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 Voltmeter/ 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 MotorBrandEngine Code DiameterLengthBurn TimeTotal Impulse Maximum Thrust MainCesaroniK1620 - Vmax 98mm9.3307 in1.53s2432Ns996 N SustainerCesaroniL985TT54mm19.33 in2.7s2678 Ns1589 N

10. Thrust Curve of Motors

11. Table of Motor Events EventTime (s)Altitude (ft)Velocity (ft/s) Motor Ignites000 Main Motor Burnout1.53230290 Main Motor Separation2360275 Sustainer Ignites if within critical angle off of the Z-axis 2.5550270 Sustainer Burn Out5.22000700 Apogee247000<20

12. Static Stability Margin Stability Margin Center of GravityCenter of Pressure With Booster1.6887.6 in98.0 in Without Booster1.1465.8 in72.8 in

13. Thrust-to-Weight Ratio and Rail Exit Ascent Analysis With Booster SectionWithout Booster Section Rail exit velocity (ft/s)64- Max velocity (ft/s)290690 Max Mach number0.260.61 Max acceleration (ft/s 2 )260262 Peak altitude (ft)13507000 Thrust-to-Weight Ratio7:16:1

14. Mass Statement and Mass Margin SubsystemMass (lbs)Mass Limit (lbs) Propulsion (Including: motor mounts and centering rings) 12.015.0 Structure (Including: body tube, coupling tubes, bulkheads, nose cones, fin sets) 21.426.5 Recovery (Including: main parachute, drogue parachute, detachable components parachutes) 5.06.3 Payload (Including: avionics bays, electrical components) 13.016.3 Miscellaneous (Including: Paint scheme, dressings/coatings) 1.01.4 Total52.465.5

15. Parachute Sizes and Descent Rates ParameterDrogueMainBooster Diameter (in)8512060 Deployment Altitude (ft)700012001350 Velocity at Deployment (ft/s) >2054>20 Descent Rate (ft/s)17.51523 Harness Length (ft)203010 Shroud Line Length (in)93.513266

16. Kinetic Energies ParachuteParachute Size Vehicle Section Mass of Section Descent Rate Kinetic Energy Booster60 inchesBooster Section 6 lbs22.6 ft/s50 ft-lbs Mini Avionics Bay 3 lbs22.6 ft/s24 ft-lbs Drogue85 inchesDrogue & Main Bay 29.5 lbs54 ft/s-- Drogue Bay 11 lbs17.5 ft/s52.6 ft-lbs Main120 inchesAvionics Bay 8 lbs15 ft/s28 ft-lbs Main Section 8.5 lbs15 ft/s30 ft-lbs

17. Predicted Drift from Launch Pad 0 mph5 mph10 mph15 mph20 mph 0 ft.1050ft.2284ft.3654ft.4515 ft. Predicted Altitude 0 mph5 mph10 mph15 mph20 mph 7089ft.7078ft.7043ft.6981ft.6888ft.

18. Test Plans and Procedures Test PurposeTest Status Full-Scale Test Flight To ensure safe stage separation and sustainer motor ignition during flight In Progress Smart Ignition Device To ensure that the sustainer ignition charge will be inhibited if the rocket off of the vertical. Completed Booster Section Separation Ground Test To ensure booster section can separate from main bay with attachment scheme Complete Airstart TestTo ensure Raven3 has appropriate output current to airstart sustainer Complete

19. Full Scale Flight – 1 st Test

20. Full Scale Flight Test Data

21. Recovery System Testing Test PurposeTest Status To ensure design of parachute can withstand forces Completed – Successful To determine velocity that the parachute will fly, and impact force of different rocket sections Completed – Successful To test static ejection charges of full scale parachutes Completed – Successful To demonstrate durability of bulkhead attachment scheme within the rocket. Completed – Successful

22. Electrical Component Testing ComponentTest PurposeTest Status Microcontrollers including the Raspberry pi and Arduinos To test functionality and programming logic Completed RockeTiltometer and Raven 3 altimeters To test functionality and accuracy Completed VoltmeterTo test functionality and accuracy Completed XBee Pro 900To test functionality and communication between systems Completed GPS units for separable sections To test functionality and accuracy Completed

23. Summary of Requirements Verification Launch Vehicle RequirementStatus Rocket must not fly higher than 20,000 ft. AGLComplete Rocket must carry a scientific payloadComplete Rocket must have dual altimetersComplete Rocket must have dual deploy recovery systemComplete Rocket must be reusable on the day of recoveryComplete Rocket must land within 5000 ft. of the launch pad assuming 20 mph wind Complete Students must do all critical design and fabricationComplete Team must use a launch and safety checklistComplete Rocket must use a commercially available, certified motor Complete Rocket must be capable of being prepped for launch in less than 2 h Complete Rocket must be able to remain in a launch-ready configuration for at least 1 h Complete Rocket must attain an altitude between 6500-7500 ft.Complete Drogue parachute successfully deploys at apogee and main at 1200 ft. Complete Rocket must be compatible with a 1.5’’ launch railComplete

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 MotorBrandEngine Code DiameterLengthBurn TimeTotal Impulse Maximum Thrust MainCesaroniK1620 - Vmax 98mm9.3307 in1.53s2432Ns996 N SustainerCesaroniL985TT54mm19.33 in2.7s2678 Ns1589 N

27. Payload Design and Dimensions 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 Tesseract

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 Integration Hazard Detection/Avionics Bay

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

31. Payload Integration LVIS Electrical schematic of RockeTiltometer2 with Raven3 Image of RockeTiltometer2 with connections

32. Payload Integration Tesseract 1 2 3 4 5 6

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 (x2 for each section) External Interfaces 1515 rail buttons

34. Summary of Requirements Verification Payload PayloadRequirementStatus Hazard DetectionBulkhead covering camera must be detachableComplete Hazard DetectionPayload must be capable of detecting landing hazardsComplete Hazard DetectionData must be transmitted to the ground in real timeIncomplete LVISMotor staging must perform properlyComplete LVISPayload must record lateral vibrations in the airframeComplete LVISData must be recoverableComplete TesseractPayload must be able to record a potential differenceComplete TesseractPayload must record altitudeComplete TesseractData must be stored and recoverableComplete

35. Questions?