MBSE-based hydrogen energy powered aircraft airworthiness analysis method and device

Abstract

The invention relates to the technical field of aircraft design, and discloses a hydrogen energy powered aircraft airworthiness analysis method and device based on MBSE, and the method comprises the steps: building a modeling architecture standard of a hydrogen energy aircraft power system; according to the modeling architecture standard of the target hydrogen energy aircraft power system, modeling each substructure of the target hydrogen energy aircraft power system to obtain a target hydrogen energy aircraft power system model composed of a plurality of substructure models; obtaining airworthiness regulations; each requirement in the airworthiness regulations is represented by using a physical structure to realize a specific function; and analyzing whether each substructure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulation or not to obtain an analysis result. According to the method, potential differences and conflicts between the target hydrogen energy aircraft power system and the existing airworthiness regulations can be visually and accurately identified, and the hydrogen energy power aircraft certification efficiency is improved.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft design, and for example, to an MBSE-based airworthiness analysis method and device for hydrogen-powered aircraft. Background Art

[0002] As the requirements of the passenger and cargo transportation industry continue to rise, the growth rate of civil aviation will remain stable in the future. In addition to the traditional requirements of economic efficiency, in order to achieve the goals of carbon peak and carbon neutrality, green and environmentally friendly hydrogen-powered aircraft have received close attention from domestic and foreign aviation manufacturing industries and research institutions. At present, many countries around the world are actively engaged in the research of hydrogen-powered aircraft and their power systems, including China's "Lingque H", Germany's "H2FLY", France's ZEROe, and the United States' "Phantom Eye", all of which have completed or are carrying out design and verification work.

[0003] For civil aircraft, according to the regulations of CCAR-21 for operating aircraft, aircraft must pass the airworthiness certification of the civil aviation authorities before being put into use. Hydrogen-powered aircraft are aircraft with significant novel design features. Unlike traditional aircraft that store fuel in fuel tanks, hydrogen-powered aircraft rely on liquid hydrogen to achieve the same function. Therefore, for existing airworthiness standards, many clauses and requirements are no longer applicable. Such design features require the applicant to analyze, confirm and form the certification basis and corresponding special conditions as soon as possible to ensure that such aircraft have a safety level equivalent to the current airworthiness regulations.

[0004] The formation and confirmation process of the airworthiness certification basis of traditional aircraft is mainly based on documents. However, there are many hydrogen-powered configurations, and different types of aircraft have scattered and complex characteristics in design and implementation, which may show potential differences in airworthiness certification requirements. Traditional document-based airworthiness analysis and design methods are difficult to fully capture potential design details. Such differences are easily overlooked in the airworthiness analysis process, ultimately leading to repeated changes in the model's airworthiness design. In addition, the natural language contained in the document has inherent ambiguity and ambiguity when conveying technical details, which may lead to misunderstandings of the intent and requirements of the airworthiness analysis, thereby affecting the accuracy of the design and the efficiency of airworthiness certification. Therefore, at this stage, there is an urgent need for a more precise, dynamic and standard method to analyze, identify and manage these potential differences to ensure that the airworthiness certification process for hydrogen-powered aircraft is correct, comprehensive and efficient.

[0005] The current civil aviation industry is facing dual challenges of energy and environment, and hydrogen power is a key technical path to address this problem. The existing civil aircraft airworthiness regulations have potential applicability differences and incomplete coverage of the design features of hydrogen-powered aircraft, so they cannot directly form the basis for the airworthiness certification of hydrogen-powered aircraft. Summary of the invention

[0006] In order to provide a basic understanding of some aspects of the disclosed embodiments, a brief summary is given below. The summary is not an extensive review, nor is it intended to identify key / critical components or delineate the scope of protection of these embodiments, but rather serves as a prelude to the detailed description that follows.

[0007] The disclosed embodiments provide a method and device for airworthiness analysis of hydrogen-powered aircraft based on MBSE. The formation and confirmation process of the airworthiness certification basis of traditional aircraft is mainly based on documents. The traditional document-based airworthiness analysis and design method is difficult to fully capture potential design details, which are easily overlooked in the airworthiness analysis process. There is a problem of low accuracy in the aircraft airworthiness design review, which results in the need for repeated changes in the aircraft airworthiness design.

[0008] In some embodiments, a method for airworthiness analysis of hydrogen-powered aircraft based on MBSE is provided, wherein the method comprises:

[0009] Establishing a modeling architecture standard for hydrogen-powered aircraft power systems, wherein the architecture standard for hydrogen-powered aircraft power systems includes: performing an architecture analysis on a basic hydrogen-powered aircraft power system according to a physical structure, obtaining multiple substructures, and marking the function corresponding to each substructure, wherein a substructure includes a subsystem or a component;

[0010] Acquire the target hydrogen-powered aircraft power system;

[0011] According to the modeling architecture standard of the target hydrogen-powered aircraft power system, each substructure of the target hydrogen-powered aircraft power system is modeled to obtain a target hydrogen-powered aircraft power system model composed of multiple substructure models;

[0012] Obtain airworthiness regulations;

[0013] Represent each requirement in the airworthiness regulations by a physical structure that achieves a specific function;

[0014] The analysis results are obtained by analyzing whether each substructure model of the target hydrogen-powered aircraft power system meets each requirement in the airworthiness regulations.

[0015] Preferably, by analyzing whether each substructure model of the target hydrogen-powered aircraft power system meets each requirement in the airworthiness regulations, the analysis results are obtained, including:

[0016] Each substructure model traverses the two elements of physical structure and function corresponding to each airworthiness regulation;

[0017] If the substructure model is completely consistent with the physical structure and function elements of the corresponding requirements in the airworthiness regulations, the corresponding requirements are deemed applicable;

[0018] If the substructure model matches one of the two elements of physical structure and function required by the corresponding requirements in the airworthiness regulations, it needs to be evaluated;

[0019] If the substructure model does not match both the physical structure and functional elements of the corresponding requirements in the airworthiness regulations, it is considered not applicable.

[0020] By analyzing whether each substructure model of the target hydrogen-powered aircraft power system meets each requirement of the airworthiness regulations, the analysis results are obtained, including:

[0021] If a substructure model has both analysis results of pending evaluation and not applicable, the analysis results of the substructure model shall be regarded as pending evaluation.

[0022] Preferably, the hydrogen energy power of the hydrogen energy aircraft power system includes: a hydrogen turbofan engine, a hydrogen turbo electric fan engine and a hydrogen fuel cell electric fan engine.

[0023] Preferably, the plurality of substructures include any one or more of: a hydrogen energy fuel system, a lubricating oil system, a turbine engine, a cooling system and a fire protection device.

[0024] Preferably, the function of the hydrogen energy fuel system is to supply energy, the function of the lubricating oil system is to provide lubrication, the function of the turbine engine is to provide power, the function of the cooling system is to control and adjust the temperature, and the function of the fire protection device is to block flames.

[0025] Preferably, the method further comprises:

[0026] Based on the analysis results, the target hydrogen-powered aircraft power system model can be adjusted or the airworthiness regulations can be adaptively modified.

[0027] Preferably, the modeling is performed using SysML.

[0028] In some embodiments, a MBSE-based hydrogen-powered aircraft airworthiness analysis device is disclosed, comprising:

[0029] The standardized architecture module is configured to establish a modeling architecture standard for a hydrogen-powered aircraft power system, wherein the architecture standard for a hydrogen-powered aircraft power system includes: performing an architecture analysis on a basic hydrogen-powered aircraft power system according to a physical structure to obtain a plurality of substructures, and marking a function corresponding to each substructure, wherein a substructure includes a subsystem or a component;

[0030] Establishing a target model module, which is configured to obtain a target hydrogen-powered aircraft power system, modeling each substructure of the target hydrogen-powered aircraft power system according to a modeling architecture standard of the target hydrogen-powered aircraft power system, and obtaining a target hydrogen-powered aircraft power system model composed of a plurality of substructure models;

[0031] A regulation conversion module is configured to obtain airworthiness regulations and represent each requirement in the airworthiness regulations by using a physical structure to implement a specific function;

[0032] The analysis module is configured to analyze whether each substructure model of the target hydrogen-powered aircraft power system meets each requirement in the airworthiness regulations, obtain analysis results, and adjust each substructure model.

[0033] Preferably, the device further includes: an adjustment module configured to adjust the target hydrogen-powered aircraft power system model or adaptively modify the airworthiness regulations according to the analysis results.

[0034] The MBSE-based airworthiness analysis method and device for hydrogen-powered aircraft provided in the embodiments of the present disclosure can achieve the following technical effects:

[0035] The disclosed embodiment converts the target hydrogen-powered aircraft power system and airworthiness regulations into physical structures and functions, and then compares and matches the target hydrogen-powered aircraft power system and airworthiness regulations. In this way, the potential differences and conflicts between the target hydrogen-powered aircraft power system and the existing airworthiness regulations can be intuitively and accurately identified, thereby improving the efficiency of hydrogen-powered aircraft certification.

[0036] The above general description and the following description are exemplary and explanatory only and are not intended to limit the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] One or more embodiments are exemplarily described by corresponding drawings, which do not limit the embodiments. Elements with the same reference numerals in the drawings are shown as similar elements, and the drawings do not constitute a scale limitation, and wherein:

[0038] Figure 1 It is a flow chart of a hydrogen-powered aircraft airworthiness analysis method based on MBSE provided in an embodiment of the present disclosure;

[0039] Figure 2-a is a schematic diagram of the principle of a hydrogen turbofan engine provided by an embodiment of the present disclosure;

[0040] Figure 2-b It is a schematic diagram of the principle of a hydrogen turbo electric fan engine provided by an embodiment of the present disclosure;

[0041] Figure 2-c This is a schematic diagram of the principle of a hydrogen fuel cell electric fan engine provided by an embodiment of the present disclosure;

[0042] Figure 3-a is a schematic diagram of a hydrogen turbofan engine model provided by an embodiment of the present disclosure;

[0043] Figure 3-b is a schematic diagram of a hydrogen turbo electric fan engine model provided by an embodiment of the present disclosure;

[0044] Figure 3-c is a schematic diagram of a hydrogen fuel cell electric fan engine model provided by an embodiment of the present disclosure;

[0045] Figure 4 It is a modeled regulation and screening schematic diagram provided by an embodiment of the present disclosure;

[0046] Figure 5 is a schematic diagram of a basic airworthiness formalization model provided by an embodiment of the present disclosure;

[0047] Figure 6 is a schematic diagram of a regulation applicability screening framework provided by an embodiment of the present disclosure;

[0048] Figure 7 It is a schematic diagram of an analysis flow for analyzing each substructure model of a target hydrogen-powered aircraft power system to meet airworthiness regulations, provided by an embodiment of the present disclosure. DETAILED DESCRIPTION

[0049] In order to be able to understand the features and technical contents of the embodiments of the present disclosure in more detail, the implementation of the embodiments of the present disclosure is described in detail below in conjunction with the accompanying drawings. The attached drawings are for reference only and are not used to limit the embodiments of the present disclosure. In the following technical description, for the convenience of explanation, a full understanding of the disclosed embodiments is provided through multiple details. However, one or more embodiments can still be implemented without these details. In other cases, to simplify the drawings, well-known structures and devices can be simplified for display.

[0050] The following description and accompanying drawings fully illustrate specific embodiments of the present invention so that those skilled in the art can practice them. Other embodiments may include structural, logical, electrical, process and other changes. The examples represent possible changes only. Unless explicitly required, separate components and functions are optional, and the order of operations may vary. The parts and features of some embodiments may be included in or replace the parts and features of other embodiments. The scope of the embodiments of the present invention includes the entire scope of the claims, and all available equivalents of the claims. In this article, each embodiment may be represented individually or generally by the term "invention", which is only for convenience, and if more than one invention is disclosed in fact, it is not intended to automatically limit the scope of the application to any single invention or inventive concept. In this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, without requiring or implying any actual relationship or order between these entities or operations. Moreover, the terms "comprises", "includes" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method or device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method or device. In the absence of further restrictions, the elements defined by the sentence "including a..." do not exclude the presence of other identical elements in the process, method or device including the elements. The various embodiments herein are described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same and similar parts between the various embodiments can be referred to each other. For the methods, products, etc. disclosed in the embodiments, since they correspond to the method part disclosed in the embodiments, the description is relatively simple, and the relevant parts can be referred to the method part description.

[0051] The current civil aviation industry is facing dual challenges of energy and environment, and hydrogen power is a key technical path to address this problem. The existing civil aircraft airworthiness regulations have potential applicability differences and incomplete coverage of the design features of hydrogen-powered aircraft, so they cannot directly form the basis for the airworthiness certification of hydrogen-powered aircraft.

[0052] In order to solve the problems existing in the related art, the embodiment of the present disclosure provides a hydrogen-powered aircraft airworthiness analysis method and device based on MBSE. The target hydrogen-powered aircraft power system and airworthiness regulations are converted into physical structures and functions for representation, and then the target hydrogen-powered aircraft power system and airworthiness regulations are compared and matched for analysis. In this way, the potential differences and conflicts between the target hydrogen-powered aircraft power system and the existing airworthiness regulations can be intuitively and accurately identified, thereby improving the efficiency of hydrogen-powered aircraft certification.

[0053] Combination Figure 1 As shown, the embodiment of the present disclosure provides a flow chart of a hydrogen-powered aircraft airworthiness analysis method based on MBSE, including:

[0054] S100, establishing a modeling architecture standard for a hydrogen-powered aircraft power system, wherein the architecture standard for a hydrogen-powered aircraft power system includes: performing an architecture analysis on a basic hydrogen-powered aircraft power system according to a physical structure, obtaining multiple substructures, and marking the function corresponding to each substructure.

[0055] In order to ensure standardization, unify the modeling style, and facilitate later comparison and analysis, it is necessary to establish a modeling architecture standard for hydrogen-powered aircraft power systems. In the architecture, the physical elements and functional elements of the substructures concerned with airworthiness are reflected in value attributes to indicate the properties of different substructures.

[0056] S200, acquiring a target hydrogen-powered aircraft power system.

[0057] Generally speaking, common hydrogen energy power for hydrogen-powered aircraft power systems include: hydrogen turbofan engines, hydrogen turboelectric fan engines and hydrogen fuel cell electric fan engines.

[0058] Correspondingly, the hydrogen energy power of the target hydrogen energy aircraft power system is one of a hydrogen turbofan engine, a hydrogen turbo electric fan engine and a hydrogen fuel cell electric fan engine.

[0059] S300, modeling each substructure of the target hydrogen-powered aircraft power system according to a modeling architecture standard of the target hydrogen-powered aircraft power system, and obtaining a target hydrogen-powered aircraft power system model composed of a plurality of substructure models.

[0060] In general, the multiple substructures include: one or more of a hydrogen energy fuel system, a lubricating oil system, a turbine engine, a cooling system, and a fire protection device. The function of the hydrogen energy fuel system is to supply energy, the function of the lubricating oil system is to provide lubrication, the function of the turbine engine is to provide power, the function of the cooling system is to control and adjust the temperature, and the function of the fire protection device is to block flames. It should be noted that the substructure in this application can also be a subsystem or a component.

[0061] When the hydrogen energy power of the target hydrogen energy aircraft power system is a hydrogen turbofan engine, the modeling analysis is that the basic structure of the hydrogen turbofan engine is similar to that of the gas turbine engine. The main components include a compressor, a combustion chamber and a turbine. The schematic diagram is as follows Figure 2-a shown.

[0062] Hydrogen turbofan engines use hydrogen as fuel. In the combustion chamber, the air compressed by the compressor is mixed with the injected hydrogen fuel for combustion. The heat energy released during the combustion process further pressurizes and heats the compressed gas, and the heat energy is converted into mechanical energy, which drives the turbine to rotate and generate the thrust required by the aircraft. Compared with traditional fuel engines, the main product of hydrogen combustion is water vapor, so hydrogen turbofan engines have no carbon emissions during operation and are more environmentally friendly.

[0063] When the hydrogen energy power of the target hydrogen energy aircraft power system is a hydrogen turbo-electric fan engine, the modeling analysis is that the hydrogen turbo-electric fan engine is a combination of a hydrogen turbine engine and electric propulsion technology. Its schematic diagram is as follows Figure 2-b shown.

[0064] The front end of the hydrogen turbo electric fan engine works in the same way as the hydrogen turbine engine. The difference is that in addition to the hydrogen turbine engine part, namely the compressor, combustion chamber, and turbine, the hydrogen turbo electric fan engine also includes an electric motor, a generator, and a supporting energy management system. After driving the turbine to rotate, the engine drives the generator to generate electricity, and the propulsion power of the fan is only provided by the electric motor, realizing the conversion of electrical energy into mechanical energy. In addition, part of the electrical energy will be stored in the battery and used to drive the electric fan when needed, or to power other aircraft systems.

[0065] When the hydrogen energy source of the target hydrogen energy aircraft power system is a hydrogen turbine engine, the modeling analysis shows that the technology of hydrogen turbine engines is relatively complex and develops slowly. In comparison, hydrogen fuel cells are a more common power replacement technology path for normal aircraft at the current stage. Its schematic diagram is as follows Figure 2-c shown.

[0066] The principle structure of the hydrogen fuel cell electric fan engine is similar to that of the electric propulsion power unit. The engine does not have an internal combustion process, and its main thrust comes from the electric fan, and the electric energy to drive the fan is realized by the hydrogen fuel cell. After the electric motor is powered, the fan is driven by the electric motor to convert the electric energy into mechanical energy, generating the thrust required for the aircraft to move.

[0067] The three hydrogen energy power architectures are systematically modeled using SysML as follows Figure 3-a , 3-b Based on the models constructed in the three figures, the selected hydrogen energy power architecture can be automatically screened and compared by using the opaque activities in SysML, thereby accurately defining the scope of application of existing airworthiness regulations.

[0068] S400, obtain airworthiness regulations.

[0069] For civil aviation products, the basis for airworthiness certification is crucial. It covers key elements such as applicable airworthiness standards, environmental regulations and special conditions for the product. When the product or component involved has innovative or unique design features, the intended use is beyond the norm, or the existing regulations are not fully applicable or fully covered, it is necessary to analyze and tailor the applicability of the airworthiness regulations and propose special conditions applicable to the design features. These special conditions are proposed in the form of a problem summary and reviewed by the Technical Review Committee, and then a report with recommended approval is submitted to the airworthiness department. The purpose of proposing special conditions is to ensure that products with novel or unique design features, or those with unconventional intended uses, can achieve a safety level consistent with the current airworthiness standards. Currently, with the continuous advancement of science and technology and application innovation, the use of special conditions in the type certification process is becoming more and more frequent. For example, in the airworthiness certification process of transport aircraft and novel vertical take-off and landing aircraft, existing airworthiness regulations may be tailored and analyzed to form special conditions applicable to the design features of the model. In addition, during the conceptual design and preliminary design stages of the model / system, a mapping of design features and airworthiness requirements can fully assess the difficulty and cost of airworthiness certification that may be caused by technical complexity, which is more beneficial for later design. Therefore, a faster and more accurate airworthiness suitability analysis method is needed.

[0070] S500, represents each requirement in the airworthiness regulations by using a physical structure to achieve a specific function.

[0071] Compared with the document-based airworthiness regulations applicability analysis method, the MBSE method has the advantages of traceability, visualization, and modeling. MBSE can visualize the complex internal connections in the text of airworthiness regulations into requirements that are met by physical-functional mapping. By using block definition diagrams to build a regulatory model, and then associating requirements with underlying clauses, and using activity diagrams to compare with the novel architecture, the applicability results of each clause can be obtained. Therefore, this framework can screen hydrogen-powered aircraft of any architectural form, ensuring rapid and correct screening while also forming a basis for early design iterations. Figure 4 The figure shows a logic diagram of the analysis of the embodiment of the present disclosure.

[0072] Specifically, according to the Civil Aviation Administration of China, the design of normal aircraft must comply with the airworthiness requirements of CCAR-23, which includes strict specifications for flight performance, structure, power, system safety, etc. As an emerging aviation technology, the design features of the power unit of hydrogen-powered aircraft are significantly different from those of normal aircraft.

[0073] CCAR-23-R3 adopts a division-section-clause structural framework to establish the minimum safety requirements for aircraft. The clauses involved are all prescriptive, and once established as type airworthiness requirements, they cannot be interfered with by external inputs. The underlying clauses of the framework use a clear description method: "physical components" implement specific "functions." Taking clause 23.1011(c) as an example, it stipulates that the amount of available oil in the aircraft under critical operating conditions must be at least equal to the product of the endurance time and the maximum allowable oil consumption rate of the engine, and must also include appropriate margins to ensure circulation and cooling. This requirement can be summarized as the "lubricating oil system" needs to provide a "lubrication" function, which is achieved through the performance requirement of "available oil quantity." Based on the natural language description of the underlying clauses, the "physical-functional" paradigm mapping corresponding to each clause is captured and modeled in a modular form to avoid information transmission errors caused by language ambiguity. The specific form is as follows: Figure 5 shown.

[0074] Taking the hydrogen energy power system as the research object, the E division is modeled. The requirements for clause traceability are reflected by the corresponding physical-functional element pairs, as shown in the table below.

[0075]

[0076] Here, the functional elements and physical elements of the same regulation do not correspond completely one to one. For example, the functional element of "providing power" can be completed by both a turbine engine and a piston engine.

[0077] The requirements arising from the regulatory provisions and clauses are shown in the following table.

[0078]

[0079] Similarly, several regulatory provisions may have the same requirement. For example, 23.955(a)(2) and 23.955(f) both require fuel flow limits, so these two regulations share the same requirement. Figure 6 As shown in Figure 1, this mapping relationship can not only accurately capture the specific requirements of airworthiness regulations, but also transform these requirements into specific executable design and verification standards. Through this systematic and modular approach, the clarity, consistency and operability of airworthiness standards are ensured.

[0080] S600, obtaining analysis results by analyzing whether each substructure model of the target hydrogen-powered aircraft power system meets each requirement in the airworthiness regulations.

[0081] Specifically, see Figure 7 , by analyzing whether each substructure model of the target hydrogen-powered aircraft power system meets each requirement in the airworthiness regulations, the analysis results are obtained, including:

[0082] S610, traverse each substructure model to the two elements of physical structure and function corresponding to the requirements in each airworthiness regulation.

[0083] Each substructure model is compared with the corresponding requirements in each airworthiness regulation one by one, and the regulatory requirements that match the regulatory requirements matrix in terms of physical or functional characteristics are identified.

[0084] S620: If the substructure model is completely consistent with the physical structure and functional elements of the corresponding requirements in the airworthiness regulations, the corresponding requirements are deemed to be applicable.

[0085] S630, if the substructure model matches one of the two elements of physical structure and function of the corresponding requirements in the airworthiness regulations, it needs to be evaluated.

[0086] S640, if the substructure model does not match the corresponding requirements in the airworthiness regulations for both the physical structure and the functional elements, it is considered not applicable.

[0087] It should be understood that the analysis process of the applicability of airworthiness regulations is carried out for the aircraft architecture. This application adopts a method based on the mapping of physical elements and functional elements. The method compares and screens the physical elements and functional elements in the aircraft architecture with the physical-functional mapping specified in the airworthiness clause. If the two are exactly the same, it can be determined that the requirements of this clause are applicable to hydrogen-powered aircraft. If only one of the physical or functional elements is the same, it indicates partial applicability. This situation should be a feature that the review team and the applicant focus on.

[0088] S650: If the substructure model has both analysis results of to-be-evaluated and not applicable, the analysis result of the substructure model is considered to be to-be-evaluated.

[0089] It should be understood that it is particularly important to note that in traversing each airworthiness regulation, some substructure models correspond to the physical elements and functional elements of multiple airworthiness regulations. For example, there are novel aircraft with some A features and some B features. For example, the novel aircraft can be a hydrogen hybrid architecture. In this case, it is necessary to take "to be evaluated" as the priority analysis result.

[0090] In the hydrogen turbofan aircraft architecture, traditional functions such as energy supply and fuel delivery are undertaken by dedicated hydrogen circulation systems and hydrogen fuel pipelines, and the corresponding systems and pipelines constitute the key physical elements in the architecture.

[0091] For hydrogen fuel cell electric aircraft, although the functions it implements are consistent with the requirements in the provisions of Part E, the physical element that implements these functions, the hydrogen fuel cell itself, is a novel technology. This is a scope that the novelty review group needs to discuss and determine in depth. It is worth noting that in the hydrogen turbofan architecture, in addition to the traditional function of transporting fuel, the hydrogen fuel system also implements other functions that are different from the hydrogen fuel cell electric aircraft architecture.

[0092] In terms of providing power, the hydrogen energy hybrid architecture no longer relies solely on traditional turbine engines, but also relies on hydrogen fuel cells.

[0093] Therefore, in terms of the function of providing power for the hydrogen energy hybrid architecture, the analysis result of the two elements of the physical structure and function of the corresponding requirements of the airworthiness regulations for the hydrogen circulation system and hydrogen fuel pipeline is "applicable", while for the two elements of the physical structure and function of the corresponding requirements for transporting fuel, the functions are the same but the physical structures are different, and the analysis result is "pending evaluation".

[0094] For the above-mentioned novel aircraft, specific analysis is needed according to the circumstances.

[0095] The above description and the accompanying drawings fully illustrate the embodiments of the present disclosure so that those skilled in the art can practice them. Other embodiments may include structural, logical, electrical, process and other changes. The embodiments represent only possible changes. Unless explicitly required, separate components and functions are optional, and the order of operation may vary. The parts and features of some embodiments may be included in or replace the parts and features of other embodiments. Moreover, the words used in this application are only used to describe the embodiments and are not used to limit the claims. As used in the description of the embodiments and the claims, unless the context clearly indicates, the singular forms of "a", "an" and "the" are intended to include plural forms as well. Similarly, the term "and / or" as used in this application refers to any and all possible combinations of listings containing one or more associated ones. In addition, when used in the present application, the term "comprise" and its variants "comprises" and / or comprising refer to the presence of stated features, wholes, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, wholes, steps, operations, elements, components and / or groups thereof. In the absence of further restrictions, the elements defined by the sentence "comprising a ..." do not exclude the presence of other identical elements in the process, method or device comprising the elements. In this article, each embodiment may focus on the differences from other embodiments, and the same and similar parts between the various embodiments may refer to each other. For the methods, products, etc. disclosed in the embodiments, if they correspond to the method part disclosed in the embodiments, then the relevant parts can refer to the description of the method part.

[0096] Those skilled in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software may depend on the specific application and design constraints of the technical solution. The technicians may use different methods for each specific application to implement the described functions, but such implementations should not be considered to exceed the scope of the embodiments of the present disclosure. The technicians may clearly understand that, for the convenience and simplicity of description, the specific working processes of the above-described devices, devices and units may refer to the corresponding processes in the aforementioned method embodiments, and will not be repeated here.

[0097] The flowchart and block diagram in the accompanying drawings show the possible architecture, functions and operations of the device, method and computer program product according to the embodiment of the present disclosure. In this regard, each box in the flowchart or block diagram can represent a module, a program segment or a part of the code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. In some alternative implementations, the functions marked in the box can also occur in an order different from that marked in the accompanying drawings. For example, two consecutive boxes can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, which can depend on the functions involved. In the description corresponding to the flowchart and the block diagram in the accompanying drawings, the operations or steps corresponding to different boxes can also occur in an order different from that disclosed in the description, and sometimes there is no specific order between different operations or steps. For example, two consecutive operations or steps can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, which can depend on the functions involved. Each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, may be implemented by dedicated hardware-based devices that perform the specified functions or actions, or may be implemented by a combination of dedicated hardware and computer instructions.

Claims

1. A hydrogen-powered aircraft airworthiness analysis method based on MBSE, characterized in that: The method comprises: Establishing a modeling architecture standard for a hydrogen-powered aircraft power system, wherein the architecture standard for a hydrogen-powered aircraft power system includes: performing an architecture analysis on a basic hydrogen-powered aircraft power system according to a physical structure, obtaining multiple substructures, and marking the function corresponding to each substructure, wherein a substructure includes a subsystem or a component; Acquire the target hydrogen-powered aircraft power system; According to the modeling architecture standard of the target hydrogen-powered aircraft power system, each substructure of the target hydrogen-powered aircraft power system is modeled to obtain a target hydrogen-powered aircraft power system model composed of multiple substructure models; Obtain airworthiness regulations; Represent each requirement in the airworthiness regulations by a physical structure that achieves a specific function; The analysis results are obtained by analyzing whether each substructure model of the target hydrogen-powered aircraft power system meets each requirement in the airworthiness regulations.

2. The MBSE-based airworthiness analysis method for hydrogen-powered aircraft according to claim 1 is characterized in that: By analyzing whether each substructure model of the target hydrogen-powered aircraft power system meets each requirement of the airworthiness regulations, the analysis results are obtained, including: Each substructure model traverses the two elements of physical structure and function corresponding to each airworthiness regulation; If the substructure model is completely consistent with the physical structure and function elements of the corresponding requirements in the airworthiness regulations, the corresponding requirements are deemed applicable; If the substructure model matches one of the two elements of physical structure and function required by the corresponding requirements in the airworthiness regulations, it needs to be evaluated; If the substructure model does not match both the physical structure and functional elements of the corresponding requirements in the airworthiness regulations, it is considered not applicable.

3. The MBSE-based airworthiness analysis method for hydrogen-powered aircraft according to claim 2 is characterized in that: By analyzing whether each substructure model of the target hydrogen-powered aircraft power system meets each requirement of the airworthiness regulations, the analysis results are obtained, including: If a substructure model has both analysis results of pending evaluation and not applicable, the analysis results of the substructure model shall be regarded as pending evaluation.

4. The MBSE-based airworthiness analysis method for hydrogen-powered aircraft according to claim 1 is characterized in that: The hydrogen energy power of the hydrogen energy aircraft power system includes: hydrogen turbofan engine, hydrogen turbo electric fan engine and hydrogen fuel cell electric fan engine.

5. The MBSE-based airworthiness analysis method for hydrogen-powered aircraft according to claim 1 is characterized in that: The multiple substructures include: any one or more of: a hydrogen energy fuel system, a lubricating oil system, a turbine engine, a cooling system and a fire protection device.

6. The MBSE-based airworthiness analysis method for hydrogen-powered aircraft according to claim 5 is characterized in that: The function of the hydrogen energy fuel system is to supply energy, the function of the lubricating oil system is to provide lubrication, the function of the turbine engine is to provide power, the function of the cooling system is to control and regulate the temperature, and the function of the fire protection device is to block flames.

7. The MBSE-based airworthiness analysis method for hydrogen-powered aircraft according to claim 1 is characterized in that: The method further comprises: Based on the analysis results, the target hydrogen-powered aircraft power system model can be adjusted or the airworthiness regulations can be adaptively modified.

8. The MBSE-based airworthiness analysis method for hydrogen-powered aircraft according to claim 1 is characterized in that: Modeling is done using SysML.

9. A hydrogen-powered aircraft airworthiness analysis device based on MBSE, characterized in that: include: The standardized architecture module is configured to establish a modeling architecture standard for a hydrogen-powered aircraft power system, wherein the architecture standard for a hydrogen-powered aircraft power system includes: performing an architecture analysis on a basic hydrogen-powered aircraft power system according to a physical structure to obtain a plurality of substructures, and marking a function corresponding to each substructure, wherein a substructure includes a subsystem or a component; Establishing a target model module, which is configured to obtain a target hydrogen-powered aircraft power system, modeling each substructure of the target hydrogen-powered aircraft power system according to a modeling architecture standard of the target hydrogen-powered aircraft power system, and obtaining a target hydrogen-powered aircraft power system model composed of a plurality of substructure models; A regulation conversion module is configured to obtain airworthiness regulations and represent each requirement in the airworthiness regulations by using a physical structure to implement a specific function; The analysis module is configured to analyze whether each substructure model of the target hydrogen-powered aircraft power system meets each requirement in the airworthiness regulations, obtain analysis results, and adjust each substructure model.

10. The MBSE-based hydrogen-powered aircraft airworthiness analysis device according to claim 1, characterized in that: The device further comprises: The adjustment module is configured to adjust the target hydrogen-powered aircraft power system model or adaptively modify the airworthiness regulations according to the analysis results.

Images