The literature review is conducted through an appropriate search protocol to ensure the selection of the most relevant sources. This paper presents the current state-of-the-art in the development of future aircraft for civil aviation. For this reason, there is a strong drive to explore unconventional aircraft with the aim of reducing both environmental emissions and Direct Operating Cost. Nevertheless, aviation remains under intense pressure to become more sustainable. Advanced and well-established technologies such as active flow control systems, wing-tip devices, high bypass ratio engines, composite materials, among others, have demonstrated fuel-burn benefits by reducing drag and/or weight. In recent decades, the environmental impacts of aviation have become a key challenge for the aeronautical community. The framework demonstrates the capability of optimizing across multiple, different system architectures in an efficient way that is scalable for larger design spaces and larger dimensionality problems. The optimization process benefits from a data-driven localization step to identify sets of similar architectures. The performance of different architectures is analyzed with respect to key performance indicators (fuel burn, weight, power). It is demonstrated for the electrification of the Primary Flight Control System (PFCS) and the landing gear braking system using different electric actuation technologies. In addition, it enables the integration of models at multiple levels of fidelity depending on the size of the design space and the accuracy required. This framework enables the designer to prioritize different designs and offers traceability on the optimal choices. This paper focuses on some recent advancements in the MISSION project and presents a design framework that combines a filtering process to down-select feasible architectures, a modeling platform that simulates the power system of the aircraft, and a machine learning-based clustering and optimization module. The ModellIng and Simulation tools for Systems IntegratiON on Aircraft (MISSION) project aims to develop an integrated modelling and simulation framework. The push toward reducing the aircraft development cycle time motivates the development of collaborative frameworks that enable the more integrated design of aircraft and their systems. Keywords: Aerodynamic design, Bended-wing-body, Propulsion Airframe Integration, Stability and control, Structure Finally, further study aspects are advocated. The energy to revenue work ratios of well-developed BWB configurations are compared, which are 31.5% and 40% better than that of TAW, using state-of-art engine technology and future engine technology, respectively.

The difficulties of propulsion and airframe integration are analyzed. A static stability criterion is recommended and further clear and adequate criteria are required by the evaluations of flying and handling qualities. The structure concepts of non-cylinder pressurized cabin are of high risks on weight prediction and weight penalty. It was found that the high aerodynamic efficiency of BWB aircraft can be well scaled by the mean aerodynamic chord and wetted aspect ratio, and should be realized with the trade-offs among stability and control and low-speed performance. The purpose of the present work is to analyze the developments of critical technologies for BWB conceptual design from a historical perspective of technology progress. By past decades’ investigations the Blended-Wing-Body (BWB) concept has emerged as a potential solution, which can simultaneously fulfill metrics of noise, emission and fuel burn. The classical Tube-And-Wing (TAW) configuration following the Cayley’s design principles has been optimized to the architecture’s limit, which can hardly satisfy the further requirements on green aviation. Civil aviation faces great challenges because of its robust projected future growth and potential adverse environmental effects.

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