Abstract
State Dependent Algebraic Riccati Equation (SDRE) technique is rapidly emerging as a design method, which provides a systematic and effective means of designing nonlinear controllers, observers and filters. This paper describes a new method of integrating the SDRE technique with the Dynamic Inversion control law that is frequently used in the design of aircraft control systems. This technique when applied to the design of a control system for a flight vehicle is shown to improve the stability and performance characteristics. Nomenclature ( φ θ ψ ) = Euler Angles of Rotation ( p q r ) = Angular Velocities ( U V W ) = Linear Velocities ( L M N ) = Generalized Moments ( Fx Fy Fz ) = Generalized Forces ( Jx Jy Jz Jxz ) = Moments of Inertia
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