; The newly-developed aviation product testability minimum acceptable value calculation module is configured to determine the testability minimum acceptable value of the newly-developed aviation product.

12. The airborne product testability minimum acceptable value determination device of claim 11, wherein, The historical same-type product parameter acquisition module comprises: The coverage calculation unit is configured to calculate a first coverage rate of the plurality of specified functions of the given newly-developed aviation product being covered by each of the historical products, a second coverage rate of the plurality of specified systems of the given newly-developed aviation product being covered by each of the historical products, and a third coverage rate of the plurality of parts of the given newly-developed aviation product being covered by each of the historical products in terms of process technology; The historical same-type product determination unit is configured to determine the 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.

13. The airborne product testability minimum acceptable value determination apparatus of claim 12 wherein, In the historical same-type product determination unit, when a1*s1+a2*s2+a3*s3>85%, the historical product is determined as the historical same-type product of the newly-developed aviation product, where 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.

14. The airborne product testability minimum acceptable value determination device of claim 13 wherein, 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.

15. The aircraft product minimum acceptable value determination device of claim 11, wherein, The testability minimum acceptable value includes a detection rate minimum acceptable value.

16. The aircraft product minimum acceptable value determination device of claim 11, wherein, The testability minimum acceptable value includes an isolation rate minimum acceptable value.

17. The airborne product testability minimum acceptable value determination device of claim 11, wherein, The testability minimum acceptable value includes a false alarm rate minimum acceptable value.

18. The airborne product testability minimum acceptable value determination apparatus of claim 11 wherein, 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: ； wherein, a testability specified value for historical similar products, a testability minimum acceptable value for historical similar products, a state qualification development time for historical similar products, a fielding qualification time for historical similar products.

19. The airborne product testability minimum acceptable value determination device of claim 11 wherein, 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 : ； wherein, a value of the testability index for a newly developed aviation product, a predicted development time for the condition identification of a newly developed aviation product, a predicted time for the deployment of a newly developed aviation product.

20. The airborne product testability minimum acceptable value determination device of claim 19 wherein, The newly-developed aviation product testability minimum acceptable value calculation module further includes: a correction unit for correcting the minimum acceptable value of testability of the new aircraft product by a correction parameter a correction is made, the correction parameter a being determined by the following formula: α=λ(1-β)ln(1+tn0 / tn1) / K; where λ is a technology maturity factor, with a value of 0.8-1.2, λ is smaller when the maturity is higher, β is a user risk rate, i.e., the probability of a non-conforming product being misjudged as conforming for the user, with a value of 0.05-0.20, and K is a confidence coefficient, with a value of 0.8-1.2.

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