University of Florida Rocket Team Preliminary Design Review Presentation

1. University of Florida Rocket TeamPreliminary Design Review Presentation

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

3. Overview Mass: 91.16 pounds Target Altitude: 10,000 feet Lower Electronics Bay Lower Airframe Upper Airframe Upper Electronics Bay Middle Airframe Heat-Coated Bulkhead Piston Hatch Boattail Baffles Centering Rings

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

5. Dimensions About 135 inches long Inner diameter: 6.0 inches Outer diameter: 6.2 inches

6. Airframe • Four sections of airframe • Upper Airframe (24 inches) • Upper Electronics Bay (18 inches) • Middle Airframe (18 inches) • Lower Airframe (48 inches) • E-class fiberglass tubes rolled in house

7. Upper Electronics Bay Features a hatch to allow for easy access to the electronics L-shaped platform to maximize space

8. Lower Electronics Bay Located in lower airframe just above motor Lower plate with hole in center for wiring

9. Lower Airframe Lower electronics bay, centering rings, and motor tube slide out as one piece Bulkhead above motor is heat coated to protect electronics Threaded rod lines up holes and transfers thrust to the bulkhead and 2 centering rings

10. Bulkheads and Centering Rings Machined from aluminum Fasten to the airframe with 4 screws Precise Relatively thin and lightweight

11. Boattail To reduce base drag Serves as motor retention and motor centering Houses the camera for ground scanning payload Exposed length: 2.67 in

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

13. Motor Choice • Chosen for consistency and geometry • Certified by National Association of Rocketry (NAR)

14. Outline • Overview • Vehicle Design • Motor Choice • Flight Dynamics and Simulations • Recovery • Payloads • Electronics • Future Work

15. Stability Characteristics Rail Exit Velocity = 70 ft/sec Thrust to Weight Ratio = 6.85

16. Flight Simulations OpenRocket software used to simulate rocket’s flight Wind tunnel testing in the near future will allow for more accurate drag coefficient values

17. Altitude versus Time • Maximum altitude of 10,200 feet • Drogue parachute deployment at 25 seconds (apogee) • Main parachute deployment at 210 seconds, 700 feet of altitude

18. Velocity and Acceleration versus Time • Peak velocity of 892 ft/s at 4 seconds • Shows drogue and main parachute deployment at 25 and 210 seconds respectively • Peak acceleration of 292 ft/s2 at 1.5 seconds • Shows acceleration from drag and gravity up to apogee at 25 seconds • Constant velocity under drogue, zero acceleration

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

20. Recovery Objectives Reusable without repairs Kinetic Energy each piece is less than 75 ft-lbf Main and drogue parachute manufactured by team GPS tracking device Minimal crosswind drift

21. Recovery System Drogue Deployment at apogee 60 inches in diameter Semi-ellipsoid canopy shape Charge baffle ejection system Descent velocity: 48.1 ft/s Main Deployment at 700ft 168 inches in diameter Semi-ellipsoid canopy shape Piston Ejection System Descent velocity: 12.4ft/s

22. Parachute Manufacturing Ripstop nylon Gore design Hem tape Shroud lines

23. Charge Baffle Two discs with non overlapping circular patters of holes Cools gasses from ejection charges and removes particulates Used to protect drogue parachute

24. Kinetic Energy

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

26. Ground Scanning System 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

27. 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

28. Camera Integration Camera will mount in boattail Titanium Nitride Heat Coating on boattail

29. Payload Verification Saved control image analyzed for hazards and quantified by team Success criteria requires 75% of analyzed hazards to be detected by software

30. Boost Systems Payload Enables characterization of realtime internal forces imparted by motor during burnout Provides a novel way to calculate drag on the rocket Enables in-flight, real time structural analysis of component assemblies Bulk Head Strain Gage Motor Tube Motor Casing

31. Triboelectric Effect Analysis • Substantial charge build up due to triboelectric effects can institute a Faraday cage hindering incoming and outgoing signals • Payload reveals a novel way to characterize the effects of triboelectric buildup on antenna signal power in a simple, low resource, recoverable, and easily instituted package • System Design • Conductive paint is used to coat the payload bay which houses the antenna for the rocket. • Fastened in contact to the conductive paint is a wire which is run down the length of the rocket and connected to static wicks located on the trailing aft edge of the fins. • A relay is located inline with the wire allowing connection to be made from the conductive paint to the static wicks. • During lift off the antenna communicates with a groundstation where the received power is measured. • The the relay is disconnected and charge is allowed to accumulate on the conductive coatingforming a Faraday cage disrupting the out coming signals to an extent. • Once around 5,000 ft the relay is connected allowing charge to accumulate now on the static wicks ridding the payload bay of the faraday cage. • The sudden spike in signal power should be picked up by the groundstation and directly related to the charge build up on the conductive paint.

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

33. Image Processing

34. Data Acquisition & Communication

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

36. Component Testing Recovery Testing Structural Testing Electronics Testing Motor Testing Payload Component Testing

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

38. Future Work Develop detailed, final design Manufacture subscale Component Testing Order all materials Subscale Launch, Feb. 8th