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University of Florida IntimiGATOR FRR

University of Florida IntimiGATOR FRR. Outline. Overview System Design Recovery Design Payload Design Simulations and Performance Testing . Project Summary . Launch Vehicle The launch vehicle is designed to reach an altitude of a mile It contains 3 separate payloads:

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University of Florida IntimiGATOR FRR

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  1. University of Florida IntimiGATORFRR

  2. Outline • Overview • System Design • Recovery Design • Payload Design • Simulations and Performance • Testing

  3. Project Summary • Launch Vehicle • The launch vehicle is designed to reach an altitude of a mile • It contains 3 separate payloads: • The Science Mission Directorate payload measures atmospheric conditions and allows the calculation of lapse rate • The Lateral Flight Dynamics payload collects data on the vehicle’s roll rate for analysis • The Flow Angularity and Boundary Layer Development payload aids the team in knowing the vehicle orientation • There is dual-deployment recovery, with separate drogue and main parachutes for the SMD payload lander and launch vehicle

  4. Outline • Overview • System Design • Recovery Design • Payload Design • Simulations and Performance • Testing

  5. System

  6. Vehicle Dimensions • Diameter: 6 inches • Length: 115 inches • Weight: 30 lbs

  7. Static Stability Margin CG = 74.2” CP = 91.1” The static stability margin is 2.78

  8. Fins Dimensions: Fins and mount made from ABS plastic on a rapid prototype machine

  9. Motor Selection • Cessaroni L1720 WT • 1755 grams of propellant • Total impulse of 3660 N-s • 2.0 second burn time • Altitude of 5280 feet • 2.2 pound margin for error

  10. Outline • Overview • System Design • Recovery Design • Payload Design • Simulations and Performance • Testing

  11. Vehicle Recovery • Dual Deployment • Drogue release at apogee • Main release at 700 ft AGL • Drogue Parachute • 36 inches in diameter • Descent velocity of 65 ft/s • Main parachute • 96 inches in diameter • Descent velocity 18 ft/s • Recovery harness • 5/8” nylon • 25ft nosecone-upper • 35ft lower-upper

  12. Vehicle Recovery Systems • Drogue parachute • Directly below nosecone • Released during first separation event • Main parachute • Housed in middle airframe between avionics bay and pneumatics bay • Released during second separation event • Separation between pneumatics bay and middle airframe

  13. SMD Payload Recovery • Dual Deployment • Drogue release at apogee • Main release at 700 ft AGL • Drogue Parachute • 36 inches in diameter • Descent rate of 25 ft/s • Main Parachute • 36 inches in diameter • Descent rate of 12.5 ft/s • Recovery harness • 3/8” nylon • 10-15 ft

  14. SMD Payload Recovery Systems • Drogue parachute • Released during first separation event • Housed directly below vehicle drogue parachute • Main parachute • Released from parachute housing during secondary payload separation event • stored in housing and ejected using a piston system

  15. Kinetic Energy at Key Points Launch Vehicle and SMD Payload

  16. Outline • Overview • System Design • Recovery Design • Payload Design • Simulations and Performance • Testing

  17. Science Mission Directorate Payload – Objectives and Requirements • Objective • To calculate the environmental lapse rate • Requirements • Measure temperature, pressure, relative humidity, solar irradiance, and UV radiation as a function of altitude • GPS readings and sky-up oriented photographs • Wireless data transmission

  18. Science Mission Directorate Payload • Rests in the upper airframe on top of a piston • Ejects from the rocket at apogee • Dual deployment recovery

  19. Science Mission Directorate Payload • Payload legs spring open upon ejection • Some atmospheric sensors mounted on the lid • Body made of blue tube for data transmission purposes

  20. Science Mission Directorate Payload Design • Arduino Microcontroller • Samples analog sensors and reads outputs from Weatherboard and GPS • Weatherboard • Senses atmospheric data and transmits to the microcontroller using synchronous communication • Analog sensors • Compared to the pre-programmed output from the Weatherboard • XBee Pro 900 • Sends data back to ground station • Camera • Takes sky-up oriented video

  21. Lateral Flight Dynamics (LFD) • Objectives • Introduce a determinable roll rate during flight after burn-out • Derive ODEs of the rockets roll behavior • Use linear time invariant control theory to evaluate roll dampening using rollerons • Determine percent overshoot, steady state error, and settling time • Requirements • Ailerons deflect with an impulse to induce roll • Rollerons inactively dampen roll rate

  22. LFD • Procedures (after burnout) • Phase I • Ailerons impulse deflect • Rollerons locked • Rocket naturally dampens its roll rate • Phase II • Ailerons impulse deflect • Rollerons unlocked • Rollerons dampen out roll rate

  23. LFD Fin Layout • Uses pneumatic actuators to unlock rollerons and deflect ailerons • Rollerons locked using a cager Rolleron Cager Aileron Aileron Actuator

  24. LFD Manufacturing • All components locally manufactured Wheel on Mill Finished Wheel Casing

  25. LFD Assembled Fin

  26. LFD Air Tank Specifics and Failure Modes • Ailerons fail in the neutral position • Loss of air pressure fails to the neutral position

  27. LFD ANALYSIS • Roll data points analyzed using numerical methods • Plots roll characteristics • Derives an ODE • Linear Time Invariant Control Theory • Governing equation - • ODE transformed into Laplace form (frequency domain) • Impulse function (R(s) = 1) is applied to the plant (Gp) • From the plants denominator the frequency can be determined

  28. Flow Angularity • Objectives • Take differential pressure readings from each transducer • Determine angularity and boundary layer properties • Requirements • Pre-calibration in wind tunnel will result in non-dimensional coefficients • Can be compared to flight results to obtain angularity • Calibration involves testing probe at multiple angles and flow velocities

  29. Flow Angularity Schematics

  30. Flow Angularity Analysis • Non-dimensional coefficients

  31. Outline • Overview • System Design • Recovery Design • Payload Design • Simulations and Performance • Testing

  32. Flight Simulations • Used RockSim and MATLAB 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 • After wind tunnel testing, can get fairly accurate CD values that can be used in the program

  33. Performance • MATLAB code is compared with RockSim • Led to design changes • Maximum altitude predictions separated by 713 ft due to Cd value differences • maximum altitude predicted by RockSim of 5475 ft • MATLAB predicts 4772 ft • Room for unexpected mass or drag due to the simulations reaching over one mile

  34. Performance • Thrust-to-weight ratio • 12.98 • Need above 1 for lift-off • Rail exit velocity • 76.8 ft/s

  35. Drift Calculations SMD Payload Drift IntimiGATOR Drift

  36. Outline • Overview • System Design • Recovery Design • Payload Design • Vehicle Optimization • Simulations and Performance • Testing

  37. Component Testing Summary • All components of the launch vehicle and three payloads have planned tests • 21 tests outlined in detail in FRR report • Ensure all design details will work as expected • Allow the team to make necessary adjustments • Make sure the vehicle has a successful competition launch

  38. Some Completed Tests

  39. Subscale Results • Launched with Aerotech J500 3 separate times • 1st subscale launch had a successful deployment of the SMD mock payload • 2nd subscale launch showed that the SMD Main parachute housing was successful • 3rd subscale launch included the LFD payload fins with the rollerons unlocked • Rocket remained completely stable throughout flight and visually showed no roll

  40. Full Scale Launch • Occurred on March 17, 2012 • Launched with a Cesaroni L1720WT • Reached an altitude of 4294 ft. • Sustained some damage on impact due to no main parachute deployment

  41. Full Scale Launch- Lack of Altitude • Upper airframe launched was 4” longer than designed • Centering rings attached with screw inserts that sheared off • Motor impulse was not fully transferred to the rocket • Coefficient of drag may be higher than anticipated • A scale model of the rocket is being rapid prototyped to perform wind tunnel testing

  42. Full Scale Launch- Recovery • Separation did not occur at the main event at 700ft AGL • Multiple further tests are being performed to ensure separation

  43. Sponsors • NASA • Boeing • Millennium Engineering and Integration • Northrop Grumman • Pratt & Whitney • Acquip, Inc. • University of Florida Thank You!

  44. Questions?

  45. Community Outreach • Gainesville High School • 400 students throughout the school’s 6 periods • Interactive PowerPoint Presentation covering the basics of rocketry • Derivations of relatable equations • Model rocket launches

  46. Community Outreach • PK Yonge Developmental and Research School • 150 6th grade students • Interactive PowerPoint Presentation with videos • Model rocket launches

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