TERMINAL GUIDANCE OF AN AIR-TO-SURFACE MISSILE USING OPTIMAL CONTROL AND FILTERING.

Abstract

The optimal control of an air-to-surface missile is determined for a criterion with an integral quadratic weighting of state and control plus a quadratic weighting of terminal state. The controller is then simulated with the nonlinear equations of motion. The control law is capable of correcting errors in both translational and angular position which are determined relative to a nominal path. A Kalman filter is then employed to smooth the state signals which are corrupted by white noise. Representative values of noise, which characterize a range of optical seekers, are used. Greatly improved performance is obtained. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1967
Accession Number
AD0664336

Entities

People

  • Michael J. Breza

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Equations
  • Equations Of Motion
  • Filters
  • Filtration
  • Guidance
  • Integrals
  • Kalman Filters
  • Noise
  • Terminal Guidance
  • Terminals
  • White Noise

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Control Systems Engineering.
  • Missile Defense Systems.