Abstract
To face the increasing environmental footprint of commercial aviation, industrial and research efforts have been focusing on exploring unconventional configurations and new propulsion paradigms, mostly based on electric technology. Such explorations require Overall Aircraft Design that has to be performed in an integrated multidisciplinary design environment. Such design environments are often limited to multidisciplinary analysis, adapted for a single aircraft configuration or require an important effort to be mastered. FAST-OAD is a software program developed by ONERA and ISAE-SUPAERO for aircraft sizing analysis and optimization that aims at user friendliness and modularity. It is an aircraft sizing code based on multidisciplinary design optimization techniques and the point mass approach to estimate the required fuel and energy consumption for a given set of TLARs. This paper presents the motivations for moving from the original software program, called FAST, to the open source code FAST-OAD based on OpenMDAO.
Highlights
To face the increasing environmental footprint of commercial aviation, industrial and research efforts have been focusing on exploring unconventional configurations and new propulsion paradigms, mostly based on electric technology
At the University of Michigan, the MDOLab focuses on the accurate and efficient computation of derivatives to aid gradient-based optimization methods and collaborates with NASA in the development of OpenMDAO [3], a framework to facilitate the application of Multidisciplinary design optimization (MDO)
Architecture The architecture of the open source code FAST-Overall Aircraft Design (OAD) has been organized as shown in Figure 3 and is implemented using the OpenMDAO framework to benefit from its efficient Multidisciplinary Design Analysis and Optimization (MDAO) capabilities [3]
Summary
To face the increasing environmental footprint of commercial aviation, industrial and research efforts have been focusing on exploring unconventional configurations and new propulsion paradigms, mostly based on electric technology. The resizing block acts on the wing position, the main landing gear position, and sizing of the horizontal and vertical tail plane to have a design that verifies a static margin objective This requires an aerodynamic analysis to determine the aerodynamic center and the weights analysis to determine the different mass used for the equilibrum. The highest level loop takes care of converging the initial guess for Maximum TakeOff Weight (MTOW) and the one computed after the performance analysis has computed the fuel required for the mission. This multidisciplinary design analysis process has been validated on a conventional short medium range commercial aircraft [10]. This big picture has been used to build the road map of FAST-OAD presented
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