Propellant Stress Relief Groove for the Titan 4 SRMU

Abstract

A method has been developed to design a propellant stress relief groove (SRG) for solid rocket motors. The method considers a time-dependent pressure distribution in both burn-back and 'burn-forward' analyses and allows a desired bondline stress condition to be incorporated into the SRG design. Application of the method to obtain an improved propellant SRG for the Titan IV Solid Rocket Motor Upgrade (SRMU) is illustrated in this report. The improved propellant SRG obtained from this method for the Titan IV SRMU provides significant enhancement in the propellant structural margin of safety throughout motor firing. Titan IV solid rocket motor, Propellant, Stress analysis.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1993
Accession Number
ADA278628

Entities

People

  • I-shih Chang

Organizations

  • The Aerospace Corporation

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • High Temperature
  • Hydroxyl Terminated Polybutadiene
  • Internal Pressure
  • Margin Of Safety
  • Physical Properties
  • Pressure Distribution
  • Propellant Grains
  • Propellants
  • Rocket Engines
  • Rockets
  • Safety
  • Standards
  • Stress Analysis
  • Stress Concentration
  • Stresses
  • Structural Analysis

Fields of Study

  • Physics

Readers

  • Canine Service Warrior Training Program for Wounded Warriors in the Veterinary Industry, Supported by Donors.
  • Rocket Propulsion.
  • Tribology (the study of the boundary interaction between sliding surfaces, lubrication, wear and friction).