Affiliations: ASELSAN Inc., MGEO Division, 06511 Akyurt, Ankara,
Turkey | Department of Mechanical Engineering, Faculty of
Engineering and Architecture, Gazi University, 06570 Maltepe, Ankara,
Turkey
Note: [] Corresponding author: Dr. Uğur Dalli, ASELSAN Inc. MGEO
Division, 06511 Akyurt, Ankara, Turkey. Fax: +90 312 847 5320; E-mail:
[email protected]
Abstract: An active control method utilizing the multiple trailing edge flap
configuration for rotorcraft vibration suppression and blade loads control is
presented. A comprehensive model for rotor blade with active trailing edge
flaps is used to calculate the vibration characteristics, natural frequencies
and mode shapes of any complex composite helicopter rotor blade. A computer
program is developed to calculate the system response, rotor blade root forces
and moments under aerodynamic forcing conditions. Rotor blade system response
is calculated using the proposed solution method and the developed program
depending on any structural and aerodynamic properties of rotor blades,
structural properties of trailing edge flaps and properties of trailing edge
flap actuator inputs. Rotor blade loads are determined first on a nominal rotor
blade without multiple active trailing edge flaps and then the effects of the
active flap motions on the existing rotor blade loads are investigated.
Multiple active trailing edge flaps are controlled by using open loop
controllers to identify the effects of the actuator signal output properties
such as frequency, amplitude and phase on the system response. Effects of using
multiple trailing edge flaps on controlling rotor blade vibrations are
investigated and some design criteria are determined for the design of trailing
edge flap controller that will provide actuator signal outputs to minimize the
rotor blade root loads. It is calculated that using the developed active
trailing edge rotor blade model, helicopter rotor blade vibrations can be
reduced up to 36% of the nominal rotor blade vibrations.
