1. Atomic Aggies CDR

2. Final Launch Vehicle Dimensions Diameter 5.5” Overall length: 117.14 inches Approximate Loaded Weight: 34.36 lb.

3. Key design features 5.5” Blue Tube 3-3/8 Fiberglass reinforced birch plywood fin set Ogive polycarbonate nosecone

4. Final motor choice ManufactoryEngine Class/Model Diameter (mm) Length (in) Burn Time (s) Impulse (N- s) Avg. thrust (N) RockSim Altitude (ft.) Cesaroni Technology L8007519.14.683722795.55743

5. Rocket flight stability in static margin diagram

6. Thrust-to-weight ratio and rail exit velocity

7. Kinetic energy at key phases of the mission, especially landing Parachute Velocity at Deployment (ft./s) Landing Velocity (ft./s) Kinetic Energy During Descent (ft-lb) Kinetic Energy Upon Landing (ft-lb) Drogue 57.27 ft/s Section 1 - 365.5 ft-lb Section 2 - 331.04 ft-lb Section 3 - 651.89 ft-lb Main 75.729 ft/s18.66 ft/s Section 1 - 37.85 ft-lb Section 2 - 35.14 ft-lb Section 3 - 69.2 ft-lb

8. Test plans and procedures Full scale test launch: 1 st test launch is planned for Febuary 16 Data Analysis Planning for 2 nd test launch

9. Parachute sizes, recovery harness type, size, and length Drogue Parachute: Elliptical Custom 24” diameter Decent Rate: 75 ft/s Main Parachute: Iris Ultra 96” diameter Decent Rate: 16.53 ft/s Recovery harness will be 27’ of ½” tubular nylon.

10. Avionics Bay

11. Predicted drift from the launch pad Wind speedDrift 0-2 MPH0 Ft’ 3-7 MPH133.02445’ 8-14 MPH367.30896’ 15-25 MPH686.55649’

12. Final payload design overview The payload will incorporate sensors that will be used to measure solar irradiance, ultraviolet radiation, atmospheric pressure, temperature, and humidity once apogee is reached by our rocket. The payload bay will contain one camera taking video throughout the duration of the flight, where still shots will be obtained of the horizon. The payload will include a GPS unit to provide spatial data and to provide a tracking unit to aid in vehicle recovery. A DE0- Nano FPGA Development and Education Board will be used to control data collection operations and provide data logging. Data will be sampled and stored at a frequency of 1Hz starting at apogee until ten minutes after landing. The data will be transmitted wirelessly from the vehicle to a ground receiving station where it will be stored and processed on a personal computer.

13. Payload Integration/Testing Top is the DE-0 Nano board connected to the seven segment module for testing, and to the right is the PCB with temperature, pressure, and humidity sensors soldered on. The seven segment display above shows what channel (sensor) is being displayed along with the converted analog value. To display this data we also converted the digital measurements to HEX values for testing purposes making sure we are receiving the correct data information.

14. Interfaces The scientific payload will be independent of recovery electronics so that there is no interference between the two systems. The DE-0 Nano microcontroller will be used to take analog readings given from five specific atmospheric Strato-Logger Altimeter on board the payload to trigger the data collection at apogee. Data stored on the FPGA board will be transmitted to the receiver at the ground station.

15. Status of requirements verification Design Building process of full scale rocket has begun with about 30% completion. Payload Sensors have been interfaced to the FPGA and ongoing testing is still being done

16. Questions from Panel?