Optimal Controllers for Homing Missiles

Abstract

Optimum control theory is applied to develop a guidance law for homing missiles. An existing, closed form, general solution of the 'minimum error regulator' problem is applied to a previously solved problem which uses a very simple plant model, in order to verify its applicability. The solution method is then applied to a system that includes autopilot lag, and in this case the optimum law is shown to differ from proportional navigation.

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Document Details

Document Type
Technical Report
Publication Date
Sep 11, 1968
Accession Number
AD0843725

Entities

People

  • G. Willems

Organizations

  • United States Army Aviation and Missile Command

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Automatic Pilots
  • Control Systems
  • Control Theory
  • Differential Equations
  • Digital Computers
  • Equations
  • Equations Of State
  • Export Controls
  • Government (Foreign)
  • Guidance
  • Homing
  • Line Of Sight
  • Navigation
  • Proportional Navigation
  • Regulators
  • Targets

Fields of Study

  • Mathematics

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Inertial Navigation Systems.