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Critical Design Review 02/02/ 2012 Project Phoenix 2011-2012 The Pennsylvania State University

Critical Design Review 02/02/ 2012 Project Phoenix 2011-2012 The Pennsylvania State University. Presenters. Russell Moore – Project Manager Brian Taylor – Systems Engineer Matt Hanna – Structures & Aerodynamics Lead Tony Maurer – Structures & Aerodynamics Lead

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Critical Design Review 02/02/ 2012 Project Phoenix 2011-2012 The Pennsylvania State University

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  1. Critical Design Review 02/02/ 2012 Project Phoenix 2011-2012 The Pennsylvania State University

  2. Presenters • Russell Moore – Project Manager • Brian Taylor – Systems Engineer • Matt Hanna – Structures & Aerodynamics Lead • Tony Maurer – Structures & Aerodynamics Lead • Heather Dawe – Propulsion Lead • Rob Algazi – Propulsion Lead • Adam Covino– Payload Lead • Brian Lani – Payload Lead • Eric Gilligan – Avionics & Recovery Lead • Lawrence Digirolamo – Avionics & Recovery Lead • Tom Letarte – Safety Officer

  3. Discussion Topics • Overview • Structures & Aerodynamics • Avionics & Recovery • Propulsion • Payload • Safety and Quality Assurance • Outreach • Conclusion

  4. Overview (Project/Vehicle) • Rocket is 92.2” in length, 4.5” in diameter (OD)- 4.375” (ID)- and weighs 29 lbs. • Uses machined fin brackets, motor retainer and tail cone. • Recovery System is Single Ejection (CO2)/Dual Deployment

  5. Fin Bracket • Allows for easy replacement of damaged fins • Allows experimentation of fin design (to alter the CP and therefore Static Stability) • CNC machined aluminum • No epoxy or other permanent bond • Screws into fin and through body tube

  6. Motor Retainer • Machined Aluminum forward motor retainer • Attaches to motor casing • Screwed into airframe • No epoxy or other permanent bonds • Acts as an Av bay aft bulk plate

  7. Tail Cone • CNC machined aluminum aft motor retainer • Reduces drag up to 50% for subsonic flight [1] • Threads onto aft of booster section • No epoxy or other permanent bonds • Opens up more room in airframe

  8. Structures • Rocket Flight Static Stability • 1.4 • Current Simulated Mass: 29.3 pounds • Mass Margin: 2.6 pounds • Predicted Drift

  9. Propulsion • Motor choice: AMW L777 • Thrust-to-weight ratio: 5.96 (average) • Rail exit velocity: 55.25 ft/s

  10. Propulsion Full Scale Motor: Animal Works L777 (75mm) • Determined By Open Rocket Models

  11. Propulsion Sub-Scale Motor: Aerotech J315 (54mm) • Determined By Open Rocket Models

  12. Propulsion Full Scale Contingency Motor: Cesaroni L935

  13. Propulsion Full Scale Contingency Motor: Cesaroni L935

  14. Avionics & Recovery • Main Parachute: Fruity Chutes 84” Iris Ultra • Drogue Parachute: Rocketman 3’ Ballistic Mach II Chute • Recovery Harness: 50’ of ½” tubular Kevlar • Altimeters: 2x PerfectFliteStratoLogger • Down-body Camera: PD80 • Recovery Aids: • Garmin Astro DC-20 GPS System • BeepX Sonic Beacon

  15. Avionics & Recovery Sled and Bay Design BeepX Sonic Beacon Altimeters 9V Battery Holders Switches BP Ejection Canister BeepX 12V 23A Battery CD3 Ejection System CO2 Canister Note: Aft Bulkhead is actually an aluminum bulkhead that interfaces with the motor casing and screws into the airframe

  16. Avionics & Recovery • Apogee • CD3 CO2 ejection device • Black powder ejection charge • Drogue is released and main is held within the airframe by the main parachute containment harness. • 750 ft AGL • Tender Descender releases the main and the drogue pulls it out of the airframe and deployment bag

  17. Avionics & Recovery • Descent Rate • 64 ft/s under drogue • 15 ft/s under main • Kinetic Energy • Booster Section: 73.8 ft-lbs • Nosecone/Payload: 15.6 ft-lbs

  18. Avionics & Recovery • Altimeter test • Tested functionality of altimeters and ability to fire e-matches • CD3 independent test • Tested stand-alone functionality of CD3 system • Sub-scale ground test • Tested the ability of the CD3 system to eject the nosecone

  19. Payload NASA SMD Mission Payload: • Measure atmospheric parameters • Will collect following data: • Pressure • Temperature • Relative Humidity • Solar Irradiance • Ultra-violet Radiation

  20. 900MHz Transmitter Payload HASB HASB Arduino Control Arduino Control Power Supply Power Supply Light Sensor Light Sensor Data Logger Data Logger

  21. Payload

  22. Payload Scientific Value: • Analyze collected information to profile atmospheric boundary layer • Determine stability and depth of atmospheric boundary layer • Construct a Skew-T diagram of the boundary layer as visual aid to determine weather severity [www.met.psu.edu]

  23. Safety & Quality Assurance • CO2 Canisters for CD3 System • Manufactured to UL1191 Standard • Burst pressure: 7000psi • 75% Fill • 30 min @ 100 ⁰C, 15min @ 150 ⁰C Pressure vs %Fill for varying Temperature

  24. Safety & Quality Assurance

  25. Upcoming Milestones • Verification Testing as in explained in Appendix D: Test Matrix (February) • MDRA Launch (March 10-11) • METRA Launch (March 24) • FRR (March 26)

  26. Educational Engagement • Discovery Space Museum Workshops • January 27, February 8 & 22, March 21 • Spikes Fest • February 12 • Park Forest Middle School STEM Fair • March 14

  27. Expenses Full Scale Rocket Expenses by Subsystem Overall Club Expenses

  28. Conclusion • Tests show that rocket is structurally sound and ejection/internal circuitry works. • Further testing for drogue parachute size, landing radius distance, and motor performance.

  29. References [1] Fleeman, l.E., Tactical Missile Design – Second Edition, American Institute of Aeronautics and Astronautics, Inc., VA 2006 [2] www.fruitychutes.com [3] www.apogeerockets.com [4] www.met.psu.edu [5] www.wildmanrocketry.com [6] www.pro38.com [7] www.giantleaprocketry.com [8] www.eurorocketry.org

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