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)

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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

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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

Demonstrate complete compliance with 45th 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

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

Oxidizers Advantages Disadvantages

Nitrous Oxide(N2O)

Widely available, inexpensive, non-toxic, self-pressurizing

Less efficient that other oxidizers

Liquid Oxygen(O2)

Very efficient oxidizer, can be self-pressurizing, non-caustic

Difficult support structure, exotic insulation required

Hydrogen Peroxide (H2O2)

Efficient oxidizer, ignites on contact with many fuels

Caustic, difficult to obtain required concentrations

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3 oxidizers and fuels considered during the design phase Nitrous Oxide and HTPB were selected for their ease of

manufacture and safety properties

Fuels Advantages Disadvantages

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

Polystyrene Easily machined, inexpensive

Potentially more brittle than HDPE, research is currently underway

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PHASE 1: First test fire Description Amount

Motor

All parts needed to construct motor used for static test firings $357.17

FuelMaterials for building fuel grains $217.00

Ground Support EquipmentEquipment needed to support launch $470.18

TOTAL $1044.35

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Pro E Model of the Motor Testing Apparatus

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

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Used to mold the HTPB resin into correct shape

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Nozzle was created from solid block of granite

Extra Safety Precautions were taken when lathing the material

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Created from aluminum Separates oxidizer tank from combustion

chamber

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