LQG法による航空機主翼の振動制御技術

概要

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In active vibration control technology, gust load alleviation and flutter suppression technologies are studied for aircraft. For this purpose, an aero-servoelastic analysis code was developed using the MSC/NASTRAN by MHI. Moreover, a control low-synthesis method was developed, being applied to LQG (linear quadratic Gaussian) method for reduced order control law design. To validate both the aeroservoelastic analysis and the control law synthesis code, the wind tunnel test of gust load alleviation was conducted in a 2m low-speed wind tunnel of Nagoya Aerospace Systems Works using an aeroelastic wind model equipped with an actively controlled trailing edge surface. Analysis results were compared with the results from tests and good agreement with test results was obtained for the wing acceleration. To estimate the effects of gust load alleviation and flutter suppression technologies, they were applied to a 150-passenger twin-engine commercial airplane. For gust load alleviation, a 46.9% wing bending moment reduction effect was presented and flutter suppression, 30.7% flutter speed augmentation effect was presented.
1991-09-25