2.  Expand upon knowledge base developed from Panther 1 solid rocket launch (6/28/06)  Enhance relationship and training opportunities between Florida Tech, Space Florida, Air Force, and other Universities  Launch first hybrid rocket from Cape Canaveral Air Force Station (CCAFS) 2

3.  Develop a hybrid rocket compliant with Air Force safety directives  Launch from CCAFS  Obtain hybrid rocket trajectory data for NASA’s Universal Controls Analysis Tool (UCAT) program 3

4.  Develop a safe hybrid propulsion system  Test fire propulsion system utilizing 6-DOF Motor Thrust Stand  Build or modify a 6-DOF Inertial Measurement Unit (IMU)  Develop an approved recovery system  Launch to an agreed upon altitude and flight trajectory  Expand roadmap and lessons learned incorporating procedures needed to launch hybrids from CCAFS 4

5.  Demonstrate complete compliance with 45 th Space Wing safety requirements to launch at CCAFS  Develop and submit Safety Plan to University Safety Office (USO)  Test fire the propellant using the test stand to gain an accurate model for launch

6. 6  Rocket design is tentative and dimensions are not set. Driving factors include:

7. OxidizersAdvantagesDisadvantages Nitrous Oxide (N 2 O) Widely available, inexpensive, non-toxic, self- pressurizing Less efficient that other oxidizers Liquid Oxygen (O 2 ) Very efficient oxidizer, can be self- pressurizing, non-caustic Difficult support structure, exotic insulation required Hydrogen Peroxide (H 2 O 2 ) Efficient oxidizer, ignites on contact with many fuels Caustic, difficult to obtain required concentrations 7  3 oxidizers and fuels considered during the design phase  Nitrous Oxide and HTPB were selected for their ease of manufacture and safety properties FuelsAdvantagesDisadvantages Hydroxy- Terminated Polybutadiene (HTPB) Available as resin, relatively high regression rate Thermal decomposition causes difficulties with combustion modeling High-Density Polyethylene (HDPE) Easily machined and obtained Low regression rate PolystyreneEasily machined, inexpensive Potentially more brittle than HDPE, research is currently underway

8. 8 PHASE 1: First test fireDescriptionAmount Motor All parts needed to construct motor used for static test firings$357.17 Fuel Materials for building fuel grains$217.00 Ground Support Equipment Equipment needed to support launch$470.18 TOTAL $1044.35

9. 9 Pro E Model of the Motor Testing Apparatus

10. 10 Apparatus to test the propulsion system on the 6 Degree of Freedom Thrust Stand

11. 11  Used to mold the HTPB resin into correct shape

12. 12  Nozzle was created from solid block of granite  Extra Safety Precautions were taken when lathing the material

13. 13  Created from aluminum  Separates oxidizer tank from combustion chamber

14. Fall: Conduct multiple static test fires Continue discussion with 45 SW Finalize motor specifications Finalize payload design Design recovery system Spring: Conduct live test fire(?) Finalize talks with 45 SW Assemble final rocket Launch Publish results…obtain glory 14