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Student Launch Project Critical Design Review February 28, 2014

Student Launch Project Critical Design Review February 28, 2014. Team Structure. Final Launch Vehicle Dimensions. Key Design Features. Launch Vehicle Sections CubeSat/Electrometer, Camera System, Parallel Boosters Fin Style Launch Vehicle Separations

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Student Launch Project Critical Design Review February 28, 2014

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  1. Student Launch Project Critical Design Review February 28, 2014

  2. Team Structure

  3. Final Launch Vehicle Dimensions

  4. Key Design Features • Launch Vehicle Sections • CubeSat/Electrometer, Camera System, Parallel Boosters • Fin Style • Launch Vehicle Separations • Parallel Boosters, Booster Section, Drogue Bay/Detachable Bulkhead

  5. Forward Section-CubeSat • Nose Cone • Electrometer • CubeSat

  6. Avionics/Payload Section-Hazard Detection • Avionics/Payload components • Hazard Detection System • Drogue Bay disengagement

  7. Booster Section-Parallel Boosters • Parallel booster attachment/detachment • Booster section disengagement • Fin material and shape • Positive motor retention

  8. Final Motor Choice (18,500 ft)

  9. Thrust Curve of Motors (18,500ft)

  10. Table of Motor Events (18,500ft)

  11. Final Motor Choice (9,000 ft) Aerotech Motors were chosen over Cesaroni because of the motor mount sizes, should the team use Aerotech motors, the integration would only require the change of the type of motor casings used.

  12. Thrust Curve of Motors (9,000 ft)

  13. Table of Motor Events (9,000 ft)

  14. Static Stability Margin

  15. Thrust-to-Weight Ratio and Rail Exit

  16. Thrust-to-Weight Ratio and Rail Exit

  17. Mass Statement and Mass Margin

  18. Mass Statement and Mass Margin

  19. Recovery Subsystem • 6-sided parachutes with Cd=0.75 • Ripstop nylon • 80 – 120 CFM • 1 inch tubular nylon • 4000 lbs • 3/16 inch flat braided Dacron • 600 lbs • 3/8 inch brass grommets • No 69 size “E” nylon thread • 8.5 lbs

  20. Recovery Specifications

  21. Kinetic Energies

  22. Predicted Drift from Launch Pad 18,500 ft. Flight

  23. Predicted Drift from Launch Pad 9,000 ft. Flight

  24. Launch Vehicle Testing

  25. Exploding Nylon Bolt Testing

  26. Recovery System Testing

  27. Electrical Components Testing

  28. Scale Model Flight Test

  29. Scale Model Flight Test

  30. Staged Recovery Test • Deployment Testing • Static ground test for rocket separation and parachute deployment. • Altimeter Testing • Ground testing barometric pressure sensor and accelerometer calibration

  31. Hazard Detection System Overview • Cancellation of the LiDAR System • Cost • Availability of Parts • Eliminate moving parts • Raspberry Pi Edge Detection • Sobel Operator • Minimal components • Ease of integration

  32. P.I.M.S. Payload Overview

  33. P.I.M.S. Payload Overview

  34. P.I.M.S. Payload Overview

  35. Tesseract Payload Overview

  36. Hazard Detection/Avionics Bay Integration

  37. P.I.M.S. Payload Integration • Raven3 integration • Avionics Bay • Above the Sustainer • Mini-Avionics Bay • Payload Sled • Keeps Electronics upright throughout the flight • Ease of payload retrieval • Ease of manufacturing Raven3 diagram from manufacturer

  38. P.I.M.S. Payload Integration • RockeTiltometer • Ignition Control System • Ease of integration • Compatible with Raven3 Image from manufacturer

  39. Tesseract Payload Integration 1 2 6 5 4 3

  40. Launch Vehicle Interfaces • Internal Interfaces • Nose cone and payload sections • All-threads • Bulkhead-like centering rings • Nut locks • Drogue bay, avionics bay, main bay, sustainer section, booster section and mini parachute bay. • #2-56 nylon shear pins (x3 for each section) • External Interfaces • 1515 rail buttons • Parallel booster attachment points

  41. Payload Interfaces • Structural Interfaces • All-thread rods • Aluminum chassis • Plywood sleds • Grid style pc board

  42. Status of Requirements Verification

  43. Questions?

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