Anthony:
Anyone tried powered Li/Al alloy in solids? Or is the Li too small a
fraction to make any real difference?
Bill
On Sat, Mar 31, 2018 at 12:58 PM Anthony Cesaroni <acesaroni@xxxxxxxxxxx>
wrote:
…or magnesium/aluminum alloy all the way through. Amorphous silicon and
Al/Si alloys also work well in small motors. What you lose in impulse is
made up by the increase in combustion efficiency.
Anthony J. Cesaroni
President/CEO
Cesaroni Technology/Cesaroni Aerospace
http://www.cesaronitech.com/
(941) 360-3100 x101 Sarasota
(905) 887-2370 x222 Toronto
*From:* arocket-bounce@xxxxxxxxxxxxx [mailto:arocket-bounce@xxxxxxxxxxxxx]
*On Behalf Of *George William Herbert
*Sent:* Saturday, March 31, 2018 2:30 PM
*To:* arocket@xxxxxxxxxxxxx
*Subject:* [AR] Re: Accounting for cured HTPB in ProPEP
Idly wondering if aluminum up top and magnesium near bottom of cylindrical
motor might help...
-george
Sent from my iPhone
On Mar 31, 2018, at 10:04 AM, William Claybaugh <wclaybaugh2@xxxxxxxxx>
wrote:
Yeah, I looked over ISP’s product list and they clearly have a 235
second-ish propellant for less than about 15 lbsm propellant devices and a
250-ish second propellant for everything bigger.
Bill
On Sat, Mar 31, 2018 at 11:00 AM Henry Spencer <hspencer@xxxxxxxxxxxxx>
wrote:
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
