AN OPTIMUM INTERCEPTION LAW WITH BOUNDED CONTROL IN PRESENCE OF NOISE

Abstract

The subject of this report is the derivation of optimum control rule for guidance of a space vehicle which seeks to reach a moving target. The available thrust vector is assumed to be bounded in magnitude and any on-board measurements to be contaminated by random noise. The performance measure is chosen to be the expectation of terminal miss distance. The optimum control rule is shown to be a function of the sign of the expected value of line-of-sight angular rotation with respect to an inertial coordinate system and, consequently, measurement of this angular rate (e.g., by means of an angle tracking system) is sufficient to implement the optimum control rule. The optimum controller is very simple and more suited to space application than the conventional method of proportional navigation commonly used in missile systems operating in lower altitudes due to the desirability of using reaction jets in space vehicles.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1967
Accession Number
AD0820631

Entities

People

  • David C. Sworder
  • Nasser E. Nahi

Organizations

  • University of Southern California

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • California
  • Coordinate Systems
  • Differential Equations
  • Equations
  • Export Controls
  • Line Of Sight
  • Measurement
  • Miss Distance
  • Navigation
  • Partial Differential Equations
  • Space Systems
  • Spacecraft
  • Targets
  • Terminals
  • United States
  • Vehicles

Readers

  • Missile Defense Systems.
  • Radar Systems Engineering.
  • Regression Analysis.

Technology Areas

  • Space
  • Space - Spacecraft Maneuvers