Abstract
Experimental measurement of rigid body mass properties, specifically pitch inertia, of aircraft is becoming increasingly important for flutter analysis. This paper proposes a methodology for calculating rigid body inertia properties when the flexible modes of an aircraft are coupled to some degree with their corresponding rigid body modes, i.e. the rigid body modes are not fully rigid. The methodology will be demonstrated on a simple analysis model of a plate-like structure where the rigid body and primary flexible structural modes are coupled.
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