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Unformatted text preview: Aircraft Stabilization I. PHYSICAL DESCRIPTION AND SYSTEM EQUATIONS The equations governing the motion of an aircraft are a complex set of nonlinear coupled differential equations. However, under certain assumptions, they can be decoupled and linearized into the longitudinal and lateral equations. Pitch control is a longitudinal problem, and in this example, you are asked to design an autopilot that controls the pitch of an aircraft. Assume that the aircraft is in steadycruise at constant altitude and velocity; thus, the thrust and drag cancel out and the lift and weight balance out each other. Also, assume that change in pitch angle does not change the speed of an aircraft under any circumstance (unrealistic but simplifies the problem). Under these assumptions, the longitudinal equations of motion of an aircraft can be written as ˙ α = − . 44 α + 55 . 2 q + 0 . 2 δ ˙ q = − . 012 α − . 55 q + 0 . 03 δ ˙ θ = 55 . 2 q (1) where α ( t ) denotes the angle of attack, δ ( t...
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This note was uploaded on 08/23/2011 for the course EML 4312 taught by Professor Dixon during the Spring '07 term at University of Florida.
 Spring '07
 Dixon
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