Plantation High School Team 1 CDR

1. Plantation High School Team 1 CDR Engaging students through STEM payload integration

2. Final launch vehicle dimensions • 14.2lbs / 6441.012g (without motor) • 16.7lbs / 7597.5g (with motor) • 94.5in.

3. Discuss key design features • Nose Cone - • carbon fiber. • very light and strong • Payload Bay - • Payload holder • (See payload design) • Transition - • 6 in. - 3 in. airframe. • 2 centering rings • Holding 3in coupler • Thrust Plate • Aluminum • Force distribution • Bolted and epoxied

4. Construction Middle Section/ Part 2 of 3 Bottom section/ Part 1 of 3

5. Construction • Laid out on mold • Epoxied • vacuum sealed Filled with clay to help hold smooth shape

6. Construction Thrust Plate used in previous years • Milled with Da Vinci 3-axis CNC router

7. Final motor choice • Aerotech K1275 • Average thrust of 1200N • Burn time 1.8 Sec

8. Backup motor choice • Aerotech K828 • Average thrust of 825N • Burn time 2.35Sec

9. Rocket flight stability in static margin diagram • CP: 72.1" from the nose cone • CG: 54.3" from the nose cone • Margin: 2.96

10. Thrust-to-weight ratio and rail exit velocity • Thrust-to-weight Ratio • 89.8 N/lbs. • Rail Exit Velocity • 99.93 ft/s.

11. Mass Statement and mass margin Mass Statement (Vehicle)

12. Mass Statement and mass margin Mass statement (Payload) Total - 6348g.

13. Parachute sizes, recovery harness type, size, and length, and descent rates • Drogue Chute - 24 In • Rip-stop nylon • 68.92 ft/sec • Main Chute - 86 In • Rip-stop nylon • 19.23 ft/sec • Recovery Harness • 2000 lb kevlar shock cord *Changed from tubular nylon

14. Kinetic energy at key phases of the mission, especially landing

15. Predicted drift from the launch pad with 5-, 10-, 15-, and 20-mph wind Predicted Drift (Based on wind speed) • 0 MPH - 0 Ft. • 5 MPH - 361.94 Ft. • 10 MPH - 717.78 Ft. • 15 MPH - 1101.92 Ft. • 20 MPH- 1471.56 Ft. Below Max of 2,500Ft.

16. Test plans and procedures • Parachutes- inspected and used in test launch • Shroud line connections • Recovery harness length • Ejection charges - tested outside • Separation • Black powder quantity check • Payload(sensor package) - tested in separate rocket • Properly recording data • February ~ • Vehicle's design, stability, and effectiveness • Test of full scale - March 9

17. Scale model flight test

18. Scale model flight test 1st launch: Apogee - 431 ft. • Drogue Deploy - apogee at 431 ft. • Main Deploy - 250 ft. -Engine: Estes F-50 single use 2nd launch: Apogee - 654 ft. • Drogue Deploy - Apogee at 654 ft. • Main Deploy - 250 ft. -Engine: Estes G-40 single use

19. Scale model flight Alt Bay Switch Raised Rail Button

20. Scale model flight test Carbon Fiber Nose cone and Transition No Main Deployment

21. Scale model flight test

22. Scale model flight test

23. Tests of the staged recovery system

24. Tests of the staged recovery system Main Drouge Alt bay

25. Tests of the staged recovery system

26. Final payload design overview -Elementary school • Collect data from egg vibrations to measure the conditions the egg under high G-forces • Egg held inside wooden prism • 5 Adjustable screws • 5 pressure sensors • Sensors connected to an Arduino Uno

27. Final payload design overview -Elementary school • Dimensions of elementary payload

28. Final payload design overview -Elementary school Each piece has size 8 hex nut in its center for screws. Curved sides for easy egg insertion and removal.

29. Final payload design overview Flexiforce pressure sensor places on cylinder • Linearity (Error) < ±3% • Repeatability < ±2.5% of full scale • Hysteresis < 4.5 % of full scale • Drift - 5% per logarithmic time scale • Response Time < 5 μsec

30. Final payload design overview -Middle school • Determine if the mixture will separate faster due to the high G forces. • Two airtight containers • 3 different liquids • Control • liquides layered with no disturbance • Test • liquids mixed with servo • Video recorded

31. Final payload design overview -Middle school Control Test Ball Bearing

32. Final payload design overview -Backup • Effectiveness of Shock absorbers • Reducing vibration during flight

33. Vibration Sensor Package Final payload design overview -Backup • Measures vibration. • Main chip: LM393, SW-18010P vibration switch. • Adjustable sensitivity • Aurduino Compatible Vibration Sensor

34. Final payload design overview -Sensor Package BMP085 Barometric Pressure Sensor ADXL335 Triple Axis Accelerometer RHT03 Temperature and Humidity Sensor Arduino Uno Microprocessor

35. Final payload design overview -Sensor Package

36. Final payload design overview Barometric Pressure Sensor Temp and Humidity Sensor -Sensor Package

37. Payload integration Payload holder • Three separated sections • 2 - 12in • 1 - 4in • Middle and elementary schools payload • Team Sensor package. • Held snug into nose cone by top bulkhead.

38. Payload integration

39. Interfaces (internal within the launch vehicle and external to the ground) Altimeter Bay Schematics

40. Interfaces (internal within the launch vehicle and external to the ground) • Will be using the Vehicle Garmin Astro 220 GPS Dog tracking collar • Range of 9 miles.

41. Status of requirements verification

42. Outreach

43. Outreach

44. Outreach

45. Outreach

46. This Concludes our Presentation Any Questions? Please visit us a http://phsaerospace.weebly.com