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UF Hybrid Rocket Team’s Mile High Club. Brought to you by Chris Leonard, Ty Morton, Sam Darr , and Josh Childs. Full Scale Test Rocket. Thrust to weight ratio: 41.52. Vehicle Design Changes. Length increased by 12 inches to make overall length 68 inches - PowerPoint PPT Presentation
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UF Hybrid Rocket Team’s Mile High Club
Brought to you byChris Leonard, Ty Morton, Sam Darr, and Josh Childs
Full Scale Test Rocket
Thrust to weight ratio: 41.52
Vehicle Design Changes
• Length increased by 12 inches to make overall length 68 inches
• Four body tubes will be used instead of the original three
• The bulkheads will be decreased in length to 0.5 inches to decrease weight
• The nose cone is hollowed out to provide room for the main ejection charge
Future Tests and Construction
• Rebuild motor segment– Fins will be identical to those lost– Segment length will be increased by 1 inch
• Construct a new launch rail out of 80-20 aluminum, maintaining 7 foot rail height– New rail will be more stable and easier to use– Previous launch tower failed for various reasons
Full Scale Flight Test (PerfectFlite)
Full Scale Flight Test (Raven)
Miscellaneous Flight Data
• Rail Exit Velocity: 110 ft/sec• Parachute Size: 60 inches• Parachute Deployment Altitude: 600 feet• Descent Rate: 13 ft/s
Miscellaneous Flight Data (Raven)
Miscellaneous Flight Data (Raven)
Manufacturer Thrust Data
Average Motor Thrust: 1300 Newtons
Dual Deployment Test
•Charges are located in each red square•The charge in the motor section blew at apogee but was too powerful, shearing shock cord•Charge in the nose cone blew once rocket had descended to 600 ft, successfully slowed rocket to safe descent speed
Recovery Materials Used• 20 ft of elastic shock chord (10 in
both sections)• One 60in X-form Parachute• Green Fiber blow-in natural fiber
insulation
•Dry cleaner hangers•Pyrodex powder•E-matches•Paper towel•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
Payload Integration
Strain gage testing- test the strain gauges and data loggers with simulated loads.
Payload integration: