Accession Number:

ADA278628

Title:

Propellant Stress Relief Groove for the Titan 4 SRMU

Descriptive Note:

Technical rept. Jan 1991-Jan 1993

Corporate Author:

AEROSPACE CORP EL SEGUNDO CA

Personal Author(s):

• Chang, I-Shih

Report Date:

1993-11-01

Pagination or Media Count:

31.0

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.

Descriptors:

• *STRESS ANALYSIS
• *SOLID PROPELLANT ROCKET ENGINES
• DISTRIBUTION
• AUGMENTATION
• SOLIDS
• TIME
• ROCKETS
• MARGIN OF SAFETY
• PROPELLANTS
• SAFETY
• MOTORS
• ROCKET ENGINES
• PRESSURE DISTRIBUTION

Subject Categories:

• Mechanics
• Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE