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Student Launch Project Flight Readiness Review April 21, 2014

Student Launch Project Flight Readiness Review April 21, 2014. Team Structure. Presentation Overview. Final Launch Vehicle Final Motor Selection Static Stability/ Mass Margin Recovery System Full Scale Test Flight Verifications Integrated Research Payload.

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Student Launch Project Flight Readiness Review April 21, 2014

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  1. Student Launch Project Flight Readiness Review April 21, 2014

  2. Team Structure

  3. Presentation Overview • Final Launch Vehicle • Final Motor Selection • Static Stability/ Mass Margin • Recovery System • Full Scale Test Flight • Verifications • Integrated Research Payload

  4. Final Launch Vehicle Design and Dimensions

  5. Key Design Features • Launch Vehicle Sections • CubeSat, Hazard Detection, Multi-Staging • Fin Style • Launch Vehicle Separations • Booster Section, Drogue Bay/ Detachable Bulkhead

  6. Forward Section - CubeSat • Nose Cone • Voltmeter • CubeSat

  7. Avionics/Payload Section - Hazard Detection • Avionics/ Payload components • Hazard Detection System • Drogue bay disengagement

  8. Booster/Sustainer Section - Multi-Staging • Booster section disengagement • Fin Style and attachment • Positive Motor Retention

  9. Motor Description

  10. Thrust Curve of Motors

  11. Table of Motor Events

  12. Static Stability Margin

  13. Thrust-to-Weight Ratio and Rail Exit

  14. Mass Statement and Mass Margin

  15. Parachute Sizes and Descent Rates

  16. Kinetic Energies

  17. Predicted Drift from Launch Pad Predicted Altitude

  18. Test Plans and Procedures

  19. Full Scale Flight – 1st Test

  20. Full Scale Flight Test Data

  21. Recovery System Testing

  22. Electrical Component Testing

  23. Summary of Requirements Verification Launch Vehicle

  24. Key Design Features of the Payload • Hazard Detection System • Lateral Vibrations In line System (LVIS) • Tesseract

  25. Payload Design and Dimensions Hazard Detection/Avionics Bay

  26. Payload Design and Dimensions LVIS

  27. Payload Design and Dimensions Tesseract • Designed to measure the magnitude of accumulated triboelectric charge on the surface of the nose cone at carious altitudes • Time stamp all altitudes and charge measurements to assist in post flight analysis

  28. Tesseract Payload Overview • The system can be broken down into three separate subsystems: • Voltmeter • CubeSat • Ground Station • The nose cone will be coated with MGM Chemicals 838 Total Ground Carbon Conductive Coating

  29. Payload IntegrationHazard Detection/Avionics Bay

  30. Payload IntegrationLVIS • Locations of Raven3 • Avionics Bay • Above the Sustainer • Mini-Avionics Bay Raven3 on payload sled Raven3 diagram from manufacturer’s website

  31. Payload IntegrationLVIS • Electrical schematic of RockeTiltometer2 with Raven3 Image of RockeTiltometer2 with connections

  32. Payload IntegrationTesseract 1 2 6 5 4 3

  33. Interfaces with Ground Systems • 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

  34. Summary of Requirements VerificationPayload

  35. Questions?

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