Application of modern control theory to the design of optimum aircraft controllersA procedure is described for synthesis of optimal aircraft control systems by application of the concepts of optimal control theory to time-invariant linear systems with quadratic performance criteria. Essential in this synthesis procedure is the solution of the Riccati matrix equation which results in a constant linear feedback control law for an output regulator which maintains a plant in an equilibrium in the presence of impulse disturbances. An algorithm is derived for designing maneuverable output regulators with selected state variables for feedback.
Document ID
19740056746
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Power, L. J. (NASA Ames Research Center Moffett Field, Calif., United States)