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 Flight Readiness Review Submission Deadline: March 18, 2013

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

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.

Launch Vehicle Dimensions Vehicle Dimensions 75.2” in length 4” Outer Diameter 10” Span Diameter

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

Motor Selection 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 : ft/s

Mass Statement Component:Mass:Notes: Motor Casing12.15Weighed with retention ring Fin Can52.75Includes retention ring Secondary Payload20.3With electronics and threaded rod Removable Bulkhead6.6With eyebolt Drogue5.5With Harness and Nomex Avionics Bay Tube4.3With epoxied t-nuts Avionics16.1With avionics, batteries, nuts, threaded rod Drogue Bulkhead4.85 Main Bulkhead5.35 Piston6.5 Main Harness5.85With Nomex blanked Parachute Bay10.95 Main Parachute10.7With Quicklink Main Payload29.2With electronics and threaded rod Payload Recovery14.4With battery and fixing bolt Nosecone15.25Empty Payload Parachute4.25With Nomex, Harness and Quicklink Motor (J740)51.84Mass (loaded) Ballast19.2Added to removable bulkhead Total296.04

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

Recovery Systems (Parachute Selection) SectionParachute Choice Kinetic Energy [ft*lbf] DroguePublic Missile Works PAR PayloadPublic Missile Works PAR MainSky Angle

Recovery Systems (Altimeter Selection) AltimeterSelectionPrimary Deployment Altitude Secondary Deployment Altitude PrimaryPICO-AA2Apogee700’ BackupADEPT DDC22Apogee700’ PayloadPICO-AA1Apogee+50sNone (700’ from vehicle)

Kinetic Energy SectionParachute Choice Velocity (ft/s)Kinetic Energy (ft*lbf) DroguePublic Missile Works PAR PayloadPublic Missile Works PAR MainSky Angle

Predicted Drift Wind Speed [mph]Estimated Drift [ft] Wind Speed [mph]Estimated Drift [ft] Vehicle Deployed Payload

Vehicle Testing and Procedures FunctionTesting Procedure Charge TestingThe recovery systems were ground tested by prepping the rocket and ejecting the parachutes and primary payload. Fin TestingFin flutter was tested theoretically with fin flutter velocity theory and then compared to physical testing in a wind tunnel. Parachute TestingParachute testing was conducted by dropping the primary payload and vehicle off of a tall structure with the parachutes open to study the velocity at impact. Altimeter testingAltimeter testing was conducted within a pressured chamber and also by creating an impulse on the accelerometer.

Tests of the Staged Recovery System Ejection charge testing set up. 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.

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

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

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.

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 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: – Cessaroni K740 Total impulse less than 5,120 Ns: – 1855 Ns

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

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

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”

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 GlobalSat BU-353 GPS Xbee 900 Pro

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

Payload Testing and Procedures FunctionTesting Procedure Battery Life testingAllow the system for extended lengths of time under battery power. Xbee range testingGround station yagi antenna and smaller payload antennas are coupled to the Xbee transmitters and tested for transmission distance. Software testingPackets of data are sent between the payloads and ground station to verify transmission integrity and packet handing. Sensor testing and calibrationAtmospheric sensors tested on the prototype circuit board for continuity and are calibrated against known conditions for accuracy. Strength Testing/IntegrityDrop testing and launches to verify system hardware integrity.

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.

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

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.

Questions?