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@ARTICLE{Schmidt:858073,
      author       = {Schmidt, Hauke and Koh, S. and Dafnis, Athanasios and
                      Schröder, Kai-Uwe and Schröder, Wolfgang},
      title        = {{A}ccurate numerical simulation on the structural response
                      of the {VEGA} payload fairing using modal coupling approach},
      journal      = {CEAS space journal},
      volume       = {1},
      issn         = {1868-2510},
      address      = {Wien [u.a.]},
      publisher    = {Springer},
      reportid     = {FZJ-2018-06991},
      pages        = {1-11},
      year         = {2018},
      abstract     = {Structural aeroacoustic interactions are of great interest
                      in the design and manufacture of aerospace structures.
                      During the lift off and the early phases of the launch
                      various external loads like steady accelerations, random and
                      broadband frequency vibrations, acoustic loads due to jet
                      noise and fluid–structure interactions act on the
                      lightweight panel structure of the payload fairing. Thereby
                      internal vibrational loads and instability effects may be
                      caused by the interaction of various mechanical loads and
                      acoustic noise acting on the cylindrical shell structure.
                      Within the project “Prediction of Acoustic Loads on Space
                      Structures” funded by the European Space Agency (ESA) an
                      aeroelastic coupling approach has been built up. Therein,
                      the aerodynamic loads on the VEGA payload fairing (PLF) have
                      been determined for different flight conditions by the use
                      of the open-source CFD solver SU2. Due to the different
                      discretization between the computational fluid dynamics
                      (CFD) and computational structural dynamics (CSD) mesh the
                      approach of Radial Basis Function (RBF) has been used to
                      interpolate the resulting pressure distribution onto the
                      structural model. According to that the dynamic response of
                      the PLF has been analyzed by taking the basic aerodynamic
                      forces, structural vibration and acoustic pressure
                      fluctuations into account. An intrinsic part of this work is
                      the numerical simulation and assessment of the interaction
                      between structural vibrations, transonic flow and acoustic
                      pressure fluctuations during the early launch phase.},
      ddc          = {620},
      typ          = {PUB:(DE-HGF)16},
      doi          = {10.1007/s12567-018-0225-5},
      url          = {https://juser.fz-juelich.de/record/858073},
}