Nonlinear Control of Missiles.

Abstract

The problem of designing flight control system for high performance anti-air missiles is discussed in this report. The research addresses three areas of missile autopilot design. The first area investigates the application of nonlinear H-infinity optimal control for an integrated aerodynamic/thrust vector controlled missile. The second area investigates the design of autopilots for missiles using on-off reaction control valve actuators. A sliding mode control law is developed using H-infinity design methods. The third area focused on developing nonconservative robustness analysis algorithms for gain scheduled missile autopilots.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1995
Accession Number
ADA305454

Entities

People

  • Jack L. Sedwick
  • Kevin A. Wise
  • Rowena L. Eberhardt

Organizations

  • McDonnell Douglas

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Control Surfaces
  • Aircrafts
  • Algorithms
  • Applied Mathematics
  • Automatic Pilots
  • Closed Loop Systems
  • Computational Science
  • Control Surfaces
  • Control Systems
  • Control Systems Engineering
  • Differential Equations
  • Flight Control Systems
  • Mathematics
  • Two Dimensional
  • Unmanned Aerial Vehicles
  • Unmanned Systems

Readers

  • Control Systems Engineering.
  • Maritime and Naval Warfare Studies