1. P07109: Project M.E.T.E.O.R. Flying Rocket Team Andrew ScarlataProject Leader/ Mechanical Engineer Geoff CassellLead Engineer/ Mechanical Engineer David HallLead Engineer/ Mechanical Engineer Luke CadinMechanical Engineer Zack MottMechanical Engineer Garett PickettElectrical Engineer Brian WhitbeckMechanical Engineer Sponsor: Dr. Dorin Patru Electrical Engineering department Advisor: Dr. Jeffrey Kozak Generous donation from Harris RF Corporation

2. Project Description Part of the M.E.T.E.O.R. family Launching small payloads into low-Earth orbit Continuation of P06006: Hybrid Rocket Engine Design and Testing Working in conjunction with P07105 & P07106 Research, develop, and manufacture a flight ready hybrid rocket stage Primary Customer Need: Achieve a structure to propellant ratio of 1:10 – 2:10. Other design specifications to consider Maintain structural integrity Accommodation of other systems Manufacturing feasibility Improvements on ignition system

3. Current Design HTPB Fuel Grain Nitrous Oxide Tank (inside) Pre Combustion Chamber Post-Combustion Chamber Graphite Nozzle Electronics Payload Polymer Matrix Composite Outer Shell Micro Inertial Measurement Unit Servo Actuated Cold Jet Array Honeycomb Structure/ Composite Sandwich End Cap

4. Special Concerns Given the cooperative nature of the project, physical data is still needed to make any final design decisions Testing is scheduled for the first week of Senior Design II Analysis of more complicated systems is out of the range of expertise for team members Combustion gas behavior

5. Current State of Design Accurate theoretical models have been made and await technical data from testing results Finite Element Analysis Thermal Modeling Material selection is underway Outer body materials Composite tank selection Pre and post combustion chamber alternatives Ignition system has been optimized and preliminary construction has begun

6. Mass Budget Imported Items: Electronics/Guidance System: 1kg Pre & Post Combustion Chambers: 0.15kg each Injector Plate: 0.31kg Exit Nozzle: 0.71kg Subtotal: 2.32kg Structural Items: Pressure Vessel: 0.64kg Titanium Shell: 0.56kg Composite Body: 0.85kg Subtotal: 2.05kg Total:4.37kg Limit: 2kg

7. Flying Rocket Ignition System Darlington Configuration of Transistors R3 Igniter load (Nichrome Wire) V2 = PWM from MSP430 F1-69

8. MSD II Schedule Week 1: Testing and data acquisition Week 2:Design detail and finalization Weeks 3-5: Material selection and ordering Weeks 6-8: Manufacture Week 9: Testing Week 10:Finalized documentation and Project Review

9. Questions? Thank You