University of Florida Rocket Team Flight Readiness Review Presentation

1. University of Florida Rocket TeamFlight Readiness Review Presentation

2. Outline • Overview • Vehicle Design • Motor Choice • Flight Dynamics and Simulations • Recovery • Payloads • Electronics • Component Testing • Project Plan • Future Work

3. Design Overview 164 inches long Inner diameter: 6.0 inches Outer diameter: 6.14 inches Total Mass: 74.2 lbs Target Altitude: 10,000 ft

4. Outline • Overview • Vehicle Design • Motor Choice • Flight Dynamics and Simulations • Recovery • Payloads • Electronics • Component Testing • Project Plan • Future Work

5. Changes From CDR • Structural Changes from CDR include: • Nose cone • Nose cone Extension • Upper Airframe • Upper Electronics Bay/Airframe • Middle Airframe • Ballast mass • Fins

6. Nose Cone & Attachment • Problem • Lack of precision with nose cone plug • Difficulty fiberglassing the nose cone • Did not attach to vehicle as needed • Solution • Purchased a fiberglass tangent ogive nose cone • 11.5 inch nose cone extension airframe; length taken from upper airframe

7. Upper Electronic Bay/Airframe • Problem • Vibrations to the hatch • Electrical components interfering on the bay • Total length was compromised • Bay was not removable with CDR design • Solution • Eliminate the hatch • Build a Faraday cage • Shorten the airframe by 6 inches • Only one end has a coupler shoulder with nuts epoxied to it

8. Middle Airframe • Problems • Limited removability of UEB • Solutions • The middle airframe was changed to 14 inches long • Phenolic coupler was extended throughout airframe to provide a shoulder on either end • Shoulder that slid into UEB airframe had nuts epoxied to inside

9. Ballast Mass • Problem • No permanent solution for attachment mechanism • No proper location for ballast mass • No exact mass estimates • Solution • Remove ballast mass concept

10. Fins • Problem • Lighter mass estimates • Expected apogee higher than target altitude • Stability fluctuating • Solution • Induce drag by increasing the size of the fins and thickness • Move them forward

11. Key Design Features

12. Boattail Tangent ogive Reduces base drag Centers motor Houses GSS payload Motor retention

13. Motor Centering/ Thrust Capture Two centering rings One thrust bulkhead Threaded rod distributes load to LEB and centering mechanism Tapped holes in bulkheads for securing in place

14. Fin Attachment and Fillets G10 fins with 4 layers of fiberglass Fiberglass fillet Trapezoidal Flush with inside of body tube

15. Payload Integration Camera housed in boattail Triboelectric payload housed in nosecone Strain gages located on motor tube and easily accessible

16. Outline • Overview • Vehicle Design • Motor Choice • Flight Dynamics and Simulations • Recovery • Payloads • Electronics • Component Testing • Project Plan • Future Work

17. Cesaroni M1890 (N) Max Thrust: 2239 N Burn Time: 5.28 seconds Launch Mass: 19.5 lb. Empty Mass: 7.73 lb.

18. Cesaroni N2600-SK P Max Thrust: 2972 N Burn Time: 4.26 seconds Rail Exit Velocity: 67 ft/s Thrust to weight ratio: 8.51 Max Velocity: Mach .94 Launch Mass: 25.3 lb. Empty Mass: 10.4 lb.

19. Outline • Overview • Vehicle Design • Motor Choice • Flight Dynamics and Simulations • Recovery • Payloads • Electronics • Component Testing • Project Plan • Future Work

20. Mission Performance • 1. The vehicle achieves apogee between 9,500 and 10,500 feet. • 2. At apogee, the vehicle separates beneath the upper electronics bay, and the drogue parachute is successfully ejected. • 3. At 700 feet AGL, the nosecone and main parachute are successfully ejected. • 4. No portion of the vehicle or payloads sustain any major damage during flight or landing.

21. Altitude vs. Time Open Rocket Simulation Flight Data

22. Mass Statement

23. Velocity vs. Time

24. Stability Margin Static Stability: 1.88 calibers CG: 108 in. CP: 120 in.

25. Kinetic Energy

26. Crosswind Drift/Altitude

27. Outline • Overview • Vehicle Design • Motor Choice • Flight Dynamics and Simulations • Recovery • Payloads • Electronics • Component Testing • Project Plan • Future Work

28. Attachment Scheme

29. Recovery System Drogue Deployment at apogee 48 inches in diameter Semi-ellipsoid canopy shape Charge baffle ejection system Descent velocity: 63.3 ft/s Main Deployment at 700ft 168 inches in diameter Semi-ellipsoid canopy shape Piston ejection system Parachute deployment bag with 12in pilot chute Descent velocity: 12.6ft/s

30. Recovery Changes since CDR Use of a deployment bag for main parachute Drogue parachute reduced from 60in to 48in Number of shear pins increased Nylon upholstery thread size reduced Piston orientation changed

31. Main Parachute

32. Drogue Parachute

33. Deployment Bag

34. Full Scale Test

35. Full Scale Test

36. Full Scale Test

37. Outline • Overview • Vehicle Design • Motor Choice • Flight Dynamics and Simulations • Recovery • Payloads • Electronics • Component Testing • Project Plan • Future Work

38. Ground Scanning System Payload Ground Scanning System to detect hazards in the landing area Take an image of landing area Scan for potential hazards in real-time Send scanned image to Ground Station in real-time

39. Design Overview • Picture is taken and sent to Lower Computer • Image is saved, then sent to Upper Computer via onboard wifi • Image is run through custom color-mapping hazard detection software • Hazard is defined as the edge, corner or cliff of any surface or area. • Scanned image is sent to ground station via RF signal

40. Camera Module

41. Camera Integration

42. Payload Verification Camera module test successful Ceramic heat shield material protects camera from exhaust Saved control image analyzed for hazards and quantified by team Success criteria requires 75% of analyzed hazards to be detected by software

43. Boost System Analysis Payload Utilizes vehicle weight information and strain gage readings on the motor tube to determine the drag force seen on the rocket. Assumes that force of thrust is imparted directly onto the phenolic motor tube. Successful if the calculations of acceleration constructed from the strain gage readings coincide with the rate gyro acceleration readings.

44. Boost System Procedure Data acquisition of the strain gages will be triggered by the start of motor burn. The voltage across the Wheatstone bridges will be read by the data acquisition device until apogee. Post recovery, the data will be processed by relating the acquired voltages to strains. The strains are converted to stresses to ultimately arrive at the force of drag.

45. Boost System Integration Temperature Compensation Strain Gages Motor Tube Strain Gages Centering Rings Bulk Head

46. Triboelectric Effects Analysis Payload Determine charge build up on the exterior of the rocket Calculate surface charge density at each region Compare surface map of surface charge to the map of friction on the surface of the rocket Generate table relating acquired triboelectric charge to air friction

47. Design Overview

48. Design Integration

49. Payload Testing

50. Payload Verification