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@PHDTHESIS{Schtt:764354,
      author       = {Schütt, Marten},
      othercontributors = {Moormann, Dieter and Alles, Wolfgang},
      title        = {{F}lugzustandsregler für {K}ippflügel-{F}luggeräte mit
                      hohen {F}lugleistungen},
      school       = {Rheinisch-Westfälische Technische Hochschule Aachen},
      type         = {Dissertation},
      address      = {Aachen},
      reportid     = {RWTH-2019-06783},
      pages        = {147},
      year         = {2019},
      note         = {Veröffentlicht auf dem Publikationsserver der RWTH Aachen
                      University; Dissertation, Rheinisch-Westfälische Technische
                      Hochschule Aachen, 2019},
      abstract     = {The wide flight envelope of tilt-wing aircraft includes
                      VTOL and high flight speeds, making them attractive for
                      various applications such as inspection, air delivery and
                      air taxi. The different flight states -from thrustborne to
                      liftborne- place high demands on the design of aircraft and
                      control system. Thanks to current technologies, tilt-wing
                      aircraft can be designed unstable to achieve high flight
                      performance. Nevertheless, stabilization is a mandatory
                      criterion which must always be fulfilled. The required
                      flight controller must therefore ensure stabilization
                      throughout the entire flight envelope while enabling high
                      flight performance. In this work, a flight state controller
                      is designed and evaluated which finds a compromise to
                      achieve high flight performance while maintaining the
                      required flying qualities for tilt-wing aircraft. This
                      supports the ability to shift the design objectives of
                      tilt-wing aircraft to good flight performance. The
                      contradictory goals of high flight performance and good
                      flying qualities on the one hand and the conflicting
                      requirements for high flight performance in different flight
                      conditions on the other are discussed. The designed flight
                      state controller enables an optimal compromise between these
                      contradictory goals based on the consideration of predefined
                      criteria. Feedforwarding a trim control vector allows
                      stationary flight in the entire flight envelope. For the
                      usually large number of manipulated variables, a suitable
                      trim control vector is selected on the basis of different
                      criteria of flight performance and flying qualities. A
                      control allocation preserves the control reserves required
                      for stabilization and generates a compensated control
                      deflection by applying the pseudoinverse. The reserve of the
                      manipulated variable is taken into account implicitly by an
                      artificial reduction of the control effectiveness. The
                      designed approach of the flight state controller is applied
                      to an example aircraft with high flight performance and a
                      large number of control variables. The functionality of the
                      approach is proven by means of a nonlinear simulation and
                      final flight tests.},
      cin          = {415410},
      ddc          = {620},
      cid          = {$I:(DE-82)415410_20140620$},
      typ          = {PUB:(DE-HGF)11},
      doi          = {10.18154/RWTH-2019-06783},
      url          = {https://publications.rwth-aachen.de/record/764354},
}