Rocket Based Deployable Data Network

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. 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 Motor Selection

7. Mass Statement

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 • Flat Nylon recovery harness

10. Kinetic Energy • KE = • The kinetic energy values shown are calculated from the chosen parachutes for the rocket

11. Predicted Drift Vehicle Deployed Payload

12. Vehicle Testing and Procedures

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 • ArduinoNano • 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?