University of Florida IntimiGATOR CDR

1. University of Florida IntimiGATORCDR

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

5. System

6. Vehicle Dimensions • Diameter: 6 inches • Length: 115 inches • Weight: 29 lbs

7. Static Stability Margin CG = 72.7” CP = 91.1” The static stability margin is 3.03

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 • Vehicle Optimization • 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 SMD Payload Lander

16. Outline • Overview • System Design • Recovery Design • Payload Design • Vehicle Optimization • 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 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

26. 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

27. Flow Angularity Schematics

28. Flow Angularity Analysis • Non-dimensional coefficients

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

30. Vehicle Optimization • Objective • Optimize rocket geometry to maximize performance • Create a robust design that can accommodate any uncertainties in the EOM • Requirements • Determine uncertainty in the EOM • Perform parametric analysis

31. Vehicle Optimization • Vertical EOM: From RockSim Standard Atmosphere Manufacturer Specifications Design Space Variable Mass variance during thrust; Low uncertainty

32. Vehicle Optimization • Cost Function: • Want to maximize delta drag coefficient while still attaining target altitude

33. Vehicle Optimization • Design Space: Span (in) = [4, 7, 10, 13] Root chord (in) = [5, 8, 11, 14, 17, 20] Tip chord (in) = [4.5, 5, 5.5, 6, 6.5, 7, 7.5, 8] Fin location longitudinally (in) = [85, 90, 95, 100] • Determined based on minimum required dimensions for rolleron payload

34. Vehicle Optimization • Results: • Fin location has no impact on vehicle drag and can be altered to attain desired static margin • Area of low sensitivity occurs at minimum values of geometric design space • Maximum drag capacity occurs at minimum values of geometric design space

35. Vehicle Optimization

36. Vehicle Optimization

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

38. 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

39. Performance • MATLAB code is compared with RockSim • Led to design changes • Maximum altitude predictions separated by 71 ft • maximum altitude predicted by RockSim of 5352 ft • Room for unexpected mass or drag due to the simulations reaching over one mile

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

41. Drift Calculations

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

43. Component Testing Summary • All components of the launch vehicle and three payloads have planned tests • 21 tests outlined in detail in CDR 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

44. Completed Tests

45. Subscale Results – Dec 10th • Launched with AerotechJ500 • Payload ejected at apogee and both payload and rocket drogue parachutes deployed • Rocket drogue became entangled and only partially opened • IntimiGATOR main parachute deployed at 700 ft • upper airframe became detached from the middle airframe • Payload main parachute did not deploy until landing • No damage sustained

46. Subscale Flight and Simulations • Altitude data gathered from the flight was compared to both RockSimand MATLAB simulations • The motor has a higher initial thrust than expected causing the discrepancy for the first 5 seconds • Altitude reached: 1921 ft. • RockSim predicted: 1896 ft. • 9 degree launch angle led to the higher predicted altitude of the 1DOF MATLAB code

47. Next Subscale Launches • February 11th, Bunnell, FL • 1st Flight • Components tested • Fin mount assembly • SMD Payload main parachute deployment • Dual separation • Live data transmission • 2nd Flight • Components Tested • LFD payload system

48. Questions?