The complete set of equations governing the motion of an aircraft are six nonlinear coupled differential...

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The complete set of equations governing the motion of an aircraft are six nonlinear coupled differential equations. Under certain assumptions, they can be decoupled and linearized into longitudinal and lateral equations. Aircraft pitch is governed by the longitudinal dynamics. In this project you will design an autopilot that controls the pitch of a Boeing 747 aircraft. The basic coordinate axes and forces acting on an aircraft are shown in the figure given below. $ U vi Drag = Weight Lift Figure 1 We will assume that the aircraft is in steady-cruise at constant altitude and velocity; thus, the thrust, drag, weight, and lift forces balance each other in the x- and y-directions. We will also assume that a change in pitch angle will not change the speed of the aircraft under any circumstance. Under these assumptions, the state-space longitudinal equations for a Boeing 747 aircraft in horizontal flight at a nominal speed U-820 ft/sec at 20,000 ft (Mach 0.8) are: * = Ax + B8 8 = Cx -0.01286 0.0526 -0.1882 -1.248 -0.000444 -0.00306 0 0 Thrust 0 1640 -1.336 -2 0 = [0 0 0 1] -2.41 u 9 U W 8 + [ 0 ]8 Eq. (1) Eq. (2) 0 -65.4 -4.16 8 Eq. (4) where u is the velocity in the direction of x, w is the velocity in the z direction, q is pitch rate, is pitch angle and is the elevator deflection angle The complete set of equations governing the motion of an aircraft are six nonlinear coupled differential equations. Under certain assumptions, they can be decoupled and linearized into longitudinal and lateral equations. Aircraft pitch is governed by the longitudinal dynamics. In this project you will design an autopilot that controls the pitch of a Boeing 747 aircraft. The basic coordinate axes and forces acting on an aircraft are shown in the figure given below. $ U vi Drag = Weight Lift Figure 1 We will assume that the aircraft is in steady-cruise at constant altitude and velocity; thus, the thrust, drag, weight, and lift forces balance each other in the x- and y-directions. We will also assume that a change in pitch angle will not change the speed of the aircraft under any circumstance. Under these assumptions, the state-space longitudinal equations for a Boeing 747 aircraft in horizontal flight at a nominal speed U-820 ft/sec at 20,000 ft (Mach 0.8) are: * = Ax + B8 8 = Cx -0.01286 0.0526 -0.1882 -1.248 -0.000444 -0.00306 0 0 Thrust 0 1640 -1.336 -2 0 = [0 0 0 1] -2.41 u 9 U W 8 + [ 0 ]8 Eq. (1) Eq. (2) 0 -65.4 -4.16 8 Eq. (4) where u is the velocity in the direction of x, w is the velocity in the z direction, q is pitch rate, is pitch angle and is the elevator deflection angle

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block diagram for an autopilot system involves several components Here is a highlevel conceptual dia... View the full answer