Dormant Missile Inertial Guidance and Control System. Phase I Study Program

Abstract

The results of a test program on a Rotating Pendulum Accelerometer (RPA) to determine its applicability to the Dormant Missile Inertial Guidance and Control System are presented. Test were performed primarily to determine stability and quick starting characteristics. The feasibility model originally fabricated was modified to attain the degree of quality expected of future models. The tests demonstrated feasibility, and performed in the manner predicted, showing the following characteristics: low noise, stability required by dormant system, ability to start quickly, and capability of perfect temperature compensation. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1963
Accession Number
AD0430863

Entities

Organizations

  • Sperry Corporation

Tags

Communities of Interest

  • Air Platforms
  • Autonomy

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Bearings
  • Clocks
  • Control Systems
  • Data Analysis
  • Gas Bearings
  • Guidance
  • Inertial Navigation
  • Measurement
  • Probability
  • Resonant Frequency
  • Standards
  • Test Equipment
  • Test Sets
  • Thermal Expansion
  • United States

Fields of Study

  • Physics

Readers

  • Aerospace Test and Evaluation
  • Computational Modeling and Simulation
  • Pulsed Power and Plasma Physics.