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P07109: Project M.E.T.E.O.R.
Flying Rocket Team
Andrew Scarlata
Geoff Cassell
David Hall
Luke Cadin
Zack Mott
Garett Pickett
Brian Whitbeck
Project Leader/ Mechanical Engineer
Lead Engineer/ Mechanical Engineer
Lead Engineer/ Mechanical Engineer
Mechanical Engineer
Mechanical Engineer
Electrical Engineer
Mechanical Engineer
Sponsor: Dr. Dorin Patru
Electrical Engineering department
Advisor: Dr. Jeffrey Kozak
Generous donation from Harris RF Corporation
Project Description
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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
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Maintain structural integrity
Accommodation of other systems
Manufacturing feasibility
Improvements on ignition system
Current Design
Honeycomb Structure/
Composite Sandwich End Cap
Payload
Servo Actuated Cold Jet Array
Electronics
Polymer Matrix
Composite Outer Shell
Micro Inertial Measurement Unit
Nitrous Oxide Tank (inside)
Pre Combustion Chamber
Post-Combustion Chamber
HTPB Fuel Grain
Graphite Nozzle
Special Concerns
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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
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Combustion gas behavior
Current State of Design
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Accurate theoretical models have been made and
await technical data from testing results
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Material selection is underway
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Finite Element Analysis
Thermal Modeling
Outer body materials
Composite tank selection
Pre and post combustion chamber alternatives
Ignition system has been optimized and preliminary
construction has begun
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
Flying Rocket Ignition System
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Darlington Configuration of Transistors
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R3 Igniter load (Nichrome Wire)
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V2 = PWM from MSP430 F1-69
MSD II Schedule
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Week 1:
Week 2:
Weeks 3-5:
Weeks 6-8:
Week 9:
Week 10:
Testing and data acquisition
Design detail and finalization
Material selection and ordering
Manufacture
Testing
Finalized documentation and
Project Review
Questions?
Thank You