Abstract
Compared with general V/STOL (vertical/short taking-off and landing) aircrafts, the V/STOL aircraft based on deflected slipstream shows extremely different dynamic characteristics during the hovering phase. In this paper, a certain new type of V/STOL aircraft based on slipstream deflection is designed as research object. According to a simplified longitudinal dynamic model for the V/STOL aircraft based on deflected slipstream, it is proved that trim flap angle and centre of gravity position are two important factors during the hovering phase. Different flap angle means different trim state while the variation of centre of gravity position could change the range of trimming. Besides, modes of aircraft during the hovering phase are drawn and the law of eigenvalues changing as the variation of trim flap angle and center of gravity position is discovered. Regarding the findings as reference, the design of V/STOL based on deflected slipstream and control law design for V/STOL based on deflected slipstream during the hovering phase can be greatly improved.
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