Trailing Edge Flaps for Active Rotor Control Aeroelastic Characteristics of the ADASYS Rotor System

摘要

In the year 2005, a BK117 incorporating the ADASYS rotor system - the acronym is related to the German research project 'Adaptive Dynamische Systeme' (adaptive dynamic systems) - took off for the first flight. The four-bladed ADASYS rotor system is equipped with piezo-driven trailing edge flap units for active rotor control. In the meantime, the BK117 flew successfully with the flaps both in passive and active mode. Besides functionality tests, the already performed flights comprise a BVI noise reduction campaign and first tests for the adaptation of the vibration reduction controller. This paper gives an overview of the theoretical investigations and the related tests of the ADASYS rotor system. Emphasis is given on the aeroelastic characteristics and on the comparison with experimental results aiming towards the application of closed loop control of the active trailing edge flaps in flight for vibration reduction.