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 Preliminary Design Report Submission Deadline: October 29, 2012

2. Overview Objective Vehicle Design Materials and Justification Vehicle Safety Major Components Recovery Design Payload Design

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. Vehicle Design Vehicle Dimensions 67.75” in length 4.014” Outer Diameter 10.014” Span Diameter

5. Materials & Justification ComponentMaterialJustification Nose Cone  PNC-3.9 Plastic Nose Cone  16.75” length  3” Collar  Easily manufactured  Designed to contain electronics bay Vehicle  4” Blue Tube  51” length  Strength  Impact Resistance  Cost Bulkheads  Fiberglass  Rigidity  Strength Motor Mount  Fiberglass  Rigidity  Strength Fins  Fiberglass  Rigidity  Strength

6. Stability Margin Static Stability Margin – 1.528 Center of Pressure – 48.321” from the nose tip Center of Gravity – 42.211” from the nose tip

7. Vehicle Safety Equipment Concerns: – Black Powder – Hazardous Materials – Motor Precautions: – Refer to Material Safety Data Sheet (MSDS) for related material – Mentor and safety officer on site for supervision

8. Motor Safety Pre-Launch – Appropriate motor selection – Full inspection of motor assembly and compartment – Safe distance before launch Post-Launch – Allow motor to cool before handling

9. Motor Selection Cesaroni Technology Inc. K400-GR-13 Reloadable Motor Total Length: 15.9 in Diameter: 2.13 in Launch Mass: 54.7 oz Total Impulse: 1595 Ns Average Thrust: 399 N Maximum Thrust: 475 N Burn Time: 4 s Thrust to weight ratio: 5.9:1 Exit Rail Velocity: 55.5 ft/s

10. Motor Justification The primary reasoning for this motor choice is to reach the 1 mile apogee goal Sufficient thrust to achieve safe rail exit velocity Iterative approach to select motor based on OpenRocket simulations The size of the motor fits very well in our vehicle design

11. Launch Vehicle Verification and Test Plan Overview Verification of Vehicle Components – Perform tensile testing on all the load bearing portions of the recovery system – Perform compression testing on the tubing and all other necessary portions of the vehicle Conducting planned test launches – To ensure payload electronics are working – Parachutes deploy properly – Sustains stable flight

12. Recovery Subsystem 3 Event Recovery System: Drogue parachute deployment at apogee Payload deployment at Range Safety Officer announcement Main parachute deployment at 700ft

13. Vehicle Recovery System ComponentPart Choice AltimeterADEPT22 Drogue ParachutePublic Missile Works PAR-30 Main ParachuteSky Angle Classic 36 Electric MatchesRocketFlite MF-12 Fully redundant recovery circuit #4-40 nylon screws for shear pins Black powder charges for separation

14. Payload Recovery System Ejection charge initiated by signal from ground station Nose cone separates and lands independently with PAR-24 parachute Utilize one way bulkhead to ensure that vehicle recovery system is not compromised

15. One Way Bulkhead Ejection charges will remove bulkhead from only one direction Shear pins to hold in bulkhead

16. Payload Design Primary Payload – Raspberry Pi – Sensor Suite (coincides with SMD) – GPS – XBee Pro 900 Secondary Payload – Raspberry Pi – GPS – Xbee Pro 900

17. Payload Design

19. Payload Verification Power: Payloads will require power for a minimum of 2.5 hours. Our goal will be to have enough power for 5 hours. The amount of required power will be calculated and tested Data Acquisition: Testing will be done by collecting data from all sensors and analyzing the results Network: Both payloads will be tested by being able to successfully communicate with each other

20. Payload Verification Data storage: Payloads will be given data to store over the network. Successful storage will be tested Location tracking: Payloads will have a GPS module. Correct location data will be tested Network Range: Payloads will be required to be able to communicate and maintain a network at a distance of 1 mile. Our goal of 2 miles will be tested with a clear line of sight for 2 miles and analyzing signal loss