USLI Flight Readiness Review. Harding University Flying Bison 2010 USLI Rocket Team. Harding Flying Bison Team. Team made up of 16 members with diverse educational backgrounds: Greg Libby Elizabeth Hunter Matt G. April Josh Lisa Darah Chi Patrick Matt I. Meredith Cortney Shailer
Harding University Flying Bison 2010 USLI Rocket Team
Team made up of 16 members with diverse educational backgrounds:
Greg Libby Elizabeth
Hunter Matt G. April
Josh Lisa Darah
Chi Patrick Matt I.
Meredith Cortney Shailer
Airframe Greg, Mgr.
Motor Matt G., Mgr.
Science Payload Darah, Mgr.
Avionics Chi, Mgr.
Launch Operations Matt I., Mgr
Recovery Patrick, Mgr.
Outreach Elizabeth, Mgr.
Team Official & Safety Officer Ed
Project Progress Cortney
Length 93.55 inches 7.5 feet
Diameter 4.09 inches
Span Diameter 14.09 inches
Estimated Mass 241.39 ounces15.03 pounds
Center of Pressure 72.22 in
Center of Gravity 55.0 1in
Margin of Stability4.30 body calibers over stable
We were not able to do a scale model test as planned because some key supplies were missing.
We found out in the process that our ignition system has become defective.
We are purchasing a new unit.
We plan our full scale test on 21 March 2010.
Average Thrust = 896 N
Mass 241.39 g + 4173 g = 4.414 kg
Weight = 43.31 kg
Thrust to weight ratio = 20.7
Launch guide length: 94.0000 In.
Velocity at launch guide departure: 77.2523 ft/s
The launch guide was cleared at : 0.203 Seconds
User specified minimum velocity for stable flight: 43.9993 ft/s
Minimum velocity for stable flight reached at: 31.0498 In.
Tensile strength tests run for:
Shock cord – 3/8 in. Kevlar
U-Bolts – ¼ in diameter
Knots – Bowline
Tests stopped after Kevlar cord began to fray at 961 lbf at the knot
The Kevlar shock cord would not have separated until more force applied
Full scale flight test - planned for 21 March 2010
Dual deployment avionics test test - planned for 21 March 2010
Ejection charge amount test test - planned for 21 March 2010
Payload integration feasibility – Payload is fully integrated into the rocket
Payload success will be achieved if all the sensors perform satisfactorily and data from each is collected and stored in the on-board computer memory.
Side profile of science payload with circuit boards and batteries mounted
Contrail Rockets Certified K-888-BM Hybrid Motor
Diameter of motor 75 mm
Length of Motor 40.0 inches
Fuel Grain Used Black Smokey
Exit end of nitrous tank showing fill and overfill lines
Ignition -- Pyrodex Pellets Ignited with Resistors
Tripoli Rocketry Association, Inc., Certification
The recovery subsystem is composed of the following components:
PerfectFlite MiniAlt/WD Official USLI Altimeter and Flight Computer
G-WIZ MC-2 Backup Altimeter and Flight Computer
We gratefully acknowledge support from
NASA/Arkansas Space Grant Consortium
A part of the National Space Grant Program