Answer Happy

(b) For the system in (a), determine the sensitivity of the
transfer function to changes in the gain 𝐾1.
The space shuttle is steered using an on-board guidance controller which determines the desired attitude. The ascent autopilot uses the errors between the measured and determined target attitude through the angular position, velocity and accelerations to gimbal the space shuttle main engines and the solid rocket boosters to effect the desired vehicle attitude. A simplified version of the pitch controller is given below in Figure Q2. Commanded Commanded pitch pitch rate acceleration Shuttle Commanded Controller dynamics pitch + Pitch G](s) G2(8) 今日今日 Pitch error Pitch rate error Pitch acceleration error Accelerometer 52 Rate gyro S Inertial measuring unit 1 FIGURE Q2 Find the closed-loop transfer function Tp(s) relating measured pitch to commanded pitch. Assume all other inputs are zero.