Flight Readiness Review Atomic Aggies

1. Flight Readiness ReviewAtomic 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

10. Predicted drift from the launch pad with a 5-,10-,15-,20-mph wind

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

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

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?