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) MotorBrand Engine CodeDiameterLengthBurn TimeImpulseThrust BoostersCesaroniJ240 RL54 mm9.2913 in3.35 s808.959 Ns241.624 N MainCesaroniL61098mm16.8110 in8.13s 4842.188 Ns595.595 N SustainerCesaroni L3150 Vmax98mm15.5118 in1.57 s 4806.279 Ns3063.279 N

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

10. Table of Motor Events (18,500ft) EventTime (s)Altitude (ft)Velocity (ft/s) Motors Ignite000 Parallel Motors Burnout3.35900550 Separation of Parallel Boosters 51800600 Main Motor Burnout8.133800590 Main Motor Separation104700481 Sustainer Ignites if within 5 degrees of the Z-axis 11.55400478 Sustainer Burn Out13.0770001265 Apogee381850010

11. Final Motor Choice (9,000 ft) MotorBrand Engine CodeDiameterLengthBurn TimeImpulseThrust BoostersAerotech I229T 54 mm6.1417 in1.73 s413.681 Ns239.122 N MainAerotechL339N98mm12.1654 in8.43 in 2800.459 Ns332.359 N SustainerAerotechK1999N98mm11.3780 in1.40 s 2520.394 Ns1800.281 N 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) EventTime (s)Altitude (ft)Velocity (ft/s) Motors Ignite000 Parallel Motors Burnout1.73200230 Separation of Parallel Boosters 51070280 Main Motor Burnout8.432100300 Main Motor Separation102500250 Sustainer Ignites if within 5 degrees of the Z-axis 11.52800200 Sustainer Burnout12.93700711 Apogee30900024

14. Static Stability Margin Stability Analysis From nose coneWith Booster SectionWithout Booster Section Center of Pressure90.7870’”63.1160” Center of Gravity79.6498”54.2552” Static Stability Margin1.801.43 Rail Size/Length1.5” (1515) / 144”

15. Thrust-to-Weight Ratio and Rail Exit Ascent Analysis (18,500ft) With Booster SectionWithout Booster Section Rail exit velocity (ft/s)63.23- Max velocity (ft/s)6201283 Max Mach number0.551.14 Max acceleration (ft/s 2 )211685 Peak altitude (ft)715018500 Thrust-to-Weight Ratio5:119:1

16. Thrust-to-Weight Ratio and Rail Exit Ascent Analysis (9,000ft) With Booster SectionWithout Booster Section Rail exit velocity (ft/s)57.46- Max velocity (ft/s)300698.558 Max Mach number0.270.62 Max acceleration (ft/s 2 )175411.965 Peak altitude (ft)32009000 Thrust-to-Weight Ratio4.38:113.5:1

17. Mass Statement and Mass Margin SubsystemMass (oz)Mass Limit (oz) Propulsion (Including: motor mounts and centering rings) 469586.25 Structure (Including: body tube, coupling tubes, bulkheads, nose cones, fin sets) 232.53290.66 Recovery (Including: main parachute, drogue parachute, detachable components parachutes) 83.23104.04 Payload (Including: avionics bays, electrical components) 202.47253.09 Miscellaneous (Including: Paint scheme, dressings/coatings) 1620 Total10031254.04

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 ParameterDrogueMainParallelBooster Diameter (in)851202060 Deployment Altitude (ft) 18500120017007150 Velocity at Deployment (ft/s) 0.872817.038119 Descent Rate (ft/s)17.0314.89518.4320.15 Harness Length (ft)2030610 Shroud Line Length (in) 1001352570

21. Kinetic Energies ParachuteSection Mass of Section (lbs) Terminal Velocity (ft/s) Kinetic Energy (ft-lbs) ParallelParallel Motor0.67418.4383.56 Booster Booster Section2.7820.15728.40 Mini Avionics Bay4.5120.15717.54 Drogue Drogue & Main Bay 26.2727.07-- Drogue Bay10.4117.02746.93 Main Avionics Bay8.67514.89529.87 Main Section6.0414.89520.68

22. Predicted Drift from Launch Pad 0 mph5 mph10 mph15 mph20 mph 0 ft.622.88 ft.1280.92 ft.2046.53 ft.2663.46 ft. 18,500 ft. Flight

23. Predicted Drift from Launch Pad 0 mph5 mph10 mph15 mph20 mph 0 ft.847.97 ft.1424.93 ft.1666.09 ft.1301.99 ft. 9,000 ft. Flight

24. Launch Vehicle Testing Test PurposeTest Status Subscale TestTo ensure safe stage separation is possible Completed Cluster Ignition Test To ensure parallel circuitry can cause simultaneous ignition Completed Nylon Tie- Downs To ensure rocket motors all ignite before rocket launches Planned Booster Section Separation Ground Test To ensure booster section can separate from main bay with attachment scheme Planned Airstart TestTo ensure Raven3 has appropriate output current to airstart sustainer Planned

25. Exploding Nylon Bolt Testing Test PurposeTest Status Exploding Nylon Bolt Test To ensure exploding nylon bolts can safely separate parallel boosters from the booster section Completed. 1.5 x 3/8 inch exploding nylon bolts with 1/8 inch wide cavity almost an inch deep. Kerf mark below head. Exploding Nylon Bolts Shearing Strength To ensure exploding nylon bolts have enough shear strength to withstand rocket launch. In progress

26. 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 Planned To test static ejection charges of full scale parachutes Planned To demonstrate durability of bulkhead attachment scheme within the rocket. Planned

27. Electrical Components Testing Test PurposeTest Status Raspberry Pi Camera module To test functionality and accuracy Completed. Camera board communicated effectively with Raspberry Pi RockeTilTometerTo test functionalityPlanned ElectrometerTo test functionality and accuracy Planned Transceiver to Ground Station To test functionality and accuracy Planned Linx TM Series GPSTo test functionality and accuracy Planned

28. Scale Model Flight Test

30. Staged Recovery Test Deployment Testing o Static ground test for rocket separation and parachute deployment. Altimeter Testing o 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

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 3 4 5 6

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 o All-thread rods o Aluminum chassis o Plywood sleds o Grid style pc board Electrical Connections USB Connections Raspberry Pi, Power Supply Arduino, GPS, Camera, Digital and Analog Connections Atmospheric Sensor Serial Connections Raspberry Pi ↔ Xbee, GPS Arduino ↔ Xbee, GPS

42. Status of Requirements Verification RequirementStatus Rocket must not fly higher than 20,000 ft. AGL.Complete Rocket must carry a scientific payload.Complete Rocket must have dual altimeters.Complete Rocket must have dual deploy recovery system.Complete Rocket must be reusable on the day of recovery.Complete Rocket must land within 5000 ft. of the launch pad assuming 20 mph wind.Complete Students must do all critical design and fabrication.Complete Team must use a launch and safety checklist.Complete 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 of 18,500 with 500 foot variance.Complete Drogue parachute successfully deploys at apogee and main at 1200 ft.Complete Rocket must be compatible with a 1.5’’ launch rail.Complete Sustainer motor will only ignite if angle of attack is between 0-5 degrees.Complete

43. Questions?