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PANTHR Team Members

PANTHR Team Members. Glen Guzik Niroshen Divitotawela Michael Harris Bruce Helming David Moschetti Danielle Pepe Jacob Teufert. Primary Project Objectives. Build hybrid rocket motor - paraffin fuel (C n H m ; n~25, m~50) - nitrous oxide oxidizer (N 2 O) Conduct static test fire

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PANTHR Team Members

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  1. PANTHR Team Members Glen Guzik Niroshen Divitotawela Michael Harris Bruce Helming David Moschetti Danielle Pepe Jacob Teufert

  2. Primary Project Objectives • Build hybrid rocket motor - paraffin fuel (CnHm; n~25, m~50) - nitrous oxide oxidizer (N2O) • Conduct static test fire • Complete fabrication of rocket • Launch rocket to an altitude of ~12,000 ft. • Collect various in-flight data- acceleration curve- flight trajectory- altitude at apogee- onboard flight video

  3. Current Division of Labor • Hybrid Motor Design- Niroshen Divitotawela- Michael Harris- Jacob Teufert • Aerodynamics and Flight Stability- Bruce Helming- Danielle Pepe • Payload and Recovery- Glen Guzik- Bruce Helming • Structural Analysis- David Moschetti • - Niroshen Divitotawela • Safety and Logistics-David Moschetti-Glen Guzik

  4. Paraffin And Nitrous Oxide Test Hybrid Rocket Advantages of Hybrid Rockets • Mechanically simple compared to Liquid Rockets • Safer and more controllable than Solid Rockets Advantages of Paraffin • High Regression Rate • Practical Single-Port Design • High Energy Density (~same as kerosene) • Inexpensive • Non-toxic Advantages of Nitrous Oxide • Available • Inexpensive • High Density • Self-Pressurizing

  5. Hybrid Motor Specifications • Maximum Thrust: 1500N • Burn Time: 2-4s • Specific Impulse: ~220s Design Analyses • Initial Thermodynamic Analysis: Completed • Chamber Pressure Analysis: In Progress • Throat Area Analysis: In Progress • Advanced Thermodynamic Analysis: Planned • Wall Heat Transfer Analysis: Planned

  6. Combustion Chamber: Thermodynamic Analysis Initial • Complete Combustion • Calorically Perfect • Adiabatic • Analysis Completed, Chamber Temperature: 3800K Advanced • Computational • Dissociation Effects • Heat Transfer • Incomplete Combustion

  7. Combustion Chamber:Chamber Pressure • Begin with Conservation Equation • Apply Regression Rate Formula • Apply Choked Flow • Assume Ideal Gas

  8. Nozzle:Exit Area & Thermodynamic Properties • Assume Choked, Isentropic Flow • Exit diameter set for manufacturing ease to 2.75”

  9. Oxidizer Fill and Ignition System • Fill internal oxidizer tank via external, commercial nitrous-oxide tank. • Light solid propellant ignition charge via electric match. • Oxidizer flow started by erosion of pressure diaphragm from ignition charge.

  10. Structural Analysis • Most severely stressed components are the Combustion Chamber and Oxidizer Tank • Wall Thickness was calculated using hoop stress equation With F.S. of 1.5:

  11. Structural Analysis: Trade Study • Several Alloys were compared in the decision process for the material of the tubing needed for the tank. • Al 6061-T6 was observed to be the best metal to use considering cost and strength.

  12. Planned Structural Analysis • Stress calculations to determine size and number of bolts for Combustion Chamber and Oxidizer Tank bulkheads • Stress calculations on aluminum sections due to g-loading • Testing on fiberglass airframe to determine maximum stress

  13. PayloadConsiderations • Video camera mounted inside of rocket will record the entire flight to solid state memory • Camera view oriented toward ground • Varying the diameter of the body tube would allow desired view angle but have a higher drag than a contoured wind screen • Resulting moments offset by fins

  14. Payload Considerations: Camera Alternatives • Resolution of 640x480 at 30 fps • Disposable CVS Camcorder $29.99 • Argus Digital Video $129.99 • VID 045 Color $170- Additional RCA A/D Converter Required

  15. Payload Considerations: Accelerometer • Vendor: http://www.vernier.com • Vernier LabPro ($220)- 6 Channel Data Acquisition- Modular Sensors • 3 Accelerometers 25g ($99) • Gas Pressure Sensor ($79)

  16. Stability • Maintain the Static Margin • Over damped • Under-damped http://www.rockets4schools.org/education/Rocket_Stability.pdf

  17. Stability • Subsonic flight allows use of Barrowman Method • Once total dimensions are finalized, cp and cg can be calculated

  18. Fin Design • 3 General design of fins • CFD computations will be performed on each fin • Flutter will be considered • CNC machined

  19. Types of Nose Cones 1) Elliptical 2) Conical 3) Parabolic http://myweb.cableone.net/cjcrowell/NCEQN2.DOC

  20. Recovery • Barometric Altimeter • Drogue Chute – Deploys at apogee using a timer • Main Chute – Deploys when altimeter detects specified altitude (~1500ft)

  21. Updated Budget

  22. Safety Plan Main Risks • High Pressure Systems • Chemicals/Flammables • Test Fire and Launch Procedures • Construction Mitigation Plan • Currently working with the University Safety Office on developing procedures for handling, construction, and launch of the rocket.

  23. Questions?

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