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Hybrid laminar flow control or HLFC design is a complex and multi-disciplinary process, which demands a thorough understanding of all aspects from a global systems viewpoint. The objective of the paper is to present a preliminary design of important components of an HLFC system that helps in quick assessment of conceptual system architectures. This is important to evaluate feasibility, system performance, and overall aircraft benefits at early stages of system development. This paper also discusses the various important system requirements and issues concerning the design of active HLFC systems, and the interfaces between various disciplines are presented. It can be emphasized from the study that the future compressor design for the HLFC system should consider the thermal management aspects and additional mass flow requirements from the aerodynamics-structure design optimization and also from water drain system solutions. A method to calculate the accumulated water content inside the plenum chambers is presented, and the effect of a drain hole on the power consumption is studied. A low order thermal management study of the HLFC compressor motor shows a high temperature rise in the windings for very high speed motors for long duration operation and calls for effective cooling solutions.

Urban Air Mobility (UAM) is increasingly becoming popular for Passenger or Cargo movement in dense smart cities. Several researches so far are focused on individual vehicle architectures such as multirotor or tiltrotor etc., but not much effort in a System of Systems (SoS) point of view where a homogenous fleet of vehicle with different passenger capacity, speed, and propulsive energy concepts are assessed in a framework for a successful UAM operations in a given city. An effort is made in this paper wherein, vehicle architecture is derived from the Concept of Operations (CONOPS) of scenarios such as urban and suburban operations and as well as propulsion subsystem for sustainable UAM. This paper approaches UAM aircraft design driven by SoS approach and an agent-based simulation supports the vehicle architecture evaluation and fleet definition. The outcome of this study is: multiple aircraft design with subsystem architectures, ideal fleet size for the respective operational scenarios, autonomy and battery technology effectiveness on UAM throughput (to efficiently provide UAM on-demand service maximum passengers within 15 min wait time), and importantly, sustainability metrics such as total fleet energy required. Several System of Systems, system and subsystem level sensitivity research questions are addressed to understand the interlevel coupling.

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Integrating new functions into the aircraft can, for example, increase performance or reduce fuel consumption. Since the installation of such additional functions increases the overall aircraft complexity, it is crucial to adapt methods and tools that support the development and ensure traceability, consistency, and verifiability. In this context, model-based systems engineering and the associated Systems Modeling Language (SysML) have been established as a standard methodology. This paper presents an overview of a system development and modeling process with SysML at the concept design stage using a position-variable shock control bumps system as an example. In addition to the system modeling, safety and reliability analyses have to be considered during the design process. To keep both, the model and the associated safety assessment consistent, this work introduces an extension of SysML to enable the execution of a functional hazard assessment (FHA) according to the ARP4754A and ARP 4761 guidelines. This is the first step in conducting a model-based safety assessment. Furthermore, a modeling process with concepts management methods is performed. In summary, the presented modeling process consists of three main parts: the system modeling, functional hazard assessment and concept management.