[AR] Re: Accounting for cured HTPB in ProPEP
- From: Henry Spencer <hspencer@xxxxxxxxxxxxx>
- To: Arocket List <arocket@xxxxxxxxxxxxx>
- Date: Sat, 31 Mar 2018 12:59:55 -0400 (EDT)
On Sat, 31 Mar 2018, William Claybaugh wrote:
Given a homogeneous mix, it would seem that the propellant at the bottom
of an SRB would be no further from the nozzle then the propellant at the
top of a 9"diameter motor (of 70" grain length)...
Although that's the worst case for the SRB, and the best case for the 9"
motor -- the *average* kilogram of propellant is rather farther away in
the SRB.
Still, Sutton8 says that even in the Star 27 apogee motor -- which is
near-spherical, 800lb gross weight, with relatively short gas paths -- the
propellant is 16% aluminum. Given that this is a "final stage", I'd think
its details would be well optimized. Clearly there are some subtleties
here.
Henry
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