Propellant stress relief groove for the Titan 4 SRMU

Details Propellant stress relief groove for the Titan 4 SRMU Propellant stress relief groove for the Titan 4 SRMU

Nov 1993

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993aero.reptr....c&link_type=abstract

Technical Report, Jan. 1991 - Jan. 1993 Aerospace Corp., El Segundo, CA.

Physics

Grooves, Pressure Distribution, Solid Propellant Rocket Engines, Solid Rocket Propellants, Stress Analysis, Titan 4 Launch Vehicle, Rocket Engine Design, Time Dependence

Scientific paper

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.

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