UF Hybrid Rocket Teams Mile High Club Brought to you by Chris Leonard, Ty Morton, Alex Aueron, Sam Darr, and Josh Childs.

UF Hybrid Rocket Team’s Mile High Club

Brought to you byChris Leonard, Ty Morton, Alex Aueron, Sam Darr, and Josh Childs

Thrust to weight ratio: 41.52

Motor Selection

• Downsized motor from J1999 to J1299– Roughly 2:3 scale size and thrust

• Aerotech J1299– 850.16 Ns total impulse– 0.68 s burn time– 1253.93 N average thrust

Motor Justification

• Flight simulations with J1999 overshot 1 mile• Less thrust with J1299 decreased altitude• J1299 still has short burn time– Limits affect on scientific payload– Fast acceleration to maximize compressive forces

Vehicle Design Changes

• Length decreased by 0.5 inches• Fin size increased– Increases drag force to assist altitude reduction– Root chord length moved from 10 to 12 inches

• Extra space in lower body section– Smaller motor has shorter casing– More room for ejection charge– Potential space for excess electronics

0 10 20 30 40 50 60 70 80 90 1000

1000

2000

3000

4000

5000

6000

Altitude

Time

Altit

ude

(feet

)

0 10 20 30 40 50 60 70 80 90 100

-400

-200

0

200

400

600

800

1000

Velocity

Time

Velo

city

(ft/s

ec)Max Altitude: 5302 feet

Max Velocity: 903 ft/secVelocity at Rail : 110 ft/sec

0 10 20 30 40 50 60 70 80 90 1000

100200300400500600700800900

Drag Force

Time

Drag

For

ce (N

ewto

ns)

Max drag force: 119 Newtons

Average Motor Thrust: 1300 Newtons

Recovery System Design• Rocket is made of 3 concentric tubes:1) Nose2) Payload3) Booster

System Deployment

•Two charges are located in each red square•In the booster activate at apogee•Charges in the nose activate once rocket has descended to 700 ft.

Materials Used• 20 ft of elastic shock chord (10 in

both sections)• One 36in X-form Parachute• Green Fiber blow-in natural fiber

insulation (dog barf)

•Dry cleaner hangers•Pyrodex powder•Este’s and Copperhead igniters•Paper tower•Tape•Hot glue

Ejection testsTest Number Specs Results Comments

1 1.5 inch length hanger tube, Copper head igniter

Successful: exploded from both ends

Initial test to check if ejection charge design was viable

2 1.5 inch “split-end” tube, 1.1 gram pyrodex charge, Este’s igniter

Successful: top of test section blown, weight launched into the air

First test using test chamber

3 1.5 inch hanger tube, 1.2 gram pyrodex charge, copper head igniter

Successful: top of test section blown, weight launched into the air

Conducted in test chamber, more energetic than test 2

4 2 inch hanger tube, 1.7 gram pyrodex, copper head igniter, Kevlar run through test chamber

Successful: top of test section blown, weight launched into the air, Kevlar chord intact

Conducted in test chamber, Kevlar is viable for use as parachute chord

5 1.5 inch hanger tube, 1.4 gram pyrodex charge, Este’s igniter, conducted in booster tube of scale rocket, “dog barf” insulation

Charge was far too powerful for the tube, kicked out the top of the motor, insulation confirmed to work

Amount of powder used was based on tests for the full scale rocket: scale rocket diameter of 38mm, full scale diameter is 54mm

Charge Schematic

1. Hot glue2. Pyrodex powder3. Igniter4. Paper tower5. Tape

Scale Launch Test

3:4 scale of competition rocket. Used F-50 Aerotech motor. Carried Raven Altimeter connected to two

ejection charges. Carried additional back up ejection

charge connected to motor. Successful test, both charges were

deployed.

Future Tests

Strain gage testing- test the strain gages and data loggers with simulated loads.

Payload integration testing:

Payload Schematic

TEST LAUNCH VIDEO