HNF, HMX, polyNMMO plasticized with TMETN. What would be your guess?
Anthony
Sent from my iPhone
On Aug 5, 2015, at 3:25 AM, George Herbert <george.herbert@xxxxxxxxx> wrote:
Is the HNF propellant 1.1 or just the bulk HNF chemical?
Thanks...
George William Herbert
Sent from my iPhone
On Aug 4, 2015, at 3:12 PM, "Anthony Cesaroni" <acesaroni@xxxxxxxxxxx> wrote:
Yup. HNF propellant below. 270 seconds, sea level delivered. No metal, smoke
or flame. Minor problem, $14K/lb. among other things. Add metal and it
really screams.
<image002.jpg>
Anthony J. Cesaroni
President/CEO
Cesaroni Technology/Cesaroni Aerospace
http://www.cesaronitech.com/
(941) 360-3100 x101 Sarasota
(905) 887-2370 x222 Toronto
-----Original Message-----
From: arocket-bounce@xxxxxxxxxxxxx [mailto:arocket-bounce@xxxxxxxxxxxxx] On
Behalf Of Monroe L. King Jr.
Sent: Tuesday, August 04, 2015 6:04 PM
To: arocket@xxxxxxxxxxxxx
Subject: [AR] Re: Peltier specifications
Anthony have you done any work with HNF? Being it's so hard to get right? If
you are I want a job at CTI. lol
-------- Original Message --------
Subject: [AR] Re: Peltier specifications
From: "Anthony Cesaroni" <acesaroni@xxxxxxxxxxx>
Date: Tue, August 04, 2015 2:54 pm
To: <arocket@xxxxxxxxxxxxx>
The Russians have (had) at least one notable ram rocket engine that
used the approach. It helps overcome some aluminum combustion issues
but doesn t completely solve them like HNF does. Clever those
Russians are. :-)
Best.
Anthony J. Cesaroni
President/CEO
Cesaroni Technology/Cesaroni Aerospace http://www.cesaronitech.com/
(941) 360-3100 x101 Sarasota
(905) 887-2370 x222 Toronto
-----Original Message-----
From: arocket-bounce@xxxxxxxxxxxxx [mailto:arocket-bounce@xxxxxxxxxxxxx]
On Behalf Of Monroe L. King Jr.
Sent: Tuesday, August 04, 2015 5:38 PM
To: arocket@xxxxxxxxxxxxx
Subject: [AR] Re: Peltier specifications
Hummm now that is interesting Anthony. Hummmmmm and thanks!
-------- Original Message --------
Subject: [AR] Re: Peltier specifications
From: "Anthony Cesaroni" <acesaroni@xxxxxxxxxxx>
Date: Tue, August 04, 2015 2:31 pm
To: <arocket@xxxxxxxxxxxxx>
Been there done that. It makes your rocket smell like your grandmother's
cedar chest and sublimates causing other issues as well. Having said
that, if you press it with low micron or nano aluminum, it makes for an
interesting fuel grain with interesting ballistic characteristics.
.
Particularly in an ?all solid? hybrid.
Anthony J. Cesaroni
President/CEO
Cesaroni Technology/Cesaroni Aerospace
http://www.cesaronitech.com/
(941) 360-3100 x101 Sarasota
(905) 887-2370 x222 Toronto
-----Original Message-----
From: arocket-bounce@xxxxxxxxxxxxx [mailto:arocket-bounce@xxxxxxxxxxxxx]
On Behalf Of Monroe L. King Jr.
Sent: Tuesday, August 04, 2015 5:18 PM
To: arocket@xxxxxxxxxxxxx
Subject: [AR] Re: Peltier specifications
I wonder if Naphthalene would make a good additive to HTPB hybrid
propellant? It's a white powder (used mostly in mothballs) it sublimates
quite easily. It's a hydrocarbon, perhaps it would help stabilize hybrid
combustion?
I know adding AP to the HTPB helps combustion say 5%.
-------- Original Message --------
Subject: [AR] Re: Peltier specifications
From: Bill Claybaugh < <mailto:wclaybaugh2@xxxxxxxxxx>
wclaybaugh2@xxxxxxxxxx>
Date: Tue, August 04, 2015 2:04 pm
To: " <mailto:arocket@xxxxxxxxxxxxx> arocket@xxxxxxxxxxxxx" <
<mailto:arocket@xxxxxxxxxxxxx> arocket@xxxxxxxxxxxxx>
Not really a preburner and not really adding any complexity; the TEA
system was needed for ignition, increasing the size of that tank was
all that was required to eliminate most combustion instability.
I can't speak to other technical solutions; but note that it does not
require all that much heat to vaporize a Lox fog.
Bill
Sent from my Commodore 64
On Aug 4, 2015, at 3:54 PM, Henry Vanderbilt <
<mailto:hvanderbilt@xxxxxxxxxxxxxx> hvanderbilt@xxxxxxxxxxxxxx>
wrote:
Interesting. So if I'm understanding this correctly, you're talking
about something like an oxygen-rich preburner to make sure the
oxidizer is thoroughly vaporized as being useful for large hybrids.
Makes sense of what VG might be having methane onboard SS2 for. I'd
been wondering about that.
It sounds like the sort of thing one would come up with after
already committing to large hybrids, then hitting the (apparently
fairly typical) uneven combustion, to make them actually work. If
you assume from the start you'll need some sort of preburner with a
separate fuel system, I'd think large hybrids would lose their
lower-parts-count edge over biprops in the tradeoffs.
On 8/4/2015 11:37 AM, Bill Claybaugh wrote:
Mark:
It seems like an AN & ice water mix could be tailored to your
temperature goals. But why not go to a dry ice cooler and maximum
density: a single pass on a couple of coils should get you what you
are seeking. LN2 is also obviously an answer; both can be had in
Mojave.
As Anthony has hinted, you will need a heat source at the head end
to assure the N2O fog is vaporized, otherwise combustion will be
rough and unstable. At Amroc we injected TEA throughout the burn
to vaporize the Lox; I gather VG is using Methane in the SS2 nylon
motor.
Bill
Sent from my Commodore 64
On Aug 3, 2015, at 9:33 PM, Mark C Spiegl <
<mailto:mark.spiegl@xxxxxxxxx> mark.spiegl@xxxxxxxxx> wrote:
Wow... Im out of the office for a day and my inbox is full!
:-)
Anyway.. Anyone who has followed my hybrid projects knows Im a fan
of high density Nitrous. Im looking to cool 20-50 lbs of Nitrous
to 25-ish degF.
Goals:
(1) Flashing liquid to vapor to chill Nitrous is fine in a motor
burning 10-20 lbs of Nitrous. Much above 20lbs (esp in the
desert), flashing liquid to gas becomes impractical. I would like
to start a little closer to my target temperature of 22 degF. The
Peltier, Stirling Cooler, or whatever would chill the supply tank,
not the rocket tank.
I know ice is a quick-and-dirty answer, but I would like something
a little more elegant and deterministic. Bags of ice aren't a
great answer at FAR or Blackrock.
(2) I have had trouble igniting high density Nitrous in warm
weather. Cold weather is no problem. I cannot prove what is
happening, but I suspect temperature gradients in the long thin
Nitrous tank are causing the problem. If the Nitrous is 22 degF at
the top of the tank, it may be much much colder at the injector.
Supplying Nitrous close to the final temperature should help
mitigate this problem, if Im correct.
A related question: Any simple ways to equalize temperature
between the top and bottom of the rocket's oxidizer tank???
--MCS
(Im an EE kind of person so my solutions tend to feel like
electronics... ie Peltiers)