AN OPTIMAL LINEAR FEEDBACK GUIDANCE SCHEME

Abstract

A theory developing a linear feedback guidance scheme to correct for inflight disturbances of a vehicle during the course of a space mission is presented. The theory is predicated on the use of a nominal optimal trajectory. The scheme consists of a linear combination of: (1) perturbations of the vehicle state from its nominal state; and (2) time-varying gains to determine the control correction required to satisfy the constraints of the trajectory in an optimal fashion. Exact knowledge of the state of the vehicle is assumed. An analysis of numerical results for an idealized rocket trajectory problem shows the linear feedback guidance scheme to be effective over a wide range of chosen perturbations.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1963
Accession Number
AD0405813

Entities

People

  • Jarrell R. Elliott
  • Stuart E. Dreyfus

Organizations

  • RAND Corporation

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Altitude
  • Boundaries
  • Calculus Of Variations
  • Coefficients
  • Computational Science
  • Computer Programs
  • Computers
  • Difference Equations
  • Differential Equations
  • Equations
  • Government Procurement
  • Rocket Trajectories
  • Space Missions
  • Trajectories
  • United States

Fields of Study

  • Physics

Readers

  • Control Systems Engineering.
  • Systems Analysis and Design

Technology Areas

  • Space
  • Space - Spacecraft Maneuvers