Most previous studies on flutter were focused on the prediction of the flutter speed
using numerical methods.
Using analytical techniques developed for linear flutter analysis, the critical flutter speed
is found to be U = [U.sub.f] = 6.0385.
This paper focused on a metal beamlike high-aspect-ratio wing model and optimized the beam section subjected to multiple aeroelastic constraints including the wingtip vertical displacement, the wingtip torsion angle, and the flutter speed
. Synthesizing the analysis in this paper, the following conclusions can be drawn.
[V.sub.NE], the redline on the airspeed indicator, is an indicated airspeed, but the critical flutter speed
may be a true airspeed.
Results of numerical dynamical tests natural vibration frequencies and their forms are used for the evaluation of critical flutter speed
. Upon building of a glider's prototype, its structural elements are weighed in, their rigidity is defined and ground dynamical tests (GDT) are conducted.
In many cases, the critical flutter speed
calculated with orthogonalization is lower than it is without orthogonalization.
Flutter suppression system (FSS) design: we set as design point the actual flutter speed
of the model [U.sub.des] = [U.sub.F] = 17.8[m/s]; for this condition, the controller (namely the minimum energy one) has been calculated as well as the state observer.
Other innovations resulting from wind-tunnel testing included installation of vertical plates at the bottom center of the highway deck to increase flutter speed
. Methods of improved prediction of flutter speed
and gust response will be used in future bridge designs.
Early last year the researchers conducted wind tunnel tests to gather experimental data that were used to calculate the flutter speed
, verify the accuracy of analytical models, plot transfer functions, and develop control laws.
The actuator is provoked as the relative speed of the motion reaches the flutter speed
. The influence of the thruster on the wing surface contains force and moment.
Using a flexibly supported airfoil prototype with a semichord of 0.125 m and a span length of 0.5 m, a power of 10.7 mW was measured at the linear flutter speed
of 9.30 m/s with an optimal load of 100 k[OMEGA].
In the present work, we are interested in proving the advantages of the LQG/LTR method, as a robust control approach applied in view of increasing flutter speed
or flutter alleviation.