Spring 2003 16.61AC3-2 Aircraft Lateral Dynamics Using a procedure similar to the longitudinal case, we can develop the equa tions of motion for the lateral dynamics A r+ Bu,a p, u da and v=r sec Bo os 8o +1N)(+1N)(+N) (IAL 0 tan Bo Ix=(IxxIzz-12x)/Izz IZz=(IxxIxz-I/Ixx Ix/(Is d 0 B 0Spring 2003 16.61 AC 3–2 Aircraft Lateral Dynamics • Using a procedure similar to the longitudinal case, we can develop the equa￾tions of motion for the lateral dynamics x˙ = Ax + Bu , x =         v p r φ         , u =   δa δr   and ψ˙ = r sec θ0 A =              Yv m Yp m Yr m − U0 g cos θ0 (Lv I
xx + I
zxNv) (Lp I
xx + I
zxNp) ( Lr I
xx + I
zxNr) 0 (I
zxLv + Nv I
zz ) (I
zxLp + Np I
zz ) (I
zxLr + Nr I
zz ) 0 0 1 tan θ0 0              where I
xx = (IxxIzz − I2 zx)/Izz I
zz = (IxxIzz − I2 zx)/Ixx I
zx = Izx/(IxxIzz − I2 zx) and B =         (m)−1 0 0 0 (I
xx)−1 I
zx 0 I
zx (I
zz)−1 000         ·      Yδa Yδr Lδa Lδr Nδa Nδr      2