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University of Florida PDR Presentation

University of Florida PDR Presentation. Outline. Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work. Project Organization. Outline. Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work.

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University of Florida PDR Presentation

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  1. University of Florida PDR Presentation

  2. Outline • Project Organization • Vehicle Design • Payload Design • Recovery System • Simulations • Future Work

  3. Project Organization

  4. Outline • Project Organization • Vehicle Design • Payload Design • Recovery System • Simulations • Future Work

  5. Material and Dimensions • Material: Reinforced Phenolic • Diameter: 4 inches • Length: 96.75 inches • Weight: 22.55 lbs

  6. System Breakdown Avionics Bay Nosecone Main Parachute Flight Computer Drogue Parachute G10 Fins Main Piston Aileron Deflection Package Drogue Piston LFD Fins

  7. Stability Characteristics CG CP • The center of pressure (CP) is located 79.427" from the nose tip • The center of gravity (CG) is located 72.715" from the nose tip • Static Stability Margin of 1.68 increasing to 2.20 at motor burnout

  8. Vehicle Verification • Vehicle verification focused on safe recovery and reliable platform for LFD payload • Testing will be done to allow triple redundancy for drogue and main separation events • Accurate Stress analysis for all components

  9. Outline • Project Organization • Vehicle Design • Payload Design • Recovery System • Simulations • Future Work

  10. Lateral Flight Dynamics Payload • Study of Lateral Dynamics of Rocket during flight • Attempts to quantify natural roll dampening of rocket • Compares natural roll dampening to dampening due to AIM 9M passive stabilization system • Determine resulting couple moment due to unlocked rollerons • Consists of LFD Fin, ADP, and Electronics

  11. LFD Fins Rolleron Trim Potentiometer PC Fin Halves Linear Actuator ¼” Barrel Bolts G10 Mount • G10 Mount epoxied to motor tube • 2 fin halves bolted to permanent mount • Linear Actuator and Rolleron integrated separately

  12. Aileron Deflection Package Aileron Torsional Springs Bevel Gears Servo Motor Gearbox

  13. Electronics • Raspberry Pi • Controls servo motor for ADP • Commands unlocking of Rollerons • Collects flight dynamics data from gyros and trim potentiometers

  14. Payload Verification • Ensure Launch Vehicle will be stable with integrated Payload. • Reliability of all systems allows for quality data acquisition.

  15. Outline • Project Organization • Vehicle Design • Payload Design • Recovery System • Simulations • Future Work

  16. Recovery • All payload systems remain with launch vehicle • Drogue parachute released at apogee • Wires unplug from LFD fins using umbilical connection • Main parachute released at 700 ft AGL

  17. Vehicle Recovery • Drogue parachute 24 inches in diameter (x-form) • Descent velocity: 65 ft/s • Main parachute 96 inches in diameter (circular) • Descent velocity: 17 ft/s Kinetic Energy at Landing

  18. Recovery System Integration • Drogue parachute housed in lower airframe, below electronics bay • First separation event utilizes piston ejection and drag generated by fins for reliable separation • Main parachute housed in upper airframe, above electronics bay • Second separation event utilizes piston ejection • Shear pins prevent premature separation of nosecone and of lower airframe

  19. Recovery Redundancy • Dual PerfectFliteStratoLogger altimeters • Two-way communication via Raspberry Pi allows use of manual charge detonation system. • System will be tested thoroughly before put into use. • Ground/Software Testing • Flight Testing

  20. Outline • Project Organization • Vehicle Design • Payload Design • Recovery System • Simulations • Future Work

  21. Flight Simulations • OpenRocket and MATLAB used to simulate the rocket’s flight • MATLAB code is 1-DOF that uses ode45 • Allows the user to vary coefficient of drag for different parts of the rocket • Wind tunnel testing and full-scale demonstration will allow more accurate Cd values

  22. Preliminary Results • MATLAB code is compared with OpenRocket • Maximum altitude approximately 190 ft. lower than OpenRocket but still near target • High target altitude to account for drag due to LFD Payload

  23. Motor Choice • Cesaroni L1720 • Max Thrust 394 lb • Impulse 831 lb-s • Powerful motor allows altitude to be met with increased drag due to LFD Payload. • Gives a thrust to weight ratio of 13.1

  24. Outline • Project Organization • Vehicle Design • Payload Design • Recovery System • Simulations • Future Work

  25. Future Work • Refine designs and tolerance all components • Successfully fulfill subscale flight requirements while testing flight software • Begin manufacturing of rollerons, LFD fins, and ADP • Continue community outreach and educational engagement functions • Name Rocket

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