FEASIBILITY DEMONSTRATION OF A LARGE IMPULSE SOLID ROCKET ATTITUDE CONTROL MOTOR. VOLUME 1

Abstract

A solid propellant propulsion system was designed consisting of individual tape-mounted solid propellant rocket motors, which are fed from a storage container into firing position by means of a stepping motor-driven sprocket wheel. The rocket motors are fired, on command, at any of three positions by a signal from an external electrical source. The operation of a typical system in an attitude control application, is shown schematically. Rocket motor optimization studies show that a rectangular motor configuration with an L/D ratio of 2:1 using a simple flat end-burning grain was optimum to provide minimum weight, volume, and sprocket wheel inertia. The design of the rocket motor was based on a quartz-phenolic base, a pre-molded rubber grain inhibitor, a silicone expandable (E) dome, CWP-13 propellant, and a pyrofuze wire pyrotechnic overspray ignition system. The weight of the WSR-101 rocket motor is .0246 pounds.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1966
Accession Number
AD0387671

Entities

People

  • Norman J. Rolleri

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Combustion
  • Composite Propellants
  • Heat Transfer
  • Ignition
  • Ignition Lag
  • Ignition Systems
  • Margin Of Safety
  • Materials
  • Materials Laboratories
  • Materials Processing
  • Materials Testing
  • Mechanical Properties
  • Mechanical Working
  • Mechanics
  • Tensile Testing
  • Test And Evaluation

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Electrical Engineering
  • Rocket Propulsion.