Optimal Controllers for Homing Missiles With Two Time Constants

Abstract

Optimum control theory is applied to develop a guidance law for homing missiles for which the airframe dynamics is not neglected. This work extends the applicability of the laws derived in a previous report to systems characterized by two time constants. The effectiveness of the optimum controller thus derived is evaluated in an example by comparing it with classical proportional navigation. Additionally, extensive quantitative plots of the controller parameters are provided as an aid in specific designs.

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Document Details

Document Type
Technical Report
Publication Date
Oct 09, 1969
Accession Number
AD0862093

Entities

People

  • G. C. Willems

Organizations

  • United States Army Aviation and Missile Command

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Altitude
  • Computational Complexity
  • Computations
  • Control Systems
  • Control Theory
  • Differential Equations
  • Equations
  • Equations Of State
  • Guidance
  • Homing
  • Mathematical Filters
  • Miss Distance
  • Navigation
  • Power Spectra
  • Proportional Navigation
  • Simulations
  • Targets

Fields of Study

  • Mathematics

Readers

  • Control Systems Engineering.
  • Systems Analysis and Design