Abstract
The operating possibilities of semiactive control of landing gears aimed at application to general aviation aircraft are evaluated. Compared to fully active systems, this kind of control is simple, lightweight, and safe, its intervention being based on the modification of the oil orifice section only. This active control was designed by using a landing simulation code that allowed a reliable prediction of its effectiveness. The application of the active shock absorber to a nonflying prototype has been both numerically and experimentally investigated, by means of drop tests at different sink speeds. The setup, the control strategy, and the obtained results are described, and the measured responses are compared to simulation results. Good agreement between analytical and experimental results confirms that a heuristic tuning of the active control can be effective when adequate simulation tools are used in the design.
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