1. UCF_USLI 2010-2011 Preliminary Design Review David Cousin Freya Ford Md Arif Drew Dieckmann Stephen Hirst Mitra Mossaddad University of Central Florida 1

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3. 3 33.22” 24” 13.78” 30.78” 14” 4.5” Diameter Total Length of Rocket 97.5” 7.6” 12”

4.  Carbon Fiber Sleeves & Rolls for custom body, nosecone, and fins.  Nomex Honeycomb for fin structure.  Epoxy/Hardener University of Central Florida 4

5.  Center of gravity from the nose cone: X CG =52.0214 in  Center of pressure from the nose cone: X CP =74.6166 in  Rocket diameter: d=4.5 in  Static stability margin: SM=5.0212 University of Central Florida 5

6.  Hazards: Ammonium Perclorate (APCP) used for propellant in a motor Electronic match with pryogen coating To start the motor Hazard of premature ignition Gunpowder (Black powder) University of Central Florida 6

7. 7 In the case of windy conditions. In the case of calm conditions.

8.  Selection of Solid over Hybrid Motor Simple and easy start system Thrust schedule can be dictated by grain geometry Reasonably high specific impulse Sacrificing University of Central Florida 8

9. 9 breakdown of weights for all items used in the simulation of the rocket.

10. University of Central Florida 10 Trust curve for the Cesaroni Technologies Incorporated (CTI) L585-2G engine with a total impulse of 2653.40 Ns.

11.  Total weight of the simulated rocket With a payload of 160 oz. : 326.933 oz. With a payload of 200 oz. : 366.933 oz.  Cesaroni Technologies Incorporated (CTI) L585-2G engine Total impulse: 2653.40 Ns Maximum Thrust: 153.03 lbs (680.71 N) Average Thrust: 131.05 lbs (582.96 N) Max thrust to weight ratio  160 oz. payload: 153.03/326.933 = 0.4681 lbs/oz  200 oz. payload: 153.03/366.933 = 0.4171 lbs/oz Average thrust to weight ratio  160 oz. payload: 131.05/326.933 = 0.4008 lbs/oz  200 oz. payload: 131.05/366.933 = 0.3571 lbs/oz University of Central Florida 11

12.  Motor Purchase Plan NAR certified motors purchased by L2 certified TRA member  Motor Storage All components will be locked in flammable marked cabinet  Motor Transportation Responsibility of TRA advisor to drive motors. University of Central Florida 12

13. University of Central Florida 13 Batteries GPS Telemetry System SMD Sensor Package Camera

14. Avionics: University of Central Florida 14 ComponentModelQty.Image Flight Computer PerfectFlite MiniAlt/WD 2 GPS System Ozark Aerospace ARTS TT2 Ozark Aerospace ARTS RX-900 1111

15. Sensors & Camera: University of Central Florida 15 ComponentModelImages Microcontroller Arduino Duemilanove 3-Axis AccelerometerADXL345 Pressure Transducer/ Temperature Sensor BMP085 Humidity SensorHIH-4030 Solar Irradiance Sensor BPW34 Silicon Photodiode Ultraviolet RadiationUV12-R1-A Magnetism SensorHMC5843 CameraVD80 Mini

16. University of Central Florida 16  Design Completed A complete SMD payload including temperature, relative humidity, UV radiation, solar irradiance, pressure, acceleration, and magnetism sensors with a camera and GPS system has been designed. The Arduino has been designed for the addition of flash memory. Both the Arduino microcontroller and the camera system have USB connectivity capability for data recovery.  Full Scale Test Launch The full scale test launch will include all SMD Payload components. If the SMD Payload is recovered in good working condition, it will be deemed structurally stable for reuse. If the data recorded during the launch is recoverable, the SMD Payload design will be verified.

17.  Panel Schematic A payload bay panel schematic has been drawn outlining the layout of the SMD Payload verifying that it can be integrated into the payload bay.  Calibration and Testing All SMD Payload sensors and systems will be verified through calibration and testing. University of Central Florida 17

18.  Design Completed A complete recovery system including electric matches, a primary and secondary flight computer as well as drogue and main chutes has been designed.  Flight computer programming The primary and secondary flight computers will be programmed to eject the drogue chute at apogee and the main chute at 1000 ft.  Parachute ejection locations Structure design includes a separation point between the lower and mid sections for the main chute and another separation point between the mid and upper section for drogue. University of Central Florida 18

19.  Parachute ejection testing Recovery system shall be assembled to launch configuration. Static tests will be performed to verify that the ejection charges are capable of separating the structure sections and pushing out the parachute. Once verified on the ground, the parachute ejection system will be tested dynamically during the sub-scale launch.  Parachute descent rate test Both the drogue and main parachutes will be tested by securing a mass (equivalent to the launch vehicle and payload) to the chute and dropping it off a tall building. A stopwatch will be used to calculate the time to landing. The descent rate will then be calculated. University of Central Florida 19