Liquid rocket engine reliability evaluation method and device and electronic equipment

Abstract

The application provides a liquid rocket engine reliability evaluation method and device and electronic equipment. The method comprises the following steps: acquiring different environment reliability evaluation data under three levels of tests in the development stage of a liquid rocket engine; determining the reliability of the prior reliability corresponding to the three levels of tests based on the different environment reliability evaluation data under the three levels of tests; when the reliability meets the standard, fusing the different environment reliability evaluation data under the three levels of tests to determine the reliability prior distribution information; fusing the reliability prior distribution information and the test information to obtain the reliability posterior distribution information; and determining the final reliability evaluation result of the liquid rocket engine based on the reliability posterior distribution information. The application can analyze the reliability evaluation data under multiple levels of tests in the development stage, and can improve the accuracy and reliability of the reliability evaluation result.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of rockets, in particular to a liquid rocket engine reliability evaluation method and device and electronic equipment. BACKGROUND

[0002] Engine inherent reliability is designed, but also produced and tested, and must be fully exposed to defects and weak links of the engine in design, process and raw material selection through sufficient test time and test frequency, and improved through continuous improvement to achieve the purpose of improving reliability.

[0003] Liquid rocket engine reliability evaluation is directly accumulated by multiple sub-sample engine reliability hot test. Although the multiple sub-sample engine reliability hot test accumulation method is beneficial to the sufficiency and authenticity of the space orbit control engine reliability verification, the experimental cost is high and the test period is long. In addition, generally speaking, the reliability of engine components is high, and the sample for testing is small. If only single group of few failure or even no failure test data is used for reliability evaluation, the evaluation accuracy of the existing method is unsatisfactory. SUMMARY

[0004] The purpose of the present application is to provide a liquid rocket engine reliability evaluation method and device and electronic equipment, which can comprehensively analyze the heterogeneous environment reliability evaluation data under multiple levels of tests in the liquid rocket engine development stage, improve the accuracy and reliability of the reliability evaluation result, and use the reliability evaluation method based on multi-source information fusion under the premise of not reducing the lower limit of reliability confidence, so as to reduce the test frequency and achieve the purpose of saving funds.

[0005] In a first aspect, the present application provides a liquid rocket engine reliability evaluation method, which comprises: obtaining heterogeneous environment reliability evaluation data under three levels of tests in the liquid rocket engine development stage; the three levels of tests include component level tests, subsystem level tests and whole machine tests carried out in the engine development stage; determining the reliability of the priori corresponding to the three levels of tests based on the heterogeneous environment reliability evaluation data under the three levels of tests; when the reliability meets the standard, the heterogeneous environment reliability evaluation data under the three levels of tests is fused to determine the reliability priori distribution information; the reliability priori distribution information and the test information are fused to obtain the reliability posteriori distribution information; and determining the final reliability evaluation result of the liquid rocket engine based on the reliability posteriori distribution information.

[0006] Further, the heterogeneous environment reliability evaluation data includes life type, success type and degradation type data of each component of the engine under different levels of tests in each development stage of the life cycle and different from the field use environment conditions.

[0007] Further, the step of obtaining the environmental reliability evaluation data of the components in the liquid rocket engine development stage includes: obtaining the reliability evaluation data of a plurality of reliability analysis units corresponding to each subassembly in the liquid rocket engine; converting the reliability evaluation data of the plurality of reliability analysis units into equivalent success-failure test data; using a series model method to convert the plurality of equivalent success-failure test data into reliability evaluation data of the subassembly; and obtaining the environmental reliability evaluation data of the whole machine by jointly processing the reliability evaluation data of the plurality of subassemblies according to the correlation of the failure modes of the subassemblies. The step of obtaining the environmental reliability evaluation data of the subsystems in the liquid rocket engine development stage includes: obtaining the reliability evaluation data of each subsystem in the liquid rocket engine; and obtaining the environmental reliability evaluation data of the whole machine by jointly processing the reliability evaluation data of the plurality of subsystems according to the correlation of the failure modes of the subsystems. The step of obtaining the environmental reliability evaluation data of the whole machine in the liquid rocket engine development stage includes: performing a whole machine test on the liquid rocket engine to obtain the environmental reliability evaluation data of the whole machine.

[0008] Further, the step of jointly processing includes: determining the corresponding reliability model according to the correlation of the failure modes among the plurality of subassemblies or subsystems; and calculating the reliability evaluation data of the plurality of subassemblies or subsystems according to the reliability model to obtain the environmental reliability evaluation data of the whole machine.

[0009] Further, the step of fusing the environmental reliability evaluation data of the three levels of tests to determine the reliability prior distribution information includes: weighting and fusing the environmental reliability evaluation data of the three levels of tests to obtain the reliability prior distribution information.

[0010] Further, the development stages include: a pattern stage, a preliminary sample stage, a sample stage, a final sample stage, and a batch production stage.

[0011] Further, the step of fusing the reliability prior distribution information and the test information to obtain the reliability posterior distribution information includes: using Bayesian decision theory to fuse the reliability prior distribution information and the test information to calculate the reliability posterior distribution information of the engine.

[0012] In a second aspect, the application further provides a liquid rocket engine reliability evaluation device, which comprises: a data acquisition module, configured to acquire heterogeneous environment reliability evaluation data under three levels of tests in a liquid rocket engine development stage; the three levels of tests comprise component-level tests, subsystem-level tests and whole-machine tests carried out in the engine development stage; a credibility determination module, configured to determine credibility of prior reliability corresponding to the three levels of tests based on the heterogeneous environment reliability evaluation data under the three levels of tests; a prior distribution determination module, configured to fuse the heterogeneous environment reliability evaluation data under the three levels of tests to determine reliability prior distribution information when the credibility meets a standard; a posterior distribution determination module, configured to fuse the reliability prior distribution information and test information to obtain reliability posterior distribution information; and a result determination module, configured to determine a final reliability evaluation result of the liquid rocket engine based on the reliability posterior distribution information.

[0013] In a third aspect, the application further provides an electronic device, comprising a processor and a memory, wherein the memory stores computer executable instructions capable of being executed by the processor, and the processor executes the computer executable instructions to implement the method in the first aspect.

[0014] In a fourth aspect, the application further provides a computer readable storage medium, wherein the computer readable storage medium stores computer executable instructions, and the computer executable instructions, when invoked and executed by a processor, cause the processor to implement the method in the first aspect.

[0015] In the liquid rocket engine reliability evaluation method, device and electronic device provided by the application, first, heterogeneous environment reliability evaluation data under three levels of tests in a liquid rocket engine development stage is acquired; the three levels of tests comprise component-level tests, subsystem-level tests and whole-machine tests carried out in the engine development stage; then, credibility of prior reliability corresponding to the three levels of tests is determined based on the heterogeneous environment reliability evaluation data under the three levels of tests; when the credibility meets a standard, the heterogeneous environment reliability evaluation data under the three levels of tests is fused to determine reliability prior distribution information; the reliability prior distribution information and test information are fused to obtain reliability posterior distribution information; finally, a final reliability evaluation result of the liquid rocket engine is determined based on the reliability posterior distribution information. The application can comprehensively analyze reliability evaluation data under multiple levels of tests, improve the precision and credibility of the reliability evaluation result, and reduce the number of definitive tests to save funds without reducing the lower limit of reliability confidence. BRIEF DESCRIPTION OF DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the specific embodiments or prior art of the present application, the drawings needed to be used in the specific embodiments or prior art description will be briefly introduced as follows. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without any creative effort.

[0017] Figure 1 A flow chart of a liquid rocket engine reliability evaluation method provided for an embodiment of the present application is shown in the figure.

[0018] Figure 2 A general technical line chart of a liquid rocket engine reliability evaluation provided for an embodiment of the present application is shown in the figure.

[0019] Figure 3 A schematic diagram of a reliability evaluation data acquisition process provided for an embodiment of the present application is shown in the figure.

[0020] Figure 4 A structural block diagram of a liquid rocket engine reliability evaluation device provided for an embodiment of the present application is shown in the figure.

[0021] Figure 5 A structural schematic diagram of an electronic device provided for an embodiment of the present application is shown in the figure. DETAILED DESCRIPTION

[0022] The technical solutions of the present application will be described in detail below with embodiments. Obviously, the described embodiments are only some of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without any creative effort are within the scope of protection of the present application.

[0023] The existing multi-subsample engine reliability hot test cumulative reliability evaluation method has high test cost and long test cycle. Therefore, a special exploration method for weak links of engine reliability is proposed, which includes the following steps:

[0024] Step 1: Propose a liquid rocket engine design scheme; Step 2: Identify weak links of engine reliability; Step 3: Carry out special reliability test for weak links of engine; Step 4: Evaluate the reliability of weak links; Step 5: Carry out engine whole machine reliability verification, and integrate engine reliability verification into engine design scheme verification test and environment verification test; Step 6: Evaluate the engine reliability.

[0025] The above method only evaluates the weak links, and the evaluation accuracy is not satisfactory.

[0026] Based on this, the embodiment of the present application provides a liquid rocket engine reliability evaluation method, device and electronic equipment, which can comprehensively analyze the reliability evaluation data under multiple levels of tests in the development stage, and improve the accuracy and reliability of the reliability evaluation result. In order to facilitate the understanding of the present embodiment, first of all, a liquid rocket engine reliability evaluation method disclosed by the present application is introduced in detail.

[0027] Briefly speaking, the liquid rocket engine assembly will undergo the process of test-exposure of defects-analysis of reasons-improvement of design and process-retest in the development process. In this process, the defects in the design and manufacturing of the assembly are continuously exposed, and after analysis and improvement, it is continuously improved. If the multi-source data of different development stages of the engine is fully utilized, the data of the current stage is expanded, the accuracy and reliability of the reliability evaluation result of the assembly can be improved.

[0028] Based on this, the embodiment of the present application provides a liquid rocket engine reliability evaluation method, referring to the flow chart shown in Figure 1 and the general technical roadmap shown in Figure 2 , the method comprises the following steps:

[0029] Step S102, acquiring the different environment reliability evaluation data under three levels of tests in the development stage of the liquid rocket engine; the three levels of tests include the component level test, the subsystem level test and the whole machine test carried out in the development stage of the engine;

[0030] The development stage of the liquid rocket engine can be divided into: scheme feasibility demonstration, sample stage, preliminary sample stage, sample stage, finalization stage and batch production stage. For different development stages, different reliability evaluation data can be obtained through different tests. The test data results under different levels of tests in each development stage are obtained. Through the processing mode described later, the reliability evaluation data under different levels of tests are finally the reliability distribution of the whole machine. The different environment reliability evaluation data includes the life type, success type and degradation type data of each component of the engine under different levels of tests carried out in the development stage of the life cycle and different from the on-site use environment conditions.

[0031] Step S104, based on the different environment reliability evaluation data under the three levels of tests, determining the reliability of the prior reliability corresponding to the three levels of tests respectively;

[0032] For the multi-source reliability information of the liquid rocket engine, that is, the different environment reliability evaluation data under three different test levels, the reliability (that is, the result of consistency test) needs to be measured. The consistency test method is used to judge the degree of coincidence between the multi-source reliability information and the engine test information. If the consistency test is passed, it indicates that this kind of reliability information is reliable. For the engine reliability information before the test, the engine actual test information is recorded as At the same time, the opposite hypothesis and event are introduced:

[0033] 1) H0 J and K belong to the same population;

[0034] 2) H1 J and K belong to different populations;

[0035] 3) A Event of adopting H0 hypothesis;

[0036] 4) Event of rejecting H0 hypothesis, that is, adopting H1 event.

[0037] The reliability of the prior reliability information of the liquid rocket engine is defined as the probability that H0 hypothesis is established when A event occurs, recorded as ,

[0038]

[0039] In the formula , , wherein represents the false positive risk (the probability of not adopting A event under the condition that H0 is established), represents the false negative risk (the probability of adopting A event under the condition that H1 is established).

[0040] When calculating the reliability of the prior reliability information, it is necessary to determine . It is given by expert judgment or obtained through reliable information source analysis. If it cannot be given, generally = 0.5, at this time

[0041] . That is, the reliability.

[0042] Through the above-mentioned mode, the reliabilities corresponding to three different levels of tests can be determined in advance.

[0043] Step S106, when the reliability meets the standard (that is, the consistency test is passed), the heterogeneous environment reliability evaluation data under three levels of tests are fused to determine the reliability prior distribution information;

[0044] The credibility threshold refers to that the credibility of the three levels of tests exceeds the preset threshold, at this time, the data under the three levels of tests needs to be fused. The step is actually a process of fusing the reliability evaluation data (prior distribution) corresponding to the multiple levels of tests in the development stage respectively. The reliability prior distribution information can be obtained by weighted fusion of the reliability evaluation data under the three levels of tests.

[0045] In step S108, the reliability prior distribution information and the test information are fused to obtain reliability posterior distribution information.

[0046] In the implementation, the reliability prior distribution information and the test information can be fused by using the Bayesian decision theory to calculate the reliability posterior distribution information of the engine.

[0047] In step S110, the final reliability evaluation result of the liquid rocket engine is determined based on the reliability posterior distribution information.

[0048] In actual application, the reliability posterior distribution information can be a probability density distribution curve; there are multiple ways to determine the point estimate result of the engine, for example, the reliability corresponding to the maximum probability density in the probability density distribution curve can be used as the final reliability evaluation result of the liquid rocket engine. The liquid rocket engine reliability evaluation method provided in the embodiment fully utilizes the multi-source data under different levels of tests in the engine development stage, expands the data of the current stage, and can improve the accuracy and reliability of the component reliability evaluation result. Under the premise of not reducing the lower limit of the reliability confidence, the reliability evaluation method based on multi-source information fusion can reduce the number of tests and achieve the purpose of saving funds.

[0049] The embodiment also provides another liquid rocket engine reliability evaluation method, which is implemented on the basis of the above embodiment; the embodiment mainly describes the data acquisition process and the data fusion process under multiple levels of tests.

[0050] The development stage of the engine includes scheme feasibility demonstration, model stage, initial sample stage, sample stage, finalization stage and batch production stage.

[0051] The scheme feasibility demonstration stage is to demonstrate the feasibility of the engine technical scheme, the feasibility of adopting new technologies and economic feasibility before the engine formally enters the engineering development, according to the type planning, professional development and overall demand, with the help of early pre-research results and mature technologies of other types. This stage does not involve reliability evaluation related problems.

[0052] The mockup phase is to design and test the mockup according to the requirements of the overall engine design task and the results of the scheme feasibility demonstration, to initially break through the key technologies of each component, and to determine the engine scheme. In the mockup design, the reliability outline needs to be prepared, the performance and structural reliability evaluation methods need to be selected, the reliability indicators need to be estimated and allocated, and the reliability of the main components of the engine needs to meet the requirements in the design review.

[0053] In the preliminary sample phase and the sample phase, the selected engine scheme is respectively subjected to ground test and comprehensive test including flight test. The two phases may simultaneously include related assembly tests (including all tests on individual elements, components and sub-systems or half-systems composed of components of the engine) and whole machine tests.

[0054] In the final sample phase, the engine design work is summarized, the design is finalized, and the identification test is conducted. The engine is required to pass through several batches of production, test and prove that the engine performance is stable and the structure is reliable. In the batch production phase, the engine batch production is carried out in cooperation with the production plant, technical problems in batch production are handled, and batch sampling test and sampling flight test of the engine are participated. The two phases mainly face a large number of whole machine test of the engine.

[0055] In summary, the reliability test types that may be involved in different development phases of the engine are shown in Table 1.

[0056] Table 1

[0057]

[0058] In the embodiments of the present application, the finally statistically different levels of test data are not distinguished from the development phases, that is, the data of all phases are integrated to obtain the environmental reliability evaluation data of the three levels of tests.

[0059] Further, referring to Figure 3 The above step of obtaining the environmental reliability evaluation data of the component level test in the development phase of the liquid rocket engine includes: obtaining reliability evaluation data of a plurality of reliability analysis units corresponding to each sub-component in the liquid rocket engine; converting the reliability evaluation data of the plurality of reliability analysis units into success-failure equivalent test data respectively; converting the plurality of success-failure equivalent test data into reliability evaluation data of the sub-component by using a series model method; and obtaining the environmental reliability evaluation data of the whole machine by jointly processing the reliability evaluation data of the plurality of sub-components according to the correlation of the failure modes of the sub-components.

[0060] The step of obtaining the heterogeneous environment reliability evaluation data under the subsystem level test in the development stage of the liquid rocket engine includes: obtaining the reliability evaluation data corresponding to each subsystem in the liquid rocket engine; and jointly processing the reliability evaluation data corresponding to the plurality of subsystems according to the correlation of the failure modes of the subsystems to obtain the heterogeneous environment reliability evaluation data of the whole machine.

[0061] The step of obtaining the heterogeneous environment reliability evaluation data under the whole machine test in the development stage of the liquid rocket engine includes: performing the whole machine test on the liquid rocket engine to obtain the heterogeneous environment reliability evaluation data of the whole machine.

[0062] Further, the step of jointly processing includes: determining the corresponding reliability model according to the correlation of the failure modes among the plurality of components or subsystems; and calculating the reliability evaluation data of the plurality of components or subsystems according to the reliability model to obtain the heterogeneous environment reliability evaluation data of the whole machine.

[0063] The three test modes are described in detail as follows:

[0064] (1) Reliability evaluation of a single component:

[0065] For a single component, there can be multiple reliability analysis units according to different failure mechanisms, and the reliability information obtained by each analysis unit can be first converted into equivalent success-failure test data:

[0066] ; ;

[0067] In the formula, n is the equivalent success-failure test number of the unit, f is the failure number of the unit in the equivalent test number, RT is the lower limit of reliability confidence under the confidence level , is the cumulative probability density function of the Beta distribution.

[0068] The series reliability model considers that any reliability analysis unit fails, that is, the component fails. The Lindstrom-Maddens (L-M) method is used to convert the equivalent test numbers of multiple units into the equivalent test number of the component, that is,

[0069] ; ;

[0070] In the formula, N and F are the equivalent test number and failure number of the component, respectively.

[0071] (2) Reliability evaluation of the whole of the component level (subsystem level, half-system level) test:

[0072] Let liquid rocket engine be composed of n components (or n subsystems), where the reliability of the component with the lowest reliability is According to the correlation between engine components and failure modes, the reliability mathematical model under different correlation degrees can be obtained:

[0073] The completely unrelated reliability model:

[0074]

[0075] Weakly correlated reliability model:

[0076]

[0077] Moderately correlated reliability model:

[0078]

[0079] Strongly correlated reliability model:

[0080]

[0081] Completely correlated reliability model:

[0082]

[0083] In the formula , , , , is the reliability of the engine structure or system under different correlation degrees of reliability model, is the reliability of the component or component, is the number of units or the number of components that make up the structure. Thereafter, the selected formula in the above model is combined with the L-M method to obtain the equivalent test frequency and failure frequency of the reliability model considering correlation.

[0084] The above reliability refers to the probability of a product completing a specified function under specified conditions. After obtaining the posterior reliability distribution of the product, its reliability estimate can be obtained in a certain way.

[0085] It should be noted that the continuous limit model can not be used in the reliability evaluation of the overall component level (subsystem level, half system level) test, and is replaced by the series reliability model or the minimum value reliability model.

[0086] (3) The reliability evaluation of the whole machine test can be directly calculated from the success or failure results.

[0087] In another embodiment, the reliability of the engine system within a certain research stage can also be evaluated:

[0088] For example, for a certain engine development stage, if there is only a single order of magnitude of test, the engine reliability of this stage is the reliability test estimation result of this order of magnitude.

[0089] If there are engine test of different orders of magnitude in this stage, since the prior information obtained in each stage is binomial distribution (Beta distribution), the overall reliability distribution of this stage can be obtained by weighting fusion of the overall engine reliability estimation results obtained in each order of magnitude.

[0090] For example, there is only component level test in the sample stage, the engine reliability in the sample stage can be obtained by combining the above-mentioned models in the plurality of reliability mathematical models according to the correlation, or it can be regarded as Figure 3 the dashed box of component level test; there are three orders of magnitude of test in the preliminary sample stage, each order of magnitude is evaluated separately, and then an overall engine reliability is obtained by fusion, and the same is true for the sample stage; there is only a large number of overall engine test in the final sample stage, and the overall engine reliability evaluation data can be directly obtained.

[0091] In the embodiment, the step of fusing the heterogeneous environment reliability evaluation data under the three levels of test to determine the reliability prior distribution information comprises: weighting fusing the heterogeneous environment reliability evaluation data under the three levels of test to obtain the reliability prior distribution information.

[0092] Further, the Bayesian decision theory can be used to fuse the reliability prior distribution information and the test information to calculate the posterior distribution density of the engine reliability as the reliability posterior distribution information.

[0093] For example, the liquid rocket engine has m types of multi-source reliability information, that is, the above-mentioned heterogeneous environment reliability evaluation data under a plurality of test levels; wherein the prior distribution determined by the i-th type of reliability information (i.e. the above-mentioned heterogeneous environment reliability evaluation data) is , if the reliability of the m types of multi-source reliability information is known , then the prior distribution after the multi-source reliability information fusion based on the reliability method is :

[0094] ;

[0095] In the formula, here m=3 corresponds to three levels of test.

[0096] After obtaining the field test information of a certain type of liquid rocket engine , the Bayesian decision theory is used to calculate the reliability posterior distribution information of the engine in combination with the prior distribution result :

[0097] ;

[0098] wherein X is engine test information, represents engine structure reliability, is engine reliability prior distribution information, represents the probability density function of test information X when the reliability R is constant, and the expression of the prior distribution is combined to obtain:

[0099]

[0100] wherein , .

[0101] Let , and there is:

[0102] .

[0103] The liquid rocket engine reliability evaluation method provided in the embodiments of the present application can be used to evaluate the reliability in a certain development stage by using the above method, or can be used to comprehensively evaluate the reliability in all development stages (in this case, the development stages are not distinguished). In the embodiments of the present application, the environmental reliability evaluation data in different levels of tests in different development stages of the engine is integrated into the final reliability evaluation, and a fusion method of reliability information in multiple different levels of tests and different development stages is proposed.

[0104] Based on the above method embodiments, the embodiments of the present application further provide a liquid rocket engine reliability evaluation device, as shown in Figure 4 , the device comprises: a data acquisition module 402, configured to acquire environmental reliability evaluation data in three levels of tests in a development stage of a liquid rocket engine; the three levels of tests comprise component-level tests, subsystem-level tests and whole-machine tests carried out in the development stage of the engine; a credibility determination module 404, configured to determine the credibility of the prior reliability corresponding to the three levels of tests based on the environmental reliability evaluation data in the three levels of tests; a prior distribution determination module 406, configured to fuse the environmental reliability evaluation data in the three levels of tests when the credibility meets the standard, and determine reliability prior distribution information; a posterior distribution determination module 408, configured to fuse the reliability prior distribution information and test information, and obtain reliability posterior distribution information; and a result determination module 410, configured to determine a final reliability evaluation result of the liquid rocket engine based on the reliability posterior distribution information.

[0105] Further, the above-mentioned different-environment reliability evaluation data includes life type, success-failure type and degradation type data of each component of the engine in different levels of tests in each development stage of the life cycle and different from the field use environment conditions.

[0106] Further, the data acquisition module 402 is configured to acquire, for each subassembly in the liquid rocket engine, reliability evaluation data of a plurality of reliability analysis units corresponding to the subassembly, respectively convert the reliability evaluation data of the plurality of reliability analysis units into success-failure type equivalent test data, convert the plurality of success-failure type equivalent test data into reliability evaluation data of the subassembly by using a series model method, and jointly process the reliability evaluation data of the plurality of subassemblies according to the correlation of failure modes of the subassemblies to obtain different-environment reliability evaluation data of the whole machine.

[0107] For each sub-system in the liquid rocket engine, the reliability evaluation data corresponding to the sub-system is acquired; and the reliability evaluation data corresponding to the plurality of sub-systems is jointly processed according to the correlation of failure modes of the sub-systems to obtain the different-environment reliability evaluation data of the whole machine.

[0108] The whole machine test is performed on the liquid rocket engine to obtain the different-environment reliability evaluation data of the whole machine.

[0109] Further, the data acquisition module 402 is configured to perform the step of joint processing, including determining a corresponding reliability model according to the correlation of failure modes among the plurality of subassemblies or sub-systems, and calculating the reliability evaluation data of the plurality of subassemblies or sub-systems according to the reliability model to obtain the different-environment reliability evaluation data of the whole machine.

[0110] Further, the prior distribution determination module 406 is configured to perform weighted fusion on the different-environment reliability evaluation data in the three levels of tests to obtain reliability prior distribution information.

[0111] Further, the above-mentioned each development stage includes a sample stage, a preliminary sample stage, a sample stage, a sample stage, and a batch production stage.

[0112] Further, the posterior distribution determination module 408 is configured to fuse the reliability prior distribution information and the test information by using the Bayesian decision theory to calculate reliability posterior distribution information of the engine.

[0113] The device provided by the embodiment of the application has the same implementation principle and technical effects as the foregoing method embodiment, and for brevity of description, the part of the device embodiment not mentioned can be referred to the corresponding content in the foregoing method embodiment.

[0114] The embodiment of the application further provides an electronic device, such as Figure 5As shown, it is a structural schematic diagram of the electronic device, wherein the electronic device comprises a processor 51 and a memory 50, the memory 50 stores computer executable instructions capable of being executed by the processor 51, and the processor 51 executes the computer executable instructions to realize the above method.

[0115] In Figure 5 In the embodiment shown, the electronic device further comprises a bus 52 and a communication interface 53, wherein the processor 51, the communication interface 53 and the memory 50 are connected through the bus 52.

[0116] The memory 50 can contain a high-speed random access memory (RAM) and can also include a non-volatile memory, such as at least one disk memory. The communication connection between the system network element and at least one other network element is realized through at least one communication interface 53 (which can be wired or wireless), and the Internet, a wide area network, a local area network, a metropolitan area network, etc. can be used. The bus 52 can be an ISA (Industry Standard Architecture) bus, a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus, etc. The bus 52 can be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 5 In the figure, only one bidirectional arrow is used to represent only one bus or one type of bus.

[0117] The processor 51 can be an integrated circuit chip with processing capability. In implementation process, each step of the above method can be completed by integrated logic circuit of hardware in the processor 51 or by instructions in the form of software. The processor 51 described above can be a general processor, including a central processing unit (CPU), a network processor (NP), etc.; can also be a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field-programmable gate array (FPGA) or other programmable logic device, a discrete gate or transistor logic device, a discrete hardware component. The general processor can be a microprocessor or the processor can also be any conventional processor. The steps of the method disclosed in combination with the embodiments of the present application can be directly embodied as a hardware code processor to execute, or be executed by a combination of hardware and software modules in the code processor. The software module can be located in a random access memory, a flash memory, a read-only memory, a programmable read-only memory or an electrically erasable programmable memory, a register, or other mature storage medium in the art. The storage medium is located in the storage, and the processor 51 reads the information in the storage, and combines the hardware to complete the steps of the method of the foregoing embodiments.

[0118] The embodiment of the present application further provides a computer readable storage medium, which stores computer executable instructions. When the computer executable instructions are called and executed by a processor, the computer executable instructions cause the processor to implement the above method. For details, refer to the foregoing method embodiments, which will not be described here.

[0119] The computer program product of the method, device and electronic equipment provided by the embodiment of the present application includes a computer readable storage medium storing program codes. The instructions included in the program codes can be used to execute the method described in the foregoing method embodiments. For details, refer to the method embodiments, which will not be described here.

[0120] Unless otherwise specifically stated, the relative steps, numerical expressions and values of the components and steps set forth in these embodiments do not limit the scope of the present application.

[0121] If the functions are implemented in the form of software function units and sold or used as independent products, they can be stored in a nonvolatile computer readable storage medium executable by a processor. Based on this understanding, the technical solutions of the present application essentially or the parts that contribute to the prior art or parts of the technical solutions can be embodied in the form of a software product. The computer software product is stored in a storage medium and includes a number of instructions for causing a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present application. The aforementioned storage medium includes: a U disk, a mobile hard disk, a read-only memory (ROM, Read-Only Memory), a random access memory (RAM, Random Access Memory), a magnetic disk or an optical disk, and various media that can store program codes.

[0122] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0123] Finally, it should be noted that: the above-described embodiments are only specific embodiments of the present application, used to illustrate the technical solutions of the present application, and are not limited thereto, the protection scope of the present application is not limited thereto, although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that any skilled person familiar with the technical field can modify or easily think of changes to the technical solutions described in the foregoing embodiments within the technical scope disclosed by the present application, or make equivalent replacements to part of the technical features; and these modifications, changes or replacements do not make the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and 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 liquid rocket engine reliability assessment, characterized in that, The method comprises: obtaining the heterogeneous environment reliability evaluation data in three levels of tests in the development stage of the liquid rocket engine; the three levels of tests comprise the component level test, the subsystem level test and the whole machine test carried out in the development stage of the engine; determining the reliability of the priori corresponding to the three levels of tests based on the heterogeneous environment reliability evaluation data in the three levels of tests; when the reliability meets the standard, fusing the heterogeneous environment reliability evaluation data in the three levels of tests to determine the reliability priori distribution information; fusing the reliability priori distribution information and the test information to obtain the reliability posteriori distribution information; determining the final reliability evaluation result of the liquid rocket engine based on the reliability posteriori distribution information.

2. The method of claim 1, wherein, The heterogeneous environment reliability evaluation data comprises the life type, success type and degradation type data of the engine components in different levels of tests in different development stages of the life cycle.

3. The method of claim 2, wherein, The step of obtaining the heterogeneous environment reliability evaluation data in the component level test in the development stage of the liquid rocket engine comprises: obtaining the reliability evaluation data of a plurality of reliability analysis units corresponding to each component of the liquid rocket engine; converting the reliability evaluation data of the plurality of reliability analysis units into equivalent test data of the success type; converting the equivalent test data of the success type of the plurality of reliability analysis units into the reliability evaluation data of the component by using the series model method; and obtaining the heterogeneous environment reliability evaluation data of the whole machine by jointly processing the reliability evaluation data of the plurality of components according to the correlation of the failure modes of the components; The step of obtaining the heterogeneous environment reliability evaluation data in the subsystem level test in the development stage of the liquid rocket engine comprises: obtaining the reliability evaluation data corresponding to each subsystem of the liquid rocket engine; and obtaining the heterogeneous environment reliability evaluation data of the whole machine by jointly processing the reliability evaluation data corresponding to the plurality of subsystems according to the correlation of the failure modes of the subsystems. The step of obtaining the heterogeneous environment reliability evaluation data in the whole machine test in the development stage of the liquid rocket engine comprises: carrying out the whole machine test on the liquid rocket engine to obtain the heterogeneous environment reliability evaluation data of the whole machine.

4. The method of claim 3, wherein, The step of jointly processing comprises: determining the corresponding reliability model according to the correlation of the failure modes among the plurality of components or subsystems; calculating the reliability evaluation data of the plurality of components or subsystems according to the reliability model to obtain the heterogeneous environment reliability evaluation data of the whole machine.

5. The method of claim 1, wherein, The step of fusing the heterogeneous environment reliability evaluation data in the three levels of tests to determine the reliability priori distribution information comprises: weighting and fusing the heterogeneous environment reliability evaluation data in the three levels of tests to obtain the reliability priori distribution information.

6. The method of claim 2, wherein, The development stages comprise the sample stage, the preliminary sample stage, the sample stage, the final sample stage and the batch production stage.

7. The method of claim 1, wherein, The step of fusing the reliability priori distribution information and the test information to obtain the reliability posteriori distribution information comprises: The reliability prior distribution information and the test information are fused by using Bayesian decision theory to calculate the reliability posterior distribution information of the engine.

8. A liquid rocket engine reliability assessment device, characterized by, The device comprises: The data acquisition module is configured to acquire the heterogeneous environment reliability evaluation data of the liquid rocket engine in the three-level tests in the development stage of the engine; the three-level tests include the component-level test, the subsystem-level test and the whole engine test in the development stage of the engine; The credibility determination module is configured to determine the credibility of the prior reliability corresponding to the three-level tests based on the heterogeneous environment reliability evaluation data of the three-level tests; The prior distribution determination module is configured to fuse the heterogeneous environment reliability evaluation data of the three-level tests to determine the reliability prior distribution information when the credibility meets the standard; The posterior distribution determination module is configured to fuse the reliability prior distribution information and the test information to obtain the reliability posterior distribution information; The result determination module is configured to determine the final reliability evaluation result of the liquid rocket engine based on the reliability posterior distribution information.

9. An electronic device, comprising: The computer readable storage medium stores computer executable instructions, and the computer executable instructions, when invoked and executed by the processor, cause the processor to implement the method in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The computer readable storage medium stores computer executable instructions, and the computer executable instructions, when invoked and executed by the processor, cause the processor to implement the method in any one of claims 1 to 7.

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