1. Flight Readiness Review Atomic Aggies

2. Final Launch Vehicle Dimensions Diameter 5.5” Overall length: 117.14 inches Approximate Loaded Weight: 35.25 lb.

3. Key Design Features of launch vehicle 5.5 “ Blue Tube Fiber glass reinforced 3 (3/8”) Birch Plywood fin set Ogive polycarbonate nosecone Electronic Bay contains 3 ports for external data acquisition (solar irradiance, UV and video)

4. Motor Description Cesaroni Technology L800 Reload Propellant Weight: 63.3 oz. Average Thrust: 804 N Total Weight: 123.8 oz.

5. Rocket flight stability in static margin diagram CP: 92.65 inches CG: 69.84 inches Stability Margin: 4.13 Overstable

6. Launch thrust-to-weight ratio and rail exit velocity Exit Rail Velocity from RockSim: 57.1 feet/sec.

7. Mass statement Met mass predictions for design Maintained vehicle weight to 440 oz. Mass growth since CDR 6%

8. Parachute sizes, recovery harness type, size, and length Drogue Parachute: Classic Elliptical 24” diameter Decent Rate: 53.91 ft/s Main Parachute: Iris Ultra 96” diameter Decent Rate: 5.34 ft/s Recovery harness will be 27’ of ½” tubular nylon.

9. Kinetic energy at key phases of the mission Parachute Velocity at Deployment (ft./s) Landing Velocity (ft./s) Kinetic Energy During Decent (ft-lb) Kinetic Energy Upon Landing (ft-lb) Drogue 0 Section 1 – 333.5 Section 2 – 300.1 Section 3 – 606.98 Main49.55.34Section 1 – 3.27 Section 2 – 2.94 Section 3 – 5.955

10. Predicted drift from the launch pad with a 5-,10-,15-,20-mph wind WindPredicted Drift 5 MPH340.845 MPH 10 MPH682.155 MPH 15 MPH1023 MPH 20 MPH1362.45 MPH

11. Test plans and procedures Full scale test launch: 1 st test launch took place February 16 th 2 nd and 3 rd test launch took place on March 17 th

12. Full-scale flight test Altitude vs. time Feburary 16 th March 17 th

13. Recovery system tests Altimeter check - Simulation of altitude by changing the pressure in jar. Wiring test – check for continuity by shorting leads on terminal Ground test – test ejection charges and shear pins

14. Summary of Requirements Verification (Launch vehicle) 1 dedicated altimeter for scoring Maximum velocity is 52% of Subsonic (589.64 ft./sec.) Peak Altitude is 5277.8 ft. Rocket is recoverable and reusable containing 3 independent sections Assembled and prepared vehicle in 1 hr. 20 mins during 2 test flights Tested on board components and have remained flight ready for 2.3 hours Launch Vehicle is designed to fit on 8’ x 1” rail and launched by a 12 V ignition system w/o external support Cesaroni L800 is a reloadable motor Total impulse is 3757 Ns 3.4% of design is Ballast Vehicle design construction costs has maintained under $5,000

15. Payload design and dimensions The scientific payload and components will be mounted on a 5.36” x 18” piece of ½” ply board. Blue-Tube coupler material split lengthwise around the payload making a 5.36” diameter

16. Payload integration The payload will be encased in a blue tube coupler that will be cut to fit inside of the air frame allowing for easy access to the internal components. The payload bay will be integrated into the rocket body by sliding it in the air frame and held in place by a piece of blue tube cut to the radius of 2.68” place below the payload inside of the air frame. The payload will be aligned with a hole on the exterior of the airframe for the HD video camera.

17. Interfaces with ground systems GPS – The GPS system is the BRB900 TX/RX Base GPS Telemetry system operating at 900MHz. The data will be received by a LCD hand held receiver and Smart Data Controller connected to the ground station computer. Transmitter/Receiver – The Xbee Pro 900 transceiver will transmit and receive the stored data from the DE0 – Nano board to the ground station.

18. Summary of requirements verification (payload) The payload measures solar irradiance, ultraviolet radiation, atmospheric pressure, temperature, and humidity. The payload contains one camera taking video throughout the duration of the flight. The payload includes a GPS unit to aid in vehicle recovery. Data will be sampled and stored starting at apogee until ten minutes after landing. The data will be transmitted wirelessly to a ground receiving station and stored on a personal computer.

19. Questions from Panel?