Abstract The nonlinear differential equations governing the motion of an aircraft are described in Chap. 3. For the plant analysis and control design, these equations are linearized around a certain operating point. Two sets of state variables appear to be clearly decoupled, each defining a specific mode of aircraft motion. The state variables involved in the longitudinal mode are the pitch rate q, the airspeed V T , the angle of attack α, and the pitch angle θ. The lateral-directional mode involves the state variables for the roll rate p, the yaw rate r, the sideslip angle β, and the roll angle φ. This chapter is dedicated to the analysis and control of the longitudinal motion of the aircraft and presents an architecture for the altitude controller, which uses robust NDI in all of the control loops. This chapter brings an innovative and practical approach for stability and robustness analyses of the plant undergoing the dynamic inversion process. Moreover, this chapter provides a systematic procedure for the selection of some uncertain model parameters involved in the controllers. Finally, a new nonlinear airspeed controller is also designed and presented.
Autopilot for the Longitudinal Motion
2009-01-01
54 pages
Article/Chapter (Book)
Electronic Resource
English
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