Boost-Phase Steering for Surface-Launched Cruise Missiles,

Abstract

Implementation of boost-phase control for steering surface-launched cruise missiles to initiation of aerodynamic flight is presented. The algorithm is based on the solution of the Matrix Ricatti equation in a pseudo time domain in which the duration of booster burn is invariant. The resulting design achieves maximum launch performance in all expected environmental conditions with minimum impact on software requirements. Identification of coefficients requires little computational effort and time compared to alternative methods and is easily modified to accommodate alternate configurations and launchers. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1982
Accession Number
ADP001072

Entities

People

  • D. J. Fromnes

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Algorithms
  • Boost Phase
  • Coefficients
  • Control Theory
  • Cruise Missiles
  • Equations
  • Flight
  • Identification
  • Launchers
  • Michigan
  • Phase Control
  • Steering
  • Surface Launched
  • Time Domain

Readers

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