1 / 14

UF Hybrid Rocket Team’s Mile High Club

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

griffith-parry
Télécharger la présentation

UF Hybrid Rocket Team’s Mile High Club

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. UF Hybrid Rocket Team’s Mile High Club Brought to you by Chris Leonard, Ty Morton, Sam Darr, and Josh Childs

  2. Full Scale Test Rocket Thrust to weight ratio: 41.52

  3. 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

  4. 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

  5. Full Scale Flight Test (PerfectFlite)

  6. Full Scale Flight Test (Raven)

  7. Miscellaneous Flight Data • Rail Exit Velocity: 110 ft/sec • Parachute Size: 60 inches • Parachute Deployment Altitude: 600 feet • Descent Rate: 13 ft/s

  8. Miscellaneous Flight Data (Raven)

  9. Miscellaneous Flight Data (Raven)

  10. Manufacturer Thrust Data Average Motor Thrust: 1300 Newtons

  11. 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

  12. 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

  13. Ejection tests

  14. Payload Integration • Strain gage testing- test the strain gauges and data loggers with simulated loads. • Payload integration:

More Related