Abstract:
This paper presents the process of flight mechanical analysis and optimization of a helicopter tethering frame that is used in pilot training and research projects. An existing linear state space model of the CoAX 2D ultralight helicopter is fusioned with a parametrized analytical model of the tethering device. Using the eigenvalues of the free flying and tethered helicopter as a similarity measure, optimal values for the geometric parameters are calculated through bounded parameter optimization. In a separate section, the castor wheels that enable horizontal motion of the tethered helicopter are analyzed, yielding the parameters that are relevant for the dynamic behavior of the tethered helicopter and possible changes that should mitigate the flight mechanical effect of the wheels.