Abstract

In this paper, a new nonlinear H 1 control technique, called μ¡D H 1 method, is employed to design a missile longitudinal autopilot. The μ ¡D H 1 design has the same structure as that of linear H 1 , except that the two Riccati equations that are part of the solution process are state dependent. The μ ¡D technique yields suboptimal solutions to nonlinear optimal control problems in the sense that it provides an approximate solution to the Hamilton-Jacobi-Bellman (HJB) equation. It is also shown that this method can be used to provide an approximate closed-form solution to the state dependent Riccati equation (SDRE) and consequently reduce the on-line computations associated with the nonlinear H 1 implementation. A missile longitudinal autopilot design demonstrates the capabilities of μ¡D method. This new nonlinear H 1 design also shows favorable results as compared with the linear H 1 design based on the linearized model.

Department(s)

Mechanical and Aerospace Engineering

Sponsor(s)

Naval Surface Warfare Center

Keywords and Phrases

Riccati Equations; Control System Synthesis; Missile Control; Nonlinear Control Systems

Document Type

Article - Journal

Document Version

Final Version

File Type

text

Language(s)

English

Rights

© 2008 Institute of Electrical and Electronics Engineers (IEEE), All rights reserved.

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