Alessandro Lurgo, Robert Jung

DOI Number: N/A

Conference number: IFASD-2017-119

Whenever the structure of an aircraft component is significantly flexible, change in aerodynamic surfaces due to the structural flexibility must be taken into account in order to accurately model the behaviour of the component under aerodynamic load. This paper describes an industrial quasi steady aeroelastic application of an iteractive Computational Fluid Dynamics (CFD) Computational Structure Mechanics (CSM) co-simulation approach. This kind of approach is expected to represent a substantial improvement in predicting loads on component level. In this paper the outboard flap system of a commercial aircraft is analysed. The model is built up with the commercial multibody software Adams. Particular care has been taken to model non-linear elements. The aerodynamic flow is modelled through steady non-linear Reynolds Averaged Navier-Stokes (RANS) equations, including the engine jet efflux on the outboard flap system. The flow field is solved using the DLR (‘National Aeronautics and Space Centre’) TAU code. A static analysis of the coupled system is presented. Towards the end of this paper, a test case for an unsteady Adams-TAU co-simulation of a wing is performed. The results are compared to a Nastran-Tau co-simulation of the same wing. This work represents a step towards the realization of an unsteady aeroelastic co-simulation of the outboard flap system using the multibody approach.

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In Categories: 1.Events, Computational Aeroelasticity, IFASD 2017
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