NASA-LLIS-0176

Lessons Learned - Solid Rocket Motor (SRM) Field Joints and Configuration

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T18:13:25Z
date available	2017-09-04T18:13:25Z
date copyright	33900
date issued	1992
identifier other	HEZCQCAAAAAAAAAA.pdf
identifier uri	http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/196401
description abstract	Description of Driving Event: The primary reason for the use of the putty in the SRM was to act as a thermal barrier in the joints to prevent o-ring erosion resulting from circumferential hot gas flow during motor firing. Prior to the 51-L mishap, the putty was believed to perform such that it would allow pressure to the primary oring during the SRM ignition transient. Subsequently, it has been found that humidity and temperature enhance the characteristics of putty relative to its pressure holding characteristics. The uncertainty of these characteristic changes directly affected the ability of the field joint to seal.
language	English
title	NASA-LLIS-0176	num
title	Lessons Learned - Solid Rocket Motor (SRM) Field Joints and Configuration	en
type	standard
page	2
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1992
contenttype	fulltext
subject keywords	Flight Equipment
subject keywords	Hardware
subject keywords	Test & Verification