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CFX-12 by Century Flight

CFX-12 by Century Flight. IF AT FIRST YOU DON’T SUCCEED, TRY AGAIN… AND AGAIN AND AGAIN AND AGAIN. FRR Presentation. Vehicle Dimensions. CFX-12 weighs approximately 830 oz. and has a total length of 110 in.

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CFX-12 by Century Flight

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  1. CFX-12by Century Flight IF AT FIRST YOU DON’T SUCCEED, TRY AGAIN… AND AGAIN AND AGAIN AND AGAIN FRR Presentation

  2. Vehicle Dimensions • 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.

  3. CFX-12’S Features • 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.

  4. Cesaroni L2375WT • CFX-12 Weight: 830 oz • Max Altitude: 5,570 ft • Max Velocity: 640 ft/sec

  5. CFX-12 Stability • Total length: 110in. • Center of Gravity: 58.1in • Center of Pressure: 77.12in. • Static Margin: 2.37

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

  7. Full Scale Flight Test Data 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.

  8. Predicted Altitude 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.

  9. Parachute Stats(*) Drogue Chute 54 inch PAR-54R Main Chute 96 inch PAR-96R

  10. Predicted Drift(*)

  11. Kinetic Energy(*)

  12. Recovery Tests & Procedures(*)

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

  14. Drag Brake Design and Dimensions The CFX-12's drag brake, is a retractable nose conethat will allow us to control our maximum altitude. 1 in stoppers at the base of the ogive.

  15. Rover Design and Dimensions • 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

  16. Rover Integration • 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

  17. Verification – Drag Brake 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.

  18. Interfaces With Ground Systems Telemetry with electronics package Telemetry with Rover

  19. Requirements Verification for Vehicle • 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

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