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 Flight Readiness Review Submission Deadline: March 18, 2013

2. Overview • Objective • Launch Vehicle Design and Dimensions • Key Design Features • Motor Selection • Mass Statement and Mass Margin • Stability Margin • Recovery Systems • Kinetic Energy • Predicted Drift • Test Plans and Procedures • Full-scale Flight Test • Recovery Testing • Summary of Requirements Verification • Payload Design • Key Design of the Payload • Payload Integration • Interfaces • Summary of Requirements Verification

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 • 75.2” in length • 4” Outer Diameter • 10” Span Diameter

5. Key Design Features • 2+1 event recovery system to allow safe vehicle recovery with separate payload ejection • Piston based ejection system for the main parachute • Removable aluminum bulkheads to allow for full tube access • Fiberglass and Kevlar reinforced blue tube

6. Cesaroni Technology Inc. K740-CS Reloadable Motor • Total Length: 15.9 in (4 grain) • Diameter: 54 mm • Launch Mass: 51.8 oz. • Total Impulse: 1855 Ns • Average Thrust:747 N • Maximum Thrust: 869 N • Burn Time: 2.48 seconds • Thrust to weight ratio: 9:1 • Exit Rail Velocity : 45.17 ft/s Motor Selection

7. Mass Statement

8. Stability Margin • Static Stability Margin • 1.81 calibers • Center of Pressure • 53.5” from the nose tip • Center of Gravity • 46.3” from the nose tip

9. RecoverySystems (Parachute Selection)

10. RecoverySystems (Altimeter Selection)

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

12. Predicted Drift Vehicle Deployed Payload

13. Vehicle Testing and Procedures

14. Tests of the Staged Recovery System • Deployed the main and drogue parachutes. • Deployed the nose cone. • Successfully tested the main parachutes ejection charge potential of deploying • the nose cone in the event of a nose cone deployment failure Successful deployment of main parachute and nose cone by main parachute charge. Ejection charge testing set up.

15. Full-scale Flight Test #1 • Successful exit from rails • Successful main payload deployment • Issues with vehicle recovery systems caused total parachute failure or “lawn dart” • Failure causes determined and improved through post flight inspection

16. Full-scale Flight Test #2 • Mission success for all vehicle requirements • Payload flown with mass simulators • Drift well controlled in high winds

17. Summary of Requirements Verification (Vehicle) • Cesaroni K740: • Apogee of 5,282 feet (AGL) • Altimeters: • PICO-AA2 (primary), ADEPT DDC22 (primary backup), and PICO-AA1(nose cone) • Vehicle velocity: • 0.58 Mach • Recoverable & Reusable: • Non-degradable and reusable materials were used. • Independent Sections: • 3 sections, nose cone, booster section, and parachute bay. • Prepared for flight within 2 hours: • Full scale test launch took 1 hour and 36 minutes to fully prepare.

18. Summary of Requirements Verification (Continued) • Remain in launch ready state for 1 hour: • Estimates suggest 8 hours of functionality before any functionality is lost. • Rail size: • The rocket is functional with a 10 10 rail size. • 12 volt direct current firing system: • Succesfully launched full scale with a 12 volt current firing system. • No external circuitry • There is no external circuitry. • Commercially available motor: • CessaroniK740 • Total impulse less than 5,120 Ns: • 1855 Ns

19. Summary of Requirements Verification (Continued) • Ballast: • The ballast is less than 10% of the unballasted vehicle mass. • Successful full scale launch: • Successful launch was completed on March 17, 2013

20. Payload Design Overview • Primary payload • Deployed payload in nose cone • 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 Primary payload exploded diagram Primary payload in nose cone

21. Payload Sled Design • Fiberglass trays with aluminum threaded rods and Delrin® blocks • Machined aluminum rear bulkhead and fiberglass front bulkhead • Primary sled dimensions: 11.5” x 3.75” • Secondary sled dimensions: 7” x 3.9”

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

23. Secondary Payload Components • Raspberry Pi • GlobalSat BU-353 GPS • Xbee 900 Pro Secondary payload model render

24. Payload Testing and Procedures

25. Payload Integration • Sled containing primary payload is secured in nosecone using external bolts • Sled containing secondary payload is secured in rocket body using the same method.

26. 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 • Testing for effects of EMI performed • 1” Launch rails

27. Conclusion The team has built and tested a rocket for competition in the NASA-USLI. We are excited to travel to Huntsville and show off our hard work.

28. Questions?