THRUST VECTOR DETERMINATION FOR THE APOLLO SERVICE PROPULSION ENGINE USING A SIX-COMPONENT FORCE BALANCE

Abstract

A multicomponent force system was developed to determine the line of action of the forces generated by the Apollo Service Module engine. This force system was a force balance based on the principles of linear and repeatable installation tare effects. The basic concepts of the force balance and the statistical accuracies which were achieved are presented along with a detailed discussion of the calibration procedure and data reduction methods. Thrust vector excursion for two ablative combustion chambers during nongimbaling engine operation and limited thrust vector data during gimbaling operation are also presented. The precision of the thrust vector data was determined to be 0.033 deg for angular measurement and 0.026 in. for position determination.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1965
Accession Number
AD0475564

Entities

People

  • C. E. Robinson
  • R. B. Runyan

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Calibration
  • Chambers
  • Combustion
  • Combustion Chambers
  • Contractors
  • Data Acquisition
  • Data Reduction
  • Engineering
  • Engines
  • Equations
  • Government (Foreign)
  • Load Cells
  • Measurement
  • Service Modules
  • Test Facilities

Readers

  • Aerodynamics/Aeronautics.
  • Control Systems Engineering.
  • Rocket Propulsion.