NASA-LLIS-0224

Lessons Learned - Flight Hardware Performance Evaluation

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T15:51:49Z
date available	2017-09-04T15:51:49Z
date copyright	33928
date issued	1992
identifier other	QKZCQCAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/54982
description abstract	Description of Driving Event: During a hardware performance evaluation, Solid Rocket Motor (SRM) clevis and tang sealing surface diameters were assumed to be stable and were not remeasured during refurbishment. Subsequent testing revealed growth in the diameters after hydroproof (and possibly flight) which introduced an unrecognized variable into o-ring squeeze calculations. The static o-ring compression after mating is influenced by these actual hardware dimensions and the degree of segment concentricity, and are critical to hardware performance. During the STS 51-L Investigation, measurements were made on refurbished and reused segments, and the data indicated that segment circumferences at the sealing surfaces change with repeated use.
language	English
title	NASA-LLIS-0224	num
title	Lessons Learned - Flight Hardware Performance Evaluation	en
type	standard
page	2
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1992
contenttype	fulltext
subject keywords	Parts Materials & Processes
subject keywords	Test & Verification