Reinhard:
I’ve been pulling together a spread sheet that includes this data. Once I
have most everything I can find I’ll offer it to anyone interested.
Bill
On Sat, Feb 3, 2018 at 9:29 AM Reinhard Rath <reinhard.rath@xxxxxxxxx>
wrote:
You can find quite some data on HPR motors on Aerotechs sites. The burn
time and configuration can be found in the instructions [1] and assembly
drawings [2]. The thickness of their standard liner can be found on
rocketmotorparts.com [3].
On the extreme end of the spectrum, motors like the N1000 moon burner have
less than 0.25mm of liner thickness per second of burn time, although
typical motors are >= 0.4mm/s in a BATES configuration.
Information on ATs propellant and liner properties is not public, so it is
unclear if their numbers are applicable to other designs.
Reinhard
[1] http://www.aerotech-rocketry.com/resources.aspx?id=4
[2] http://www.aerotech-rocketry.com/resources.aspx?id=6
[3]
https://www.rocketmotorparts.com/Phenolic_Liners,_Uncut_Lengths/cat1577810_1455513.aspx
On 31.01.2018 at 21:07 William Claybaugh wrote:
Does anyone have any data on how long I can expect XX phenolic to survive
the conditions in a solid rocket motor?
Anecdotal data helps: if some part of the phenolic wall was fully exposed
to hot gas and was xx.xx inches or millimeters thick and did not fail;
that’s data. If it did fail, that is data too.
I’m adept at squeezing trends out of limited data but 20 or so usable data
points are sort of a minimum; I’m very happy to share any conclusions I may
reach.
Bill