Sergey N. Gartsev, Anton V. Dolgopolov, Vsevolod I. Smyslov

DOI Number: N/A

Conference number: IFASD-2015-113

Numerical investigation of unmanned aerial vehicle (UAV) dynamic system “Allmoving control surface actuator” with two types of nonlinearities backlash and dead zone was performed. In both cases were considered vibrations without flow and flutter boundaries. For flutter margin analysis, where partial frequencies are in demand, method of recalculation of known mode shapes and frequencies is given. In addition, subsidiary experimental procedure is proposed.

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In Categories: 2. IFASD 2015, Aeroelastic Response & Stability
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