1. FRR Presentation IF AT FIRST YOU DON’T SUCCEED, TRY AGAIN… AND AGAIN AND AGAIN AND AGAIN

2. CFX-12 weighs approximately 830 oz. and has a total length of 110 in. The launch vehicle consists mainly of two different size body tubes constructed of G12 fiberglass. 2

3. Avionics Bay The avionics bay is used solely for the commercially available altimeter housing, keeping it isolated from any interfering electronics. Drag Brake The drag brake is a retractable nose cone which increases the drag of the rocket. A simple algorithm implemented with an on board computer is used to determine the correct time to deploy the drag break to achieve the target altitude. Recovery System Based on two deployments, one at apogee, one at 800ft. Rover The rover is one of CFX-12’s payloads that will be jettisoned during the descent phase of the mission. The design allows it to land on either side and also have usable ground clearance so it can pass over small obstacles. 3

4. CFX-12 Weight : 830 oz Max Altitude : 5,570 ft Max Velocity : 640 ft/sec 4

5. Total length: 110 in. Center of Gravity: 58.1 in Center of Pressure: 77.12 in. Static Margin: 2.37 5

6. Thrust-to-Weight: 9.8-to-1 Rail Exit Velocity: 60 ft/sec Maximum Velocity:640 ft/sec 6

7. We had a successful brake-deployed full scale launch: - Observed very stable flight. - Successful recovery—all pieces survived intact. - Electronics collected data effectively. - Drag coefficient computed from data corroborated existing results. 7

8. We believe our energy management approach will result in an apogee within 1% of 5,280 ft. - We collected the data necessary for effective brake deployment algorithm design. 8

9. Parachute Selection TypeSizeResult Main Parachute Ultra Iris 144144 1.9 Oz. Ripstop 18 Sides 33 inch Spill Hole Deployment at 800 Feet Drogue Parachute PAR- 36R36 Inch Nylon 8 Sides 7 inch Spill Hole Deployment at Apogee Range (15MPH) 1289 Feet Descent Velocity (Vehicle) After Drogue 96 Ft/Sec After Main 11.2Ft/Sec Rover Range & Velocity Range 736 Feet Velocity 22 Ft/Sec Cord Strength (Lbs) Harness(Lbs) (Weight x G-Force) Percentage Result (Lbs) 1500 51x25= 1275%17.651500 9

10. Wind Speed(MPH)Drift Prediction(Feet) Rover / Vehicle 5 MPH404774 10 MPH6921284 15 MPH903.51672 20 MPH11422032 10

11. Altitude(Feet)Time(Seconds)Kinetic Energy(Ft*Lbf) Rover/Vehicle 7902.2322.231 (Max) Apogee18.370 (Min) 80168.1013575583 200106.42 74.49 74.29 Touch Down122.0174.4974.29 11

12. #1 -Recovery successful - Rope has damaged the vehicle under heavy wind - Altimeter is not used #2 - Recovery Successful - Rope is burned due to wrong installation - Altimeter is not used #3 - Recovery successful - Don’t have reliable data of velocity - Altimeter is not used #4 - Recovery unsuccessful - Structural damage received - Altimeter used for data - Altimeter did not get damaged FS#1 - 3 Altimeters accordingly - Parachute’s efficiency - Ground control based on live data HS#5 -Altimeter Deployment - Motor ejection for backup - Correct size parachute - Amount of black powder - Touch down kinetic energy - FS#2 - Kinetic Energy Calculation -Drift prediction based on the wind - Critical decision of Rover separation 12

13. Tests  wind tunnel  full scale launch  ejection Procedures  launch  recovery  motor/ igniter 13

14.  The CFX-12's drag brake, is a retractable nose cone that will allow us to control our maximum altitude.  1 in stoppers at the base of the ogive. 14

15.  The rover is an autonomous vehicle capable of maneuvering on its own by utilizing a sophisticated sensor suite. Wheel diameter: 5 in. Length: 10 in. Weight: 5lbs 15

16. The rover will be housed inside the 8” upper fuselage of the CFX-12. During ascension the rover will be exposed to three forces that could affect mission success. Rotational motion – tangling of chute shock cord Vertical forces (gee loads) excess heat from ejection charges 16

17. Test results indicate:  Drag brake has substantial impact on drag: drag coefficient of ~0.5. This gives us significant control over max altitude.  Stability has been confirmed visually in flight tests as well as in wind tunnel analysis. 17

18.  Telemetry with electronics package  Telemetry with Rover 18

19. We have met all requirements set fourth. Our independent sections are the vehicle and the rover. They each have a parachute and GPS. We are using commercially available altimeters and motors. Recovery system can be armed on pad, from outside the airframe. Final recovery event at 800ft AGL 19