Longer ago, a YouTube video could be consulted about how in the Shuttle SRB
interior, the liner on the insulation layer was manually painted with sort of
large brushes. While lying horizontally. The applied inhibitor liner shown was
oozy & black. As to how many layers were applied was not mentioned. Neither do
I have an idea which insulation layer material bonded to the case was chosen
(asbestos filled rubber?) nor why zinc chromate putty was used. The gap called
“propellant relief flap” on the 2nd drawing is unclear (to me).
Regarding the drawing scale, the propellant wall thickness may on the average
have been thicker than presented (?). It had a star core.
The field segment joint drawing shows the insulation layer/liner combo on top
of the propellant was considerably thicker than the thin casing wall thickness.
The Shuttle SRB casings were steel originally. I have so far not found if later
versions were filament wound.
NB: both above drawings depict the unaltered joint design before the Challenger
failure.
John
From: arocket-bounce@xxxxxxxxxxxxx [mailto:arocket-bounce@xxxxxxxxxxxxx] On
Behalf Of Mark C Spiegl
Sent: zaterdag 3 februari 2018 7:05
To: arocket@xxxxxxxxxxxxx
Subject: [AR] Re: Phenolic regression rate
William Claybaugh wrote:
Was some part of the liner in your core burning motors exposed to the hot
gas?
If so, then that would suggest about 0.25" of phenolic based liner for ten
seconds, consistent w/ others data.