The cantilever beam shown in Figure 2.1 is subjected to linearly distributed loads. a) Draw all necessary free-body diagrams using the method of sections and find symbolic expressions for the internal shear force (V(x)) and bending moment (M(x)) due to the external forces as functions of x, where x is a horizontal coordinate along the length of the beam, measured from the most left support of the beam. Your expression(s) must allow to obtain internal reactions for 0

The figure shows level curves of a function f(x,y). Draw gradient vectors at Q and T. Is f(Q) longer than, shorter than, or the same length as vf(T)?

The "Yaw Damper System" provides airplane stabilization about the yaw axis. The Yaw Damper minimizes dutch roll during flight by providing rudder displacement proportional to, and opposing, the yaw rate of the airplane. Transfer function of the yaw damper is taken as: 4.833 yaw rate rudder angle (s+0.551)(s+0.1 ±0.541*i) (s+0.616)(s +0.058+ i)(s+0.007) a) Give a brief knowledge about yaw dampers. b) Draw and interpret "root-locus" graphic of this transfer function. c) Draw and interpret the yaw rate distribution according to time.