CFX-12 by Century Flight

FRR Presentation

IF AT FIRST YOU DON’T SUCCEED, TRY AGAIN…AND AGAIN AND AGAIN AND AGAIN

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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.

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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 BrakeThe 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 SystemBased on two deployments, one at apogee, one at 800ft.

• RoverThe 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.

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Cesaroni L2375WT

• CFX-12 Weight: 830 oz

• Max Altitude: 5,570 ft

• Max Velocity: 640 ft/sec

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CFX-12 Stability• Total length: 110in.

• Center of Gravity: 58.1in

• Center of Pressure: 77.12in.

• Static Margin: 2.37

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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

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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.

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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.

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Parachute Stats(*)Drogue Chute

54 inch PAR-54R

Main Chute

96 inch PAR-96R Parachute Selection

Type Size Result

Main Parachute Ultra Iris 144 144 1.9 Oz. Ripstop18 Sides

33 inch Spill Hole

Deploymentat

800 Feet

Drogue Parachute PAR- 36R 36 Inch Nylon8 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 %17.65 1500

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Predicted Drift(*)Wind Speed(MPH) Drift Prediction(Feet)

Rover / Vehicle

5 MPH 404 774

10 MPH 692 1284

15 MPH 903.5 1672

20 MPH 1142 2032

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Kinetic Energy(*)Altitude(Feet) Time(Seconds) Kinetic Energy(Ft*Lbf)

Rover/Vehicle

790 2.2 322.231 (Max)

Apogee 18.37 0 (Min)

801 68.10 1357 5583

200 106.42 74.49 74.29

Touch Down 122.01 74.49 74.29

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Recovery Tests & Procedures(*)

#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 controlbased 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

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Tests Plans and ProceduresTests wind tunnel full scale launch ejection

Procedures launch recovery motor/ igniter

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Drag Brake Design and Dimensions

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.

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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

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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

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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.

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Interfaces With Ground Systems

Telemetry with electronics package Telemetry with Rover

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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