COMBUSTION TERMINATION SYSTEM FOR 120-INCH-DIAMETER SOLID ROCKET MOTOR (TITAN III-C).

Abstract

An investigation was made of combustion termination of solid propellant motors by liquid injection. The program consists of four tasks, which include laboratory and small-motor testing, subscale testing, and system demonstration in a 120-in.-diameter solid-propellant motor. A total of 4 laboratory motor and 19 small-motor (TM-1) tests were performed to evaluate several injection systems and to provide data for the study of the fundamental phenomena of combustion termination by liquid injection. In addition, 22 laboratory cold flow tests were conducted to evaluate injector flow patterns. As a result of these tests, a pintle-type injector was selected for further evaluation in the subscale (TM-3A) motor firings. Data obtained during the test program have been analyzed, and a correlation between the requirements of water flow rate and total water quantity and the motor ballistic properties was established. (Author)

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1965
Accession Number
AD0476521

Entities

People

  • F. B. Nelson

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Buildings And Structures
  • Combustion
  • Creep
  • Demonstrations
  • Diameters
  • Flow
  • Flow Rate
  • Injectors
  • Materials Laboratories
  • Propellants
  • Research Facilities
  • Rocket Engines
  • Rockets
  • Solid Propellants
  • Water Flow

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Rocket Propulsion.