Architecting commercial aircraft has been always challenging due to the complexity of the product. A Model-Based Systems Engineering (MBSE) method was employed in this paper to handle this challenge, and a widely used general-purpose systems modeling language - SysML - was adopted to support the architecting work. To ensure compatibility between the modeling language and the specific aircraft architecting methodology, we explored construction and application methods of a Domain Specific Language. A new Domain Specific Language was created, in which several extensions to SysML were made, including Function & Components, Port, Exchanged Item and Relation. Benefiting from this new Domain Specific Language, an overall aircraft architecture model was precisely constructed.

In view of the practical problems in aviation field, such as increasingly complex systems and relationships among systems, great uncertainty in cross-industry and multi-discipline, traditional systems engineering is gradually weak. In this paper, combined with the functional architecture design of civil aircraft brake system, model-based systems engineering (MBSE) is introduced. In this paper, the function of civil aircraft brake system is defined and analysed by this method, and the functional architecture model of civil aircraft brake system is built through repeated iterations, and the state switching logic among system functions is presented digitally to ensure the clarity, comprehensiveness and reliability of the functional architecture.

Model-based system engineering theory is a new breakthrough in aircraft development methodology, which can solve the problems of aviation system development, high integration, difficult management and high risks. This paper introduces the basic theory of MBSE, and applies MBSE method in the design of communication system to realize audio communication function. Starting from the needs of stakeholders, perform analysis and define system use cases. According to different scenarios, define the function requirements activity flow and determine the functional model. Then map the functional architecture to the physical layer, carry out scheme trade-off analysis, architecture design and generate physical architecture diagram to ensure that the final solution meets the needs of stakeholders. Through model evolution and iteration, product design is realized. Modeling can provide all parties with a universal and unambiguous design information exchange platform, and at the same time facilitate the realization of system virtual integration and improve the existing design process.

This article is to show a new type of aircraft system design method, which decomposes the civil aircraft high-frequency data link system architecture into functional architecture, logical architecture and physical architecture, and describes the hierarchical relationship between the function, logic and physics of the system through the SysML model language.This article shows the method what converts the traditional high-frequency data link system design work based on experience and documents into model-based architecture design work.It uses the association and traceability of the model to ensure the integrity of the information in the design process and achieve the purpose of fast and convenient system design.

Functional analysis plays a critical role in early-stage aircraft system design by defining system functions that guide downstream architectural development and verification. In practice, many design deficiencies originate not from incorrect physical realization but from incomplete or ambiguous functional definitions established at conceptual stages. This challenge is particularly pronounced in aircraft systems, where interaction- and physical-effect-induced functions tend to remain implicit and weakly justified. To address this issue, in this study, we conduct a case-study-based comparative evaluation of three functional analysis paradigms: design-theory-oriented functional decomposition, systems-engineering-based functional allocation, and scenario-driven functional analysis. Using an aircraft ground deceleration scenario as a controlled context, this comparison examines how different function-derivation mechanisms influence the identification and justification of interaction- and effect-induced functions. Through structured cross-paradigm comparison, three distinct and, in principle, reproducible derivation mechanisms, namely decomposition-driven, responsibility-driven, and physical-effect-driven, are identified. In this study, the physical-effect-driven mechanism is examined through an effect-strengthened implementation of the scenario-driven paradigm. While all paradigms consistently identify mission-oriented functions, the examined scenario-driven implementation enhances transparency in functional justification and improves sensitivity to interaction- and effect-induced functions, thereby reducing the risk of omission during conceptual design. By formalizing these derivation mechanisms and clarifying their complementary roles, this study contributes to a clearer methodological understanding of functional identification in early-stage complex system design, while providing practical guidance for methodological selection and integration in aircraft system design.