On using burst disks for engine start, it is not as simple as it first
appears. I have not been able to find commercial burst disks in the sizes
that would work for small thrust applications. I looked into using a thin
sheet of metal and found that the theoretical size that you would need to
use would be about the thickness of a sheet of aluminum foil. In addition,
how do you ensure that disk does not break free entirely and not get caught
up and block your filter. Another complexity is that a cryogenic
temperatures there will be thermal stresses in the burst disk and this
could easily cause it to break in loading operations. I am not saying that
it is impossible, however we have found that it is probably simpler and
more reliable to use a ball valve with a high torque continuous servo.
Zachary Martinez
Aerospace & Mechanical Engineering
Missouri S&T
On Tue, Mar 21, 2017 at 3:18 PM, Paul Mueller <paul.mueller.iii@xxxxxxxxx>
wrote:
Very cool! Amazing job! I do wonder what the significance is of the "+ON"
that the TVC spelled out on the concrete pad (video #2)...secret message? ;)
The solid flame looked surprisingly clear and pinkish (at least in the
video)...can you divulge the propellants? Just curious
On Tue, Mar 21, 2017 at 12:14 PM, Team Icarus SDSU <
rocketteamicarus@xxxxxxxxx> wrote:
Thank you to Robert and Anthony for more information on the staged
combustion hybrids. I can certainly attest to the reload simplicity on the
CTI HPR motors. Dead simple.
And thanks to Carl for the mention on our successful solid motor test.
The motor test had a lot of firsts for us and I will post more
footage/details on the list later today.
I am interested to learn more about staged combustion hybrids; it seems
to me that under the right circumstances this technology could use burst
disks and pyrotechnic igniters instead of cryo valves for motor startup,
which could reduce mechanical complexity at the sounding rocket scale.
Carl, could the gas from a solid propellant gas generator feasibly be
used to run a flometrics style pistonless pump instead of helium and a
liquid fuel gas generator?
Alex Lewis
Carl: can a solid propellant gas generator
On Mar 21, 2017 9:54 AM, "Carl Tedesco" <ctedesco@xxxxxxxxxxxxxx> wrote:
A good weekend for university rocketry...
This weekend the SDSU Rocket Project tested two rocket motors. The
LR-101, a 1000 lb. thrust LOX/RP-2 liquid propellant motor, and the Icarus
solid propellant motor, ~1400 lbs, of thrust. Attached are some images and
below are some links to videos.
Drone footage: Liquid propellant static test
<https://www.youtube.com/watch?v=igpL7yQ8asg&t=102s>
Close-up: Thrust Vector Control Cam
<https://www.youtube.com/watch?v=cpRF31sWdHQ>
Drone Footage: Solid rocket motor static test
<https://www.youtube.com/watch?time_continue=26&v=k-gIW7FdsCU>
My Favorite video: Student’s Reaction
<https://www.youtube.com/watch?v=6fplIw3_-6Q> (Ben’s video)
Some of the students lurk on this list, so let’s see if they’re brave
enough to give some details on their projects. We have submitted our
request to the FAA to fly to 45,000’ in April. We hope we hear back from
them soon.
