Menu:

News:

Jun 14, 2014:
Graduated UW with BSAAE degree!


SARP 2014

Results

On June 26, 2014, the Society for Advanced Rocket Propulsion (SARP) rocket team launched its high-power rocket at the 9th Annual Intercollegiate Rocket Engineering Competition (IREC) hosted by Experimental Sounding Rocket Association (ESRA). The high power HTPB/N2O hybrid rocket reached an altitude of 7000 feet at a velocity of 1100 ft/sec and was on track to reach the desired 25,000 foot elevation before the thrust chamber burned through and structurally failed. All components of the rocket were recovered.  The team received the Jim Furfaro Award for Technical Excellence.

Propellant

I had a number of duties over the course of the year as we designed our rocket. One of the first tasks that the Propulsion team needed to finish was to determine the propellant composition.  We decided on a HTPB/Paraffin Wax/Aluminum Powder fuel with Nitrous Oxide (N2O) oxidizer. To determine the best ratio of HTPB to Paraffin, numerous small-scale fuel grains were made with different amount of each, and then tested in a subscale motor.

To create the fuel grains, the fuel mixture was mixed and then poured into a phenolic liner and placed on a lathe to cool/harden.  Carbon powder was added to the mixture to reduce thermal transport during the burn and minimize the risk of sloughing.


SARP_rocketfuel.jpg SARP_fuelgrain.jpgSARP_fuelbore.jpb

Instrumentation

Two sensors were utilized for the hydrostatic testing: a pressure transducer and a force sensor. I assisted in choosing an NI DAQ to use and helped set up the LabView VI for data collection.
SARP_so_many_daqs.jpg

Testing

We started the testing process using a subscale thrust stand. The goal was to determine the thrust and pressure produced by each fuel composition, and also determine the regression rate of each fuel so that the performance of the full-scale motor could be predicted. The subscale motor produced around 100 lbf of thrust.
SARP_subscale.jpg
Once a fuel composition was decided upon, testing progressed to full-scale burns. The full scale motor produced roughly 1000 lbf of thrust during testing, as predicted.
SARP_fullscale

Lessons Learned

I learned a lot about using instrumentation and sensors, how hybrid rockets work, and that I really enjoy running hardware tests. In addition, I gained more experience with working with a team, and how to enjoy an experience even in the midst of failure.