THEORY OF ARTIFICIAL STABILIZATION OF MISSILES AND SPACE VEHICLES WITH EXPOSITION OF FOUR CONTROL PRINCIPLES

Abstract

The theory of artificial stabilization of missiles and space vehicles in propelled flight is derived by a more rigorous method than has been done in the past. The relationship between the rotary loop and path loop in their reactions to artificial stabilization schemes is emphasized. The path reaction modes are classified by setting them into relation to two singular solutions, the drift minimum and load minimum modes. Two interesting other control modes are developed, concerned with local lateral acceleration along the missile axis. These are the maximum comfort control mode and the method of controlling the center or hinge point of the motion resulting from the combination of the rotary with the path motion.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1961
Accession Number
AD0257797

Entities

People

  • R. F. Hoelker

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Accelerometers
  • Air Force
  • Angular Acceleration
  • Capillary Electrophoresis
  • Center Of Gravity
  • Command And Control
  • Command And Control Systems
  • Command Control Communications
  • Equations
  • Government Procurement
  • Measuring Instruments
  • Molecular Dynamics
  • Plastic Explosives
  • Spacecraft
  • Steady State
  • Wind
  • Wind Velocity

Fields of Study

  • Mathematics

Readers

  • Aerodynamics/Aeronautics.
  • Aviation Science / Aeronautics.
  • Theoretical Analysis.

Technology Areas

  • Space
  • Space - Spacecraft Maneuvers