Rotorcraft Fuselage Weight Assessment in Early Design Stages
2018
Like the design of fixed-wing aircraft the design of rotorcraft is generally divided into the three consecutive
phases of conceptual, preliminary and detailed design. During each phase the acquired results in turn serve
as input for new calculations, thus increasing the detail level and information about the new concept while
uncertainties about the new design are reduced. An important aspect of the overall design process is the
weight estimation in early design stages. The weight of the rotorcraft drives the design of many important
components, such as the rotor(s), the propulsion system and, therefore, the required fuel. The fuselage is
considered as the central structural part since it connects all other components to each other and serves as
protection of the occupants but in the past it often turned out to also be the heaviest part of all rotorcraft
components. This paper shows an approach to estimate rotorcraft component weights using statistical
methods based on existing rotorcraft but also an approach to use finite element methods that determine the
structural airframe weight based on mission profiles respectively bearable load cases.
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