Abstract:

A method is given for the calculation of stability and control of a hclicopctr in flight condition with lateral velocity. The rotory wing dynamic model considered is the model of flap-pitch （including the clastic deformation of control system）-torsion coupling. The induced velocity distribution derived by generalized voricx theory is taken into account. Excepting the influence of the lateral velocity on the stability and control, the c.g-a.c-e.c offset, Wade control system stiffness and blade forsional stiffness on the stability and control arc also considered.

Key words: the stability and control of helicopter, induced velocity distribution, flap-pitch-torsion coupling, lateral wind