Nonlinear Control Theory for Missile Autopilot Design.

Abstract

Bank-to-turn steering is attractive in terms of potential performance improvements over skid-to-turn steering. In order to fully realize this performance, attitude maneuvers in response to guidance system commands will sometimes take place at high body rates and angle-of-attack, where the dynamics are nonlinear. The problem is further complicated by constraints on angle of attack, control surface deflections and body rates. It appears that linear control methods may be inadequate in these cases. In this paper we consider several nonlinear control approaches. A decoupling controller is derived and shown to be well-defined (nonsingular). Conditions for constraint avoidance are derived. Stability is analyzed in the presence of estimation errors. A minimium-time control law which takes constraints into account is derived, resulting in a bang-bang controller. Keywords: equations of motion; short range air to air weapons.

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Document Details

Document Type
Technical Report
Publication Date
Apr 24, 1987
Accession Number
ADA183062

Entities

People

  • Donald E. Gustafson
  • John Baillieul
  • Mark Levi

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Automatic Pilots
  • Boundary Value Problems
  • Contracts
  • Control Surfaces
  • Control Systems
  • Control Systems Engineering
  • Decoupling
  • Dynamic Pressure
  • Equations
  • Equations Of Motion
  • Feedback
  • Governments
  • Guidance
  • Maneuvers
  • Measurement
  • Nonlinear Systems
  • Surfaces

Readers

  • Calculus or Mathematical Analysis
  • Control Systems Engineering.
  • Robotics and Automation.