Hydrogen energy power aircraft airworthiness analysis method and device based on MBSE

Abstract

The application relates to the technical field of aircraft design, and discloses a hydrogen energy power aircraft airworthiness analysis method and device based on MBSE, which comprises the following steps: establishing a modeling architecture standard of a hydrogen energy aircraft power system; modeling each substructure of a target hydrogen energy aircraft power system according to the modeling architecture standard of the target hydrogen energy aircraft power system, so as to obtain a target hydrogen energy aircraft power system model composed of multiple substructure models; obtaining airworthiness regulations; representing each requirement in the airworthiness regulations by using a physical structure to realize a specific function; and obtaining an analysis result by analyzing whether each substructure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulations. The application can intuitively and accurately identify potential differences and conflicts between the target hydrogen energy aircraft power system and existing airworthiness regulations, and improves the efficiency of hydrogen energy power aircraft approval.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft design, for example to a hydrogen energy power aircraft airworthiness analysis method and device based on MBSE. BACKGROUND

[0002] With the continuous rise of passenger and freight transport requirements, the future civil aviation growth rate will remain stable. In addition to the traditional economic and efficient requirements, in order to achieve the goal of carbon peak and carbon neutral, green and environmentally friendly hydrogen energy aircraft has received close attention from domestic and foreign aviation manufacturing and research institutions. At present, many countries in the world are actively engaged in the research work of hydrogen energy power whole aircraft and its power system, including China's "Lingque H", Germany "H2FLY", France ZEROe, and the United States "Phantom Eye" type have completed or are carrying out design and verification work.

[0003] For civil aircraft, according to the provisions of CCAR-21 for operating aircraft, the aircraft must pass the airworthiness certification of the civil aviation authority before being put into use. The hydrogen energy aircraft is a kind of aircraft with significant novel design features. Unlike traditional aircraft that store fuel in fuel tanks, hydrogen energy aircraft relies on liquid hydrogen to achieve the same function. Therefore, for the existing airworthiness standards, many provisions are no longer applicable. Such design features need to be analyzed, confirmed and formed by the applicant as soon as possible to form the basis for certification and the corresponding special conditions, so as to ensure that such aircraft has an equivalent safety level to the existing airworthiness regulations.

[0004] The formation and confirmation process of the airworthiness certification basis of the traditional aircraft is mainly based on documents. However, there are many hydrogen energy power configurations, and different types of aircraft have scattered complex features in design and implementation, which may exhibit potential differences in airworthiness certification requirements. The traditional document-based airworthiness analysis and design method is difficult to fully capture the potential design details, and such differences are easily overlooked in the airworthiness analysis process, ultimately leading to repeated changes in the design of the type. In addition, the natural language contained in the document has inherent ambiguity and ambiguity in conveying technical details, which may lead to misunderstanding of the intent and requirements of the airworthiness analysis, thereby affecting the accuracy of the design and the efficiency of the airworthiness certification. Therefore, at the present stage, a more accurate, dynamic and standard method is needed to analyze, identify and manage these potential differences to ensure that the airworthiness certification process for hydrogen energy aircraft is correct, comprehensive and efficient.

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

[0006] The following presents a simplified summary of some aspects of the disclosed embodiments in order to provide a basic understanding of such embodiments. This summary is not an extensive overview of the embodiments and is not intended to identify key / critical elements or to delineate the scope of the embodiments. Its sole purpose is to present some aspects of the disclosed embodiments in a simplified form as a prelude to the more detailed description that is presented later.

[0007] The embodiment of the present disclosure provides a hydrogen energy power aircraft airworthiness analysis method and device based on MBSE. The formation and confirmation process of the airworthiness certification basis of a 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 ignored in the airworthiness analysis process. There is a problem of low accuracy in the aircraft airworthiness design audit, resulting in repeated changes of the aircraft airworthiness design.

[0008] In some embodiments, a hydrogen energy power aircraft airworthiness analysis method based on MBSE is provided, characterized in that the method comprises:

[0009] Establishing a modeling architecture standard of a hydrogen energy aircraft power system, wherein the architecture standard of the hydrogen energy aircraft power system comprises: performing architecture analysis on a basic hydrogen energy aircraft power system according to a physical structure to obtain a plurality of substructures, and marking a function corresponding to each substructure, wherein the substructure comprises a subsystem or a component;

[0010] Obtaining a target hydrogen energy aircraft power system;

[0011] Modeling each substructure of the target hydrogen energy aircraft power system according to the modeling architecture standard 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;

[0012] Obtaining airworthiness regulations;

[0013] Expressing each requirement in the airworthiness regulations by a physical structure to implement a specific function;

[0014] Obtaining an analysis result by analyzing whether each substructure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulations.

[0015] Preferably, the analysis result is obtained by analyzing whether each substructure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulations, and the analysis result comprises:

[0016] Traversing each substructure model through the physical structure and the function of the corresponding requirement in each airworthiness regulation;

[0017] If the substructure model is completely consistent with the physical structure and the function of the corresponding requirement in the airworthiness regulations, it is determined that the corresponding requirement is applicable;

[0018] If the sub-structure model matches one of the two elements of physical structure and function of the corresponding requirement in the airworthiness regulation, the sub-structure model needs to be evaluated;

[0019] If the sub-structure model does not match either of the two elements of physical structure and function of the corresponding requirement in the airworthiness regulation, the sub-structure model is considered not applicable.

[0020] By analyzing whether each sub-structure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulation, an analysis result is obtained, and the analysis result further includes:

[0021] If the sub-structure model has both the evaluation and the not applicable analysis results, the analysis result of the sub-structure model is considered to be evaluated.

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

[0023] Preferably, the plurality of sub-structures includes one or more of: a hydrogen energy fuel system, an oil system, a turbine engine, a cooling system, and a fire protection device.

[0024] Preferably, the hydrogen energy fuel system functions to supply energy, the oil system functions to provide lubrication, the turbine engine functions to provide power, the cooling system functions to control and regulate temperature, and the fire protection device functions to block fire.

[0025] Preferably, the method further includes:

[0026] According to the analysis result, the target hydrogen energy aircraft power system model is adjusted, or the airworthiness regulation is adaptively modified.

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

[0028] In some embodiments, a hydrogen energy power aircraft airworthiness analysis device based on MBSE is disclosed, including:

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

[0030] The target model establishing module is configured to obtain a target hydrogen energy aircraft power system, model each substructure of the target hydrogen energy aircraft power system according to a modeling architecture standard of the target hydrogen energy aircraft power system, and obtain a target hydrogen energy aircraft power system model composed of a plurality of substructure models;

[0031] The regulation conversion module is configured to obtain airworthiness regulations, and represent each requirement in the airworthiness regulations by a physical structure that implements a specific function.

[0032] The analysis module is configured to obtain an analysis result by analyzing whether each substructure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulations, and adjust each substructure model.

[0033] Preferably, the device further comprises an adjustment module configured to adjust the target hydrogen energy aircraft power system model or adaptively modify the airworthiness regulations according to the analysis result.

[0034] The hydrogen energy power aircraft airworthiness analysis method and device based on MBSE provided by the embodiments of the present disclosure can achieve the following technical effects:

[0035] The embodiments of the present disclosure convert the target hydrogen energy aircraft power system and the airworthiness regulations into physical structures and functions for representation, and then perform contrast matching analysis on the target hydrogen energy aircraft power system and the airworthiness regulations. In this way, potential differences and conflicts between the target hydrogen energy aircraft power system and the existing airworthiness regulations can be intuitively and accurately identified, and the efficiency of hydrogen energy power aircraft certification is improved.

[0036] The foregoing general description and the following description are merely exemplary and explanatory, and are not intended to limit the present application. BRIEF DESCRIPTION OF DRAWINGS

[0037] One or more embodiments are exemplarily illustrated by corresponding drawings, which do not constitute limitations on the embodiments, elements with the same reference numerals in the drawings are shown as similar elements, the drawings do not constitute proportional limits, and wherein:

[0038] Figure 1 is a hydrogen energy power aircraft airworthiness analysis method flowchart provided by the embodiments of the present disclosure;

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

[0040] Figure 2-b is a hydrogen turboelectric fan engine principle schematic diagram provided by the embodiments of the present disclosure;

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

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

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

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

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

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

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

[0048] Figure 7 is an analysis flow schematic diagram of each substructure model of an analysis target hydrogen energy aircraft power system reaching 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 more fully, the implementation of the embodiments of the present disclosure will be described in detail below, and the accompanying drawings are used for reference only and do not limit the embodiments of the present disclosure. In the following technical description, in order to facilitate explanation, through multiple details, a full understanding of the disclosed embodiments is provided. However, one or more embodiments can still be implemented without these details. In other cases, in order to simplify the drawings, well-known structures and devices can be simplified.

[0050] The following description and accompanying drawings fully illustrate specific embodiments of the invention to enable those skilled in the art to practice them. Other embodiments may include structural, logical, electrical, procedural, and other changes. The embodiments represent only possible variations. Individual components and functions are optional unless explicitly required, and the order of operation may vary. Some portions and features of some embodiments may be included in or replace portions and features of other embodiments. The scope of embodiments of the invention includes the entire scope of the claims and all available equivalents of the claims. In this document, each embodiment may be referred to individually or collectively with the term "invention," which is merely for convenience and is not intended to automatically limit the scope of application to any single invention or inventive concept if more than one invention is disclosed. In this document, relational terms such as "first" and "second" are used only 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. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, or apparatus that includes said element. The various embodiments described herein are presented in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the methods, products, etc., disclosed in the embodiments, since they correspond to the method section disclosed in the embodiments, the descriptions are relatively simple; relevant details can be found in the method section description.

[0051] The civil aviation industry currently faces dual challenges of energy and the environment, and hydrogen energy is a key technological path to address these issues. However, existing civil aircraft airworthiness regulations have potential applicability differences and incomplete coverage issues regarding the design characteristics of hydrogen-powered aircraft, thus failing to directly form a basis for the airworthiness certification of hydrogen-powered aircraft.

[0052] To address the problems existing in related technologies, this disclosure provides a method and apparatus for airworthiness analysis of hydrogen-powered aircraft based on MBSE (Medium-Range Scale for Airworthiness Analysis). Both the target hydrogen-powered aircraft propulsion system and airworthiness regulations are represented by their physical structures and functions, and then a comparative analysis is performed between the target hydrogen-powered aircraft propulsion system and the airworthiness regulations. This allows for the intuitive and accurate identification of potential differences and conflicts between the target hydrogen-powered aircraft propulsion system and existing airworthiness regulations, improving the efficiency of hydrogen-powered aircraft certification.

[0053] In combination Figure 1 As shown in the figure, the embodiment of the present disclosure provides a flow chart of a hydrogen energy power aircraft airworthiness analysis method based on MBSE, which comprises the following steps:

[0054] S100, establishing a modeling architecture standard of a hydrogen energy aircraft power system, wherein the architecture standard of the hydrogen energy aircraft power system comprises: performing architecture analysis on a basic hydrogen energy aircraft power system according to a physical structure, obtaining a plurality of substructures, and marking the functions corresponding to each substructure.

[0055] In order to ensure standardization, unify modeling style, and facilitate later comparison and analysis, a modeling architecture standard of the hydrogen energy aircraft power system needs to be established. The physical elements and functional elements of the substructures concerned in the architecture are embodied in value attributes, indicating the properties of different substructures.

[0056] S200, obtaining a target hydrogen energy aircraft power system.

[0057] Generally, the hydrogen energy power of the common hydrogen energy aircraft power system comprises: a hydrogen turbofan engine, a hydrogen turbo-electric fan engine, and a hydrogen fuel cell electric fan engine.

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

[0059] S300, modeling each substructure of the target hydrogen energy aircraft power system according to the modeling architecture standard 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.

[0060] Generally, the plurality of substructures comprises one or more of a hydrogen energy fuel system, an oil system, a turbine engine, a cooling system, and a fireproof device. The function of the hydrogen energy fuel system is to supply energy, the function of the 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 temperature, and the function of the fireproof device is to block flame. It should be noted that the substructure in the present 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 a gas turbine engine, and the main components include a compressor, a combustion chamber, and a turbine, as shown in the principle diagram below. Figure 2-a

[0062] ​A hydrogen turbofan engine uses hydrogen as fuel, in the combustion chamber, the air compressed by the compressor will mix with the hydrogen fuel injected into the combustion chamber and burn. The heat energy released by the combustion process further pressurizes and heats the already compressed gas, and the heat energy is converted into mechanical energy to drive the turbine to rotate and generate the required thrust for the aircraft. Compared with traditional fuel engines, the main product of hydrogen combustion is water vapor, so the hydrogen turbofan engine has no carbon emissions during operation, and is more environmentally friendly.

[0063] When the hydrogen energy power of the target hydrogen energy aircraft power system is a hydrogen turbofan engine, the modeling analysis is that the hydrogen turbofan engine is a combination of a hydrogen turbine engine and an electric propulsion technology, and its schematic diagram is as shown in the following Figure 2-b .

[0064] The working mode of the front end of the hydrogen turbofan engine is the same as that of the hydrogen turbine engine, and the difference is that the hydrogen turbofan engine includes a motor, a generator and a supporting energy management system in addition to the hydrogen turbine engine part, i.e. the compressor, the combustion chamber and the turbine. 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 motor, realizing the conversion of electrical energy into mechanical energy. In addition, part of the electrical energy will be stored in the battery and will drive the electric fan when needed, or will power other systems of the aircraft.

[0065] When the hydrogen energy power of the target hydrogen energy aircraft power system is a hydrogen turbine engine, the modeling analysis is that the hydrogen turbine engine technology is relatively complex and slow to develop. In comparison, the current stage hydrogen fuel cell is a more common power replacement technology path for normal aircraft, and its schematic diagram is as shown in the following Figure 2-c .

[0066] The principle architecture of the hydrogen fuel cell electric fan engine is similar to that of the electric propulsion power device. The engine has no internal combustion process, and the main thrust is derived from the electric fan, and the electric energy driving the fan is realized by the hydrogen fuel cell. After the motor is powered, the fan is driven by the motor to realize the conversion of electrical energy into mechanical energy, generating the required thrust for the aircraft movement.

[0067] The three hydrogen energy power architectures are modeled using SysML, as shown in the following Figure 3-a , 3-b and 3-c. Based on the models built in the three diagrams, the selected hydrogen energy power architecture can be automatically screened and compared by using the opaque activity in SysML, so as to accurately define the applicable scope of the existing airworthiness regulations.

[0068] S400, obtaining airworthiness regulations.

[0069] For civil aviation products, airworthiness certification basis is essential. It covers the key elements of the product, such as applicable airworthiness standards, environmental regulations and special conditions. When the product or component has innovative or unique design features, the intended use exceeds the norm, or the existing regulations are not fully applicable or sufficient, an analysis of the airworthiness regulations is required to tailor and propose special conditions applicable to the design features. These special conditions are presented in the form of a problem memorandum and are reviewed by the Technical Review Board before submitting a report to the airworthiness department for approval. The purpose of the special conditions is to ensure that products with novel or unique design features, or those with non-standard intended use, can achieve the same level of safety as the existing airworthiness standards. With the continuous progress of technology and application innovation, the use of special conditions in the type certification process is becoming more frequent. For example, in the airworthiness certification process of transport category aircraft and novel vertical take-off and landing aircraft, the existing airworthiness regulations may be tailored and analyzed to form special conditions applicable to the design features of the type. In addition, during the conceptual design and preliminary design stages of the type / system, mapping the design features and airworthiness requirements can fully assess the difficulty and cost of airworthiness certification caused by technical complexity, which is more beneficial to later design, so a more rapid and accurate airworthiness applicability analysis method is needed.

[0070] S500, each requirement in the airworthiness regulations is represented by a physical structure to perform a specific function.

[0071] Compared with the document-based airworthiness regulation applicability analysis method, the MBSE method has the advantages of traceability, visualization and modeling. MBSE can abstract the complex internal relationship in the airworthiness regulation text into the requirements met by the physical-function mapping. By building a regulation model using block definition diagrams, associating requirements with underlying clauses, and comparing novel architectures using activity diagrams, the applicability of each clause can be obtained. Therefore, this framework can screen hydrogen energy-powered aircraft with any architectural form, ensuring fast and correct screening while also providing the basis for early design iteration. As shown in FIG. 1, it is a logical diagram of the analysis of the embodiment of the present disclosure. Figure 4

[0072] Specifically, according to the regulations of the Civil Aviation Administration of China, the design of normal category aircraft must comply with the airworthiness requirements of CCAR-23, which includes strict specifications for flight performance, structure, power, system safety, etc. Hydrogen energy aircraft, as a new aviation technology, has significant differences in design features from normal category aircraft.

[0073] ​CCAR-23-R3 adopts a structure framework of division-section-clause, establishing the minimum safety requirements for aircraft. The clauses involved are all prescriptive, once established as type certification requirements, cannot be interfered by external input. The bottom clause of the framework adopts a clear description way: "physical component" realizes a specific "function". Take 23.1011(c) clause as an example, it stipulates that the available oil quantity of 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 also includes the appropriate margin required to ensure the cycle and cooling. This requirement can be summarized as "oil system" needs to provide "lubrication" function, which is realized through the performance requirement of "available oil quantity". Based on the natural language description of the bottom clause, capture the "physical-function" paradigm mapping corresponding to each clause, model in a modular form, avoid information transmission failure caused by language ambiguity, specific form as shown in Figure 5 .

[0074] Take hydrogen energy power system as the research object, model E division. The requirements traced by the clauses are embodied by the corresponding physical-function element pairs, see the following table.

[0075]

[0076] Here, the function elements and physical elements of the same regulation do not completely correspond one by one, for example, the "power supply" function element can be completed by both turbine engine and piston engine.

[0077] The regulation clauses and the requirements generated by the clauses are shown in the following table.

[0078]

[0079] Similarly, several regulation clauses may have the same requirements. For example, 23.955(a)(2) and 23.955(f) both require fuel flow limitation, so these two regulations share the same requirement. The clause and requirement traceability relationship is shown in Figure 6 , this mapping relationship not only accurately captures the specific requirements of airworthiness regulations, but also converts these requirements into specific executable design and verification standards. Through this systematic and modular method, the clarity, consistency and operability of airworthiness standards are ensured.

[0080] S600, by analyzing whether each sub-structure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulations, obtaining an analysis result.

[0081] Specifically, see Figure 7 , by analyzing whether each sub-structure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulations, obtaining an analysis result, including:

[0082] S610, traversing each sub-structure model through the corresponding requirements in each airworthiness regulation in terms of both physical structure and function elements.

[0083] Comparing each sub-structure model with each corresponding requirement in each airworthiness regulation, identifying the regulatory requirements that match the sub-structure model in terms of physical or functional characteristics.

[0084] S620, if the sub-structure model is fully consistent with the corresponding requirements in each airworthiness regulation in terms of both physical structure and function elements, then the corresponding requirements are deemed applicable.

[0085] S630, if the sub-structure model matches one of the corresponding requirements in each airworthiness regulation in terms of either physical structure or function elements, then it needs to be evaluated.

[0086] S640, if the sub-structure model does not match any of the corresponding requirements in each airworthiness regulation in terms of both physical structure and function elements, then it is deemed inapplicable.

[0087] It should be understood that the analysis process of airworthiness regulation applicability for aircraft architecture is carried out. The present application adopts a method based on the mapping of physical elements and functional elements. The method compares and filters the physical elements and functional elements in the aircraft architecture with the physical-functional mapping specified in the airworthiness clauses. If they are fully consistent, it can be determined that the requirements of the clause are applicable to hydrogen energy aircraft. If only one of the physical or functional elements is the same, it indicates a partial applicability. This case should be the focus of the review team and the applicant.

[0088] S650, if the sub-structure model has both evaluation and inapplicable analysis results, then the analysis result of the sub-structure model is deemed to be evaluated.

[0089] It should be understood that special attention should be paid to the fact that in the traversal of each airworthiness regulation, some sub-structure models correspond to the physical elements and functional elements of multiple airworthiness regulations. For example, a novel aircraft has some A features and some B features. For example, the novel aircraft can be a hydrogen energy hybrid architecture. In this case, "to be evaluated" should be the priority analysis result.

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

[0091] For hydrogen fuel cell electric airplanes, although the functions achieved are consistent with the requirements in the E division clause, the physical elements that achieve these functions, the hydrogen fuel cells themselves, are a novel technology. The scope of this novelty review group requires in-depth discussion and determination. It is worth noting that in the hydrogen turbofan architecture, the hydrogen fuel system not only assumes the traditional function of delivering fuel, but also achieves other functions different from the hydrogen fuel cell electric airplane architecture.

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

[0093] Therefore, for the function of providing power in the hydrogen energy hybrid architecture, the analysis result is "applicable" for the corresponding requirements of the airworthiness regulations for the physical structure and function of the hydrogen circulation system and the hydrogen fuel pipeline, and "to be evaluated" for the corresponding requirements of the physical structure and function of assuming the delivery of fuel, which are the same function but different physical structure.

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

[0095] The above description and drawings are illustrative of embodiments of the present disclosure and are not intended to be limiting. Other embodiments can include structural, logical, electrical, process, and other changes. Embodiments are merely representative of possible variations. Individual components and functions are optional unless explicitly required, and the order of operations can be varied. Portions and features of some embodiments can be included in, or substituted for, those of other embodiments. Also, words used in this document and claims are words of description, not limitation. As used in the description and claims herein, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. Similarly, the term "and / or" as used herein refers to any one or more of the associated listed items, optionally including zero of the associated listed items. Additionally, the term "comprising" and variations thereof as used herein are intended to be open-ended terms that specify the presence of the stated features, elements, steps, operations, integers, and / or components, but do not preclude the presence or addition of one or more other features, elements, steps, operations, integers, components, and / or groups thereof. The term "consisting of" as used herein is intended to be a closed term that specifies the presence of the stated features, elements, steps, operations, integers, and / or components, but does not preclude the presence or addition of one or more other features, elements, steps, operations, integers, components, and / or groups thereof. Unless otherwise expressly stated, mechanisms of the present disclosure can be implemented in either hardware, software, or a combination thereof. The description herein assumes that the mechanisms are implemented in software in a non- limiting example unless specifically and expressly stated otherwise. If implemented in hardware, as one of ordinary skill in the art will readily understand, the mechanisms of the present disclosure can be implemented using one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DSPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, micro-controllers, microprocessors, other electronic units designed to perform the functions described herein, a combination thereof, or any suitable processing unit. The description herein assumes that the mechanisms are implemented in software in a non-limiting example unless specifically and expressly stated otherwise. If implemented in software, the mechanisms of the present disclosure can be implemented using software modules, engines, or components, including but not limited to, code, scripts, instructions or any other software. Software can be stored on one or more computer-readable media, including, but not limited to, RAM, ROM, EEPROM, flash memory or other memory, CD-ROM, digital versatile disks (DVD) or other optical disk storage, magnetic cassettes, magnetic tapes, magnetic disk storage or other magnetic storage devices, or any other medium suitable for storing software.

[0096] Those skilled in the art can understand that the units and algorithm steps of the examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware or a combination of computer software and electronic hardware. Whether the functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. The skilled person can use different methods for each specific application to implement the described functions, but such implementation should not be considered beyond the scope of the embodiments of the present disclosure. The skilled person can clearly understand that, for the convenience and brevity of description, the specific working processes of the above-described devices, apparatuses and units can refer to the corresponding processes in the foregoing method embodiments, which will not be described here.

[0097] The diagrams of the flow and block diagrams show the possible implementation architecture, function and operation of the apparatus, method and computer program product according to the embodiments of the present disclosure. In this regard, each block in the flow or block diagram can represent a module, a program segment or a part of code containing one or more executable instructions for implementing the specified logic function. In some alternative implementations, the functions annotated in the blocks can also occur in an order different from that annotated in the diagrams. For example, two consecutive blocks can actually be executed substantially in parallel, and sometimes they can also be executed in reverse order, depending on the functions involved. In the description corresponding to the flow and block diagrams in the diagrams, the operations or steps corresponding to different blocks 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 sometimes they can also be executed in reverse order, depending on the functions involved. Each block in the block diagram and / or flow diagram, and the combination of blocks in the block diagram and / or flow diagram, can be implemented by a dedicated hardware-based device performing the specified functions or actions, or can be implemented by a combination of special-purpose hardware and computer instructions.

Claims

1. A method for airworthiness analysis of a hydrogen energy power aircraft based on MBSE, characterized in that, The method comprises: establishing a modeling architecture standard of a hydrogen energy aircraft power system, wherein the architecture standard of the hydrogen energy aircraft power system comprises: performing architecture analysis on a basic hydrogen energy aircraft power system according to a physical structure to obtain a plurality of substructures, and marking a function corresponding to each substructure, wherein the substructure comprises a subsystem or a component; obtaining a target hydrogen energy aircraft power system; modeling each substructure of the target hydrogen energy aircraft power system according to the modeling architecture standard 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; representing each requirement in the airworthiness regulations by a physical structure for implementing a specific function; obtaining an analysis result by analyzing whether each substructure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulations, wherein the obtaining of the analysis result by analyzing whether each substructure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulations comprises: traversing each substructure model through two elements of a physical structure and a function corresponding to a requirement in each airworthiness regulation; if the substructure model is completely consistent with the two elements of the physical structure and the function corresponding to the requirement in the airworthiness regulation, it is determined that the corresponding requirement is applicable; if the substructure model matches one of the two elements of the physical structure and the function corresponding to the requirement in the airworthiness regulation, it needs to be evaluated; if the substructure model does not match the two elements of the physical structure and the function corresponding to the requirement in the airworthiness regulation, it is considered as inapplicable.

2. The MBSE-based airworthiness analysis method for hydrogen energy power aircraft according to claim 1, characterized in that, The obtaining of the analysis result by analyzing whether each substructure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulations further comprises: if the substructure model simultaneously has two analysis results of to be evaluated and inapplicable, the analysis result of the substructure model is considered as to be evaluated.

3. The MBSE-based airworthiness analysis method for hydrogen energy power aircraft according to claim 1, wherein, The hydrogen energy power of the hydrogen energy aircraft power system comprises: a hydrogen turbofan engine, a hydrogen turboelectric fan engine, and a hydrogen fuel cell electric fan engine.

4. The MBSE-based airworthiness analysis method for hydrogen energy power aircraft according to claim 1, wherein, The plurality of substructures comprise any one or more of one or more of a hydrogen energy fuel system, an oil system, a turbine engine, a cooling system, and a fireproof device.

5. The MBSE-based airworthiness analysis method for hydrogen energy power aircraft according to claim 4, characterized in that, The function of the hydrogen energy fuel system is to supply energy, the function of the 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 temperature, and the function of the fireproof device is to block flames.

6. The MBSE-based airworthiness analysis method for hydrogen energy power aircraft according to claim 1, wherein, The method further comprises: adjusting the target hydrogen energy aircraft power system model or adaptively modifying the airworthiness regulations according to the analysis result.

7. The MBSE-based hydrogen energy power aircraft airworthiness analysis method according to claim 1, characterized in that, Modeling is performed by SysML.

8. A hydrogen energy power aircraft airworthiness analysis device based on MBSE, characterized in that, The method comprises: a standardized architecture module configured to establish a modeling architecture standard of a hydrogen energy aircraft power system, wherein the architecture standard of the hydrogen energy aircraft power system comprises: performing architecture analysis on a basic hydrogen energy aircraft power system according to a physical structure to obtain a plurality of substructures, and marking a function corresponding to each substructure, wherein the substructure comprises a subsystem or a component; The target model module is configured to obtain a target hydrogen energy aircraft power system, model each substructure of the target hydrogen energy aircraft power system according to a modeling architecture standard of the target hydrogen energy aircraft power system, and obtain a target hydrogen energy aircraft power system model composed of a plurality of substructure models; The regulation conversion module is configured to obtain airworthiness regulations, and represent each requirement in the airworthiness regulations by a physical structure and a specific function; The analysis module is configured to obtain an analysis result by analyzing whether each substructure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulations, and adjust each substructure model, wherein the analysis result is obtained by analyzing whether each substructure model of the target hydrogen energy aircraft power system meets each requirement in the airworthiness regulations, and includes: traversing each substructure model through two elements of a physical structure and a function of a corresponding requirement in each airworthiness regulation; if the substructure model is completely consistent with the two elements of the physical structure and the function of the corresponding requirement in the airworthiness regulation, it is determined that the corresponding requirement is applicable; if the substructure model matches one of the two elements of the physical structure and the function of the corresponding requirement in the airworthiness regulation, it needs to be evaluated; and if the substructure model does not match the two elements of the physical structure and the function of the corresponding requirement in the airworthiness regulation, it is considered as inapplicable.

9. The MBSE-based hydrogen energy power aircraft airworthiness analysis device according to claim 8, characterized in that, The device further includes: The adjustment module is configured to adjust the target hydrogen energy aircraft power system model according to the analysis result, or adaptively modify the airworthiness regulations.

Images