Empirically Derived Helicopter Response Model and Control System Requirements for Flight in Turbulence

摘要

Flight test data from a UH-60 Black Hawk helicopter in turbulent conditions were used to determine control system disturbance rejection criteria and to develop a low speed turbulence model for helicopter simulation. A system identification approach to modeling the aircraft response to turbulence was used to extract representative control inputs that accurately replicate the aircraft response to disturbances. Parametric turbulence models that have a Dryden-type form and are scalable for varying levels of turbulence were developed. Estimates of flight control bandwidth for precision hover in turbulence were determined to support disturbance rejection flight control design and handling qualities criteria.