AN INTRODUCTION TO INERTIAL GUIDANCE CONCEPTS FOR BALLISTIC MISSILES (A TUTORIAL REPORT)

Abstract

Various aspects of guidance and control for ballistic missiles are presented. A discussion of the required velocity vector is given with several examples based upon the flat earth model. Error analysis procedures involving inertial reference and measurement systems are treated in some detail. Missile steering techniques are approached in such a way that stability is not a problem. Procedures for insuring that the missile velocity will be controlled to the required velocity without payload loss penalties are given. This is accomplished by introducing trajectory-shaping functions that cause the guided ballistic missile to closely follow the nominal reference trajectory. The steering discussion initially assumes a point mass missile. Control system complications that result from actual missile dynamics are also treated.

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Document Details

Document Type
Technical Report
Publication Date
Mar 15, 1961
Accession Number
AD0259865

Entities

People

  • David W. Whitcombe

Organizations

  • The Aerospace Corporation

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Accelerometers
  • Aerodynamic Forces
  • Air Force
  • Angular Momentum
  • Ballistic Missiles
  • Control Systems
  • Coordinate Systems
  • Free Flight
  • Free Flight Trajectories
  • Geometry
  • Guidance
  • Inertial Navigation
  • Inertial Navigation Systems
  • Measurement
  • Navigation
  • Specifications
  • Stabilized Platforms

Readers

  • Control Systems Engineering.
  • Missile Defense Systems.
  • Software Engineering