T. Klimmek, M. Schulze, M. Abu-Zurayk, C. Ilic, A. Merle

DOI Number: N/A

Conference number: IFASD-2019-028

The highly parameterized aeroelastic structural design process cpacs-MONA for simultaneous structural and aeroelastic design of the load carrying structure of an aircraft configuration is presented. The process consists of preliminary mass and loads estimation based on conceptual design methods followed by a parameterized set-up of simulation models and an optimization model. These models are used for a comprehensive loads analysis followed by a component wise structural optimization. The latter takes stress, strain, buckling and control surface efficiency as constraints into account. The detailed structural modelling allows also for the use of well-established structural optimization methods. The data basis for the simulation models and the various analyses is a suitable CPACS dataset. The design process cpacs-MONA is also part of various high-fidelity based MDO processes developed at DLR, where also other disciplines like for example aerodynamics and overall aircraft design are involved. In this paper three applications are presented for cpacs-MONA. In the first one cpacs-MONA is applied as an independent and stand-alone aeroelastic structural design process for the XRF1-DLR baseline configuration followed by the investigation of a number of geometrical variations regarding the wing aspect ratio and the wing sweep. Lastly the results for the structural design of cpacs-MONA are examined within the high-fidelity based MDO approach following the so-called cybermatrix protocol. Therein aerodynamic optimization, structural optimization, and loads analysis run independently in parallel with a coupling due to a regular exchange of defined parameters.

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In Categories: Aeroelastic Optimization Frameworkes, IFASD 2019
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