MBSE Integrated Launch Vehicle Model Confidence Assessment Method and Device

Abstract

This invention discloses a method and apparatus for evaluating the confidence level of an integrated MBSE launch vehicle model, comprising: decomposing the launch vehicle system to determine its constituent units and relational elements; when the decomposition method of the launch vehicle system is uncertain, converting the MBSE confidence level analysis into an analysis of the confidence level of the launch vehicle MBSE model system under a first objective condition; under the first objective condition, obtaining the number of similarities and differences between the elements of the launch vehicle MBSE model and the elements of the actual system; under a second objective condition, calculating all possible values ​​of the similarities and differences; and under a third objective condition, calculating and deriving the probability mass function of the number of similarities and differences; and obtaining the consistency confidence level evaluation result of the MBSE launch vehicle model based on the probability mass function of the total number of similarities and differences, thereby realizing the analysis of the confidence level of the integrated MBSE launch vehicle model and improving the accuracy of evaluating the launch vehicle model.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology, and in particular relates to a confidence assessment method and device for an integrated MBSE launch vehicle model. Background Technology

[0002] Model-based systems engineering (MBSE) is the formal application of modeling that supports system requirements, design, analysis, verification, and validation activities, starting from the conceptual design phase and continuing into the later stages of development and lifecycle. The transformation to an MBSE-based development model for launch vehicles enables the accurate and unambiguous communication of launch vehicle requirements, improves launch vehicle design quality, achieves full lifecycle collaboration for launch vehicles, and enhances technical state control capabilities, thereby significantly improving the development efficiency of complex launch vehicle systems.

[0003] Launch vehicle models are digital representations of real-world launch vehicle systems. Currently, there are problems with launch vehicle models built based on MBSE (Multi-Model Space Array).

[0004] 1) Is the launch vehicle model correctly constructed?

[0005] 2) What are the methods and metrics for evaluating the correctness of launch vehicle models?

[0006] Currently, there is a lack of specific strategies to address the two issues mentioned above. The accuracy of launch vehicle models relies heavily on expert experience and the technical skill of the designers. The lack of objective evaluation criteria leads to unclear optimization strategies and directions. Consequently, the accuracy of the established launch vehicle models cannot be assessed.

[0007] Therefore, it is necessary to propose a confidence assessment method for the MBSE integrated launch vehicle model. Summary of the Invention

[0008] The purpose of this invention is to provide a method, apparatus, equipment, and medium for evaluating the confidence level of an integrated MBSE launch vehicle model, to assess the accuracy of the MBSE launch vehicle model, to clarify the evaluation method and measurement indicators, and to realize the analysis of the confidence level of the integrated MBSE launch vehicle model and to evaluate the correctness of the launch vehicle model.

[0009] This invention provides a confidence assessment method for an integrated MBSE launch vehicle model, comprising:

[0010] Decomposition of the launch vehicle system: Determine the constituent units and relational elements of the launch vehicle system. The constituent units include the physical components and functional elements of the launch vehicle, and the relational elements include the relationships between the physical components of the launch vehicle system and the relationships between the functional elements of the launch vehicle system.

[0011] When the decomposition method of the launch vehicle system is uncertain, the analysis of MBSE confidence is transformed into an analysis of the confidence of the launch vehicle MBSE model system under the first objective condition;

[0012] Under the first objective condition, obtain the number of similarities and differences between the elements of the launch vehicle MBSE model and the elements of the real system; under the second objective condition, calculate all possible values ​​of the similarities and differences elements; and under the third objective condition, calculate and derive the probability mass function of the number of similarities and differences elements.

[0013] The consistency confidence assessment results of the MBSE launch vehicle model are obtained based on the probability mass function of the overall number of similar and dissimilar elements of the launch vehicle.

[0014] Preferably, the first objective condition includes: assuming that the real launch vehicle system is decomposed into N non-overlapping small launch vehicle element units, and K element units have been established in the launch vehicle MBSE, and comparing the elements of the launch vehicle MBSE model with the elements of the real launch vehicle system among the element units established in the launch vehicle MBSE, T elements with similarities and differences are obtained; wherein, the element units established in the launch vehicle MBSE include the physical elements, functional elements and relational elements of the launch vehicle.

[0015] Preferably, the second target condition includes:

[0016] Based on the first objective condition, let the number of similarities and differences among the elements of the launch vehicle model be a random variable X, and calculate all possible values ​​x for the similarities and differences among the elements. i , 1≤i≤n; the formula for calculating the number of similar and dissimilar elements is:

[0017]

[0018] Preferably, the third target condition includes:

[0019] Based on the second objective condition, calculate the probability p of the number of K elements of the inspected launch vehicle, of which T are abnormal elements. i :

[0020]

[0021] Preferably, the process of obtaining the consistency confidence assessment result of the MBSE launch vehicle model based on the probability mass function of the total number of similar and dissimilar elements of the launch vehicle includes:

[0022] The estimate is obtained based on the probability mass function of the number of similar and dissimilar elements in the overall launch vehicle. and interval estimation [p γ ,p 1-γ ],

[0023]

[0024] Upper confidence limit for one side:

[0025] p γ =p H ,

[0026] Where, p H satisfy

[0027] One-sided confidence lower limit:

[0028] p γ =p L ,

[0029] Where, p L satisfy PH represents the upper confidence limit, PL represents the lower confidence limit, and Py represents the probability of having a confidence level of y.

[0030] Preferably, the physical components of the launch vehicle include: a structural system, a propulsion system, and an electrical system; the functional components include: load-bearing function, separation function, propulsion function, continuous propellant supply function, attitude adjustment function, control function, measurement and data management function, external measurement function, safety control function, power supply and distribution function, measurement, launch and control function, and auxiliary function.

[0031] This invention also provides an MBSE integrated launch vehicle model confidence assessment device, comprising:

[0032] The decomposition module is used to determine the constituent units and relational elements of the launch vehicle system. The constituent units include physical components and functional elements of the launch vehicle, and the relational elements include the relationships between the physical components of the launch vehicle system and the relationships between the functional elements of the launch vehicle system.

[0033] The MBSE model is used when the decomposition method of the launch vehicle system is uncertain, and the analysis of the confidence of MBSE is transformed into the analysis of the confidence of the launch vehicle MBSE model system under the first objective condition.

[0034] The calculation module is used to obtain the number of similarities and differences between the elements of the launch vehicle MBSE model and the elements of the real system under the first objective condition, calculate all possible values ​​of the similarities and differences under the second objective condition, and calculate and derive the probability mass function of the number of similarities and differences under the third objective condition; and obtain the consistency confidence assessment result of the MBSE launch vehicle model based on the probability mass function of the total number of similarities and differences of the launch vehicle.

[0035] The present invention also provides an electronic device, characterized in that it comprises:

[0036] The memory is used to store the processing program;

[0037] The processor, when executing the processing program, implements the MBSE integrated launch vehicle model confidence assessment method as described above.

[0038] The present invention also provides a computer-readable storage medium storing a processing program, which, when executed by a processor, implements the MBSE integrated launch vehicle model confidence assessment method as described above.

[0039] The advantages of this invention compared to the prior art are:

[0040] The MBSE integrated launch vehicle model confidence assessment method provided by this invention evaluates the accuracy of the MBSE launch vehicle model, clarifies the assessment method and measurement indicators, enables the analysis of the confidence of the MBSE integrated launch vehicle model, and improves the accuracy of the evaluation of the launch vehicle model. Attached Figure Description

[0041] Figure 1 This is a flowchart of the MBSE integrated launch vehicle model confidence assessment method in an embodiment of the present invention. Detailed Implementation

[0042] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0043] In the process of building launch vehicle models for MBSE, the modeling engineers' experience and cognitive level are the main factors. Different designers may build different launch vehicle models for the same system. How to evaluate the correctness of the launch vehicle model and how to measure the consistency between the built launch vehicle model and the real system are problems that need to be solved.

[0044] Due to the complexity of the system, it is impossible to verify and check every component and function against the launch vehicle MBSE model one by one, which results in a huge workload. Therefore, a method is needed to quickly, efficiently and accurately analyze the correctness of the launch vehicle MBSE model.

[0045] like Figure 1 As shown, this invention provides a confidence assessment method for an integrated MBSE launch vehicle model, comprising:

[0046] S1: Decomposition of the launch vehicle system: Determine the constituent units and relational elements of the launch vehicle system. The constituent units include physical components and functional elements of the launch vehicle. The relational elements include the relationships between the physical components of the launch vehicle system and the relationships between the functional elements of the launch vehicle system. The physical components of the launch vehicle include: structural system, propulsion system, and electrical system. The functional elements include support and load-bearing functions, separation functions, propulsion functions, continuous propellant supply functions, attitude adjustment functions, control functions, measurement and data management functions, external measurement functions, safety control functions, power supply and distribution functions, measurement, launch and control functions, and auxiliary functions.

[0047] For example, launch vehicles can be divided into the following table

[0048] Table 1 Physical elements of launch vehicles

[0049]

[0050] Table 2 Functional Elements of Launch Vehicles

[0051]

[0052]

[0053] Table 3. Relationship Elements of Launch Vehicles

[0054] Serial Number Relationship Name FROM TO 1. Installation interface structure Separation 2. Installation interface structure structure 3. Installation interface structure engine 4. Installation interface structure electric 5. control signals electric power 6. control signals electric Separation 7. …… …… ……

[0055] S2: When the decomposition method of the launch vehicle system is uncertain, the analysis of the MBSE confidence level is transformed into an analysis of the confidence level of the launch vehicle MBSE model system under the first objective condition. Under the first objective condition, the number of similarities and differences between the elements of the launch vehicle MBSE model and the elements of the real system is obtained. Under the second objective condition, all possible values ​​of the similarities and differences are calculated. Under the third objective condition, the probability mass function for deriving the number of similarities and differences is calculated. The first objective condition includes: assuming that the real launch vehicle system is decomposed into N disjoint launch vehicle element units, and K element units have been established in the launch vehicle MBSE. Among the element units established in the launch vehicle MBSE, the elements of the launch vehicle MBSE model are compared with the elements of the real launch vehicle system, and T similarities and differences are obtained. Among them, the element units established in the launch vehicle MBSE include the physical elements, functional elements, and relational elements of the launch vehicle.

[0056] Those skilled in the art will understand that due to different decomposition methods and understandings of launch vehicle systems, there is a certain degree of uncertainty. Based on uncertainty analysis, the MBSE confidence analysis problem is transformed into: Assuming the real launch vehicle system is decomposed into N disjoint launch vehicle element units, as shown in Tables 1, 2, and 3, and K element units have been established in the launch vehicle MBSE, and among the element units established in the launch vehicle MBSE, T elements are found to be inconsistent between the launch vehicle MBSE model and the real system. Analyze the confidence of the launch vehicle MBSE model system under the above conditions;

[0057] Specifically, S21: Under condition S2, let the number of inconsistent elements in the launch vehicle model be a random variable X, and calculate all possible values ​​x of the inconsistent elements. i , 1≤i≤n; the formula for calculating the number of inconsistent elements is:

[0058] The above constitutes the second objective condition.

[0059] S22: Under condition S21, calculate the probability p of having checked K elements, of which T elements are inconsistent. i The calculation is derived using the following formula:

[0060]

[0061] Where T≤i≤N-K+T, in the formula,

[0062]

[0063] Simplifying, we get the following formula:

[0064] The above constitutes the third objective condition.

[0065] The probability mass function (pmf) for the number of inconsistent elements in the population is obtained.

[0066] S4: The consistency confidence assessment results of the MBSE launch vehicle model are obtained based on the probability mass function of the overall number of similar and dissimilar elements of the launch vehicle, specifically including:

[0067] The estimate is obtained based on the probability mass function of the number of similar and dissimilar elements in the overall launch vehicle. and interval estimation [p γ ,p 1-γ ],

[0068]

[0069] Upper confidence limit for one side:

[0070] pγ =p H ,

[0071] Where, p H satisfy

[0072] One-sided confidence lower limit:

[0073] p γ =p L ,

[0074] Where, p L satisfy PH represents the upper confidence limit, PL represents the lower confidence limit, and Py represents the probability of having a confidence level of y.

[0075] This invention also provides an MBSE integrated launch vehicle model confidence assessment device, comprising:

[0076] The decomposition module is used to determine the constituent units and relational elements of the launch vehicle system. The constituent units include physical components and functional elements of the launch vehicle, and the relational elements include the relationships between the physical components of the launch vehicle system and the relationships between the functional elements of the launch vehicle system.

[0077] The MBSE model is used when the decomposition method of the launch vehicle system is uncertain, and the analysis of the confidence of MBSE is transformed into the analysis of the confidence of the launch vehicle MBSE model system under the first objective condition.

[0078] The calculation module is used to obtain the number of similarities and differences between the elements of the launch vehicle MBSE model and the elements of the real system under the first objective condition, calculate all possible values ​​of the similarities and differences under the second objective condition, and calculate and derive the probability mass function of the number of similarities and differences under the third objective condition; and obtain the consistency confidence assessment result of the MBSE launch vehicle model based on the probability mass function of the total number of similarities and differences of the launch vehicle.

[0079] Based on the same concept, the present invention provides an electronic device comprising:

[0080] The memory is used to store the processing program;

[0081] The processor, when executing the processing program, implements the MBSE integrated launch vehicle model confidence assessment method as described in the embodiments of the present invention.

[0082] The present invention provides a readable storage medium storing a processing program, which, when executed by a processor, implements the MBSE integrated launch vehicle model confidence assessment method as described in the embodiments of the present invention.

[0083] This MBSE integrated launch vehicle model confidence assessment device can vary considerably depending on its configuration or performance. It may include one or more central processing units (CPUs) and memory, and one or more storage media (e.g., one or more mass storage devices) for storing applications or data. The memory and storage media can be temporary or persistent storage. The programs stored on the storage media may include one or more modules, each of which may include a series of instruction operations on the MBSE integrated launch vehicle model confidence assessment device.

[0084] Furthermore, the processor can be configured to communicate with the storage medium and execute a series of instruction operations from the storage medium on the MBSE integrated launch vehicle model confidence assessment device.

[0085] An MBSE integrated launch vehicle model confidence assessment device may also include one or more power supplies, one or more wired or wireless network interfaces, one or more input / output interfaces, and / or one or more operating systems, such as Windows Server, Vista, etc.

[0086] This invention also provides a computer-readable storage medium storing a computer program that, when executed by one or more processors, implements the MBSE integrated launch vehicle model confidence assessment method as described in Embodiment 1. If the modules in Embodiment 2 are implemented as software functional modules and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this invention, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in software form. The computer-readable storage medium can be a non-volatile computer-readable storage medium or a volatile computer-readable storage medium. The computer-readable storage medium stores instructions that, when executed on a computer, cause the computer to perform the steps of the MBSE integrated launch vehicle model confidence assessment in Embodiment 1.

[0087] Those skilled in the art will understand that the technical solution of the present invention, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in software. This computer software is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as a USB flash drive, a portable hard drive, a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk. Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working process of the device described above can be referred to the corresponding process in the foregoing method embodiments, and will not be repeated here.

[0088] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A confidence assessment method for an MBSE integrated launch vehicle model, characterized in that, include: Decomposition of the launch vehicle system: Determine the constituent units and relational elements of the launch vehicle system. The constituent units include the physical components and functional elements of the launch vehicle, and the relational elements include the relationships between the physical components of the launch vehicle system and the relationships between the functional elements of the launch vehicle system. When the decomposition method of the launch vehicle system is uncertain, the analysis of MBSE confidence is transformed into an analysis of the confidence of the launch vehicle MBSE model system under the first objective condition; Under the first objective condition, obtain the number of similarities and differences between the elements of the launch vehicle MBSE model and the elements of the real system; under the second objective condition, calculate all possible values ​​of the similarities and differences elements; and under the third objective condition, calculate and derive the probability mass function of the number of similarities and differences elements. The consistency confidence assessment results of the MBSE launch vehicle model are obtained based on the probability mass function of the total number of similar and dissimilar elements of the launch vehicle. The first objective condition includes: assuming that the real launch vehicle system is decomposed into N non-overlapping small launch vehicle element units, and K element units have been established in the launch vehicle MBSE. Among the element units established in the launch vehicle MBSE, the elements of the launch vehicle MBSE model are compared with the elements of the real launch vehicle system, and T similar and different elements are obtained. Among them, the element units established in the launch vehicle MBSE include the physical elements, functional elements and relational elements of the launch vehicle. The second objective condition includes: Based on the first objective condition, let the number of similarities and differences among the elements of the launch vehicle model be a random variable X, and calculate all possible values ​​of the similarities and differences elements. , The formula for calculating the number of similar and dissimilar elements is: ； The third objective condition includes: Based on the second objective condition, calculate the probability that among the K elements of the inspected launch vehicle, T are abnormal elements. : 。 2. The MBSE integrated launch vehicle model confidence assessment method as described in claim 1, characterized in that, The consistency confidence assessment results of the MBSE launch vehicle model obtained based on the probability mass function of the total number of similar and dissimilar elements of the launch vehicle include: The estimate is obtained based on the probability mass function of the number of similar and dissimilar elements in the overall launch vehicle. and interval estimation , ， Upper confidence limit for one side: ， in, satisfy , One-sided confidence lower limit: ， in, satisfy , PH represents the upper confidence limit, PL represents the lower confidence limit, and Py represents the probability of having a confidence level of y.

3. The confidence assessment method for the MBSE integrated launch vehicle model as described in claim 1, characterized in that, The physical components of the launch vehicle include: structural system, propulsion system, and electrical system; the functional components include: support and load-bearing function, separation function, propulsion function, continuous propellant supply function, attitude adjustment function, control function, measurement and data management function, external measurement function, safety control function, power supply and distribution function, measurement, launch and control function, and auxiliary function.

4. A MBSE integrated launch vehicle model confidence assessment device, characterized in that, The method for evaluating the confidence level of the MBSE integrated launch vehicle model as described in claim 1 includes: The decomposition module is used to determine the constituent units and relational elements of the launch vehicle system. The constituent units include physical components and functional elements of the launch vehicle, and the relational elements include the relationships between the physical components of the launch vehicle system and the relationships between the functional elements of the launch vehicle system. The MBSE model is used when the decomposition method of the launch vehicle system is uncertain, and the analysis of the confidence of MBSE is transformed into the analysis of the confidence of the launch vehicle MBSE model system under the first objective condition. The calculation module is used to obtain the number of similarities and differences between the elements of the launch vehicle MBSE model and the elements of the real system under the first objective condition, calculate all possible values ​​of the similarities and differences under the second objective condition, and calculate and derive the probability mass function of the number of similarities and differences under the third objective condition; and obtain the consistency confidence assessment result of the MBSE launch vehicle model based on the probability mass function of the total number of similarities and differences of the launch vehicle.

5. An electronic device, characterized in that, include: The memory is used to store the processing program; A processor that, when executing the processing program, implements the MBSE integrated launch vehicle model confidence assessment method as described in any one of claims 1 to 3.

6. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a processing program that, when executed by a processor, implements the MBSE integrated launch vehicle model confidence assessment method as described in any one of claims 1 to 3.

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