1. Rocket Based Deployable Data Network University of New Hampshire Rocket Cats Collin Huston, Brian Gray, Joe Paulo, Shane Hedlund, Sheldon McKinley, Fred Meissner, Cameron Borgal 2012-2013 Critical Design Report Submission Deadline: January 14, 2013

2. Overview Objective Launch Vehicle Dimensions Key Design Features Motor Selection Mass Statement and Mass Margin Stability Margin Recovery Systems Kinetic Energy Predicted Drift Test Plans and Procedures Payload Integration Interfaces

3. Objective The UNH Rocket Cats aim to create a Rocket Based Deployable Data Network (RBDDN). The objective is to design a low cost data network that can be deployed rapidly over a large area utilizing rockets.

4. Launch Vehicle Dimensions Vehicle Dimensions 71.31” in length 4.014” Outer Diameter 10.014” Span Diameter

5. Key Design Features Nose cone can be remotely deployed by the team on the ground One way bulkhead prevents the main parachute from being deployed when the nose cone is deployed The primary payload creates a Rapidly Deployable Data Network that allows wireless communication between devices

6. Motor Selection Cesaroni Technology Inc. K940-WT Reloadable Motor Total Length: 15.9 in Diameter: 2.13 in Launch Mass: 48.2 oz. Total Impulse: 1636 Ns Average Thrust: 936 N Maximum Thrust: 1116 N Burn Time: 1.75 seconds Thrust to weight ratio: 13.5:1 Exit Rail Velocity: 53.1 ft/s

7. Mass Statement Vehicle Weight ComponentMass (oz.) Nose Cone 7.196 Payload 1 (Deploy) 49.6 Fuselage Tubing 24.557 Bulkhead 1 3.8 Eject. Charges (3) 3.738 Main Parachute 1 Main Shock Cord3.54 OWB 6.32 Bulkhead 2 2 Avionics 23.84 Bulkhead 3 2.6 Drouge Parachute 0.41 Drouge Shock Cord3.44 Bulkhead 4 4.88 Payload 2 (Fixed) 29.62 Bulkhead 53.55 FWD Centering Ring0.416 AFT Centering Ring0.416 54mm MMT7.57 Fins (4)8.96 Motor54.71 Tube Coupler8 Launch Lug (2)1 Shear pins (4)0.035 Fire Blankets (3)3.79 Total254.988

8. Stability Margin Static Stability Margin – 1.81 calibers Center of Pressure – 55.048” from the nose tip Center of Gravity – 47.768” from the nose tip

9. Recovery Systems SectionParachute Choice Kinetic Energy [ft*lbf] DroguePublic Missile Works PAR- 30 4.91.7554.80600.34 PayloadPublic Missile Works PAR- 24 3.14.835.6465.5 MainSky Angle 3614.21.3420.5661.6 Flat Nylon recovery harness

10. Kinetic Energy SectionParachute Choice Velocity (ft/s)Kinetic Energy (ft*lbf) DroguePublic Missile Works PAR-30 54.8600.34 PayloadPublic Missile Works PAR-24 35.6465.5 MainSky Angle 3620.5661.6

11. Predicted Drift Wind Speed [mph]Estimated Drift [ft] 08 5440 10850 151300 201800 Wind Speed [mph]Estimated Drift [ft] 08 5440 101041 151862 202483 Vehicle Deployed Payload

12. Vehicle Testing and Procedures FunctionTesting Procedure One-way Bulkhead/Main ParachuteThe one-way bulkhead can be ground tested by prepping the rocket and ejecting the main parachute. Nose coneThe nose-cone can be ground tested by being ejected from the payload section of the rocket. Drogue ParachuteThe drogue parachute can be ground tested by ejecting and separating the booster section from the payload section of the rocket. Strength Testing/IntegrityUsing ejection charge testing to identify structural flaws, then reinforcing needed areas.

13. Scale Model Flight Test Successful exit from rails and drogue deployment Altimeter was switched off after drogue deployment The battery holder shorted the capacitor for the timer circuit The main parachute was never deployed

14. Tests of the Staged Recovery System Testing showed that revision of the one-way bulkhead was needed One-way bulkhead testing procedure. One-way bulkhead

15. Successful nose cone deployment.Successful main parachute deployment.

16. Payload Design Overview Primary payload – Deployed payload in nosecone – Atmospheric and GPS sensor data – Transmit and store sensor data Secondary payload – GPS sensor data – Act as node in network, transmit, and receive relevant data

17. Primary Payload Components Arduino Nano – Barometer: BMP085 – Humidity and Temperature: SHT15, Cantherm MF51-E thermistor – Ambient Light: PDV-P9200 – Ultraviolet: PC10-2-TO5 Raspberry Pi GPS: GlobalSat BU-353 Xbee 900 Pro

18. Secondary Payload Components Raspberry Pi GPS: GlobalSat BU-353 Xbee 900 Pro

19. Payload Testing and Procedures Battery – Test runtime under full payload power load – Use results to choose final battery packs Antenna – Test maximum transmission distance – Test antenna position in rocket – Test local EMI sources and positioning in payload

20. Payload Integration Sled containing primary payload is secured in nosecone using external bolts Sled containing secondary payload is secured in rocket body using a direct threaded connection

21. Interfaces Primary payload connects to recovery system via direct wired connection Communication to ground station and deployed nodes via Xbee 900mHz connection Avionics are isolated in separate bay 1” Launch rails

22. Conclusion Objective Launch Vehicle Dimensions Key Design Features Motor Selection Mass Statement and Mass Margin Stability Margin Recovery Systems Kinetic Energy Predicted Drift Test Plans and Procedures Payload Integration Interfaces

23. Questions?