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Rocket Based Deployable Data Network

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. Overview. Objective

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Rocket Based Deployable Data Network

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  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?

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