Using the Dutch roll approximation, determine the state feedback gains so that the damping ratio and frequency of the Dutch roll are 0.3 and 1.0 rad/s, respectively. Assume the airplane has the following characteristics:

Y = -19.5 ft/s Ng=1.5s- = 4.7 ft/s uo = 400 ft/s Yor Y,= 1.3 ft/s N,= -0.21 S- Nor= -0.082 s-