Flight Readiness Review Presentation

1. Flight Readiness Review Presentation SLI Team Enloe Team Mentors: Mr. Bowen Mr. Adams, Mr. Honeycutt

2. Table of Contents • Presenters • Motor Selection • Rocket flight stability in static stability margin • Thrust to weight motor selection in flight simulation • Rail exit velocity • Parachute sizes and descent rates

3. Table of Contents, cont. • Test plans and procedures • Scale model flight test • Dual deployment avionics test • Ejection charge amount test • Payload integration feasibility • Final Rocket Flight • Summary of FRR • Changes made since CDR

4. Presenters • Vladimir Zilberter-Team Leader • Duncan Burrows • Titus John • Amit Raval

5. Motor Selection • We are using a K700W Aerotech • This motor takes our rocket to the proper altitude. Tested and confirmed • We have tested this on Rocksim and have launched our full scale rocket on March 6th

6. Rocket Flight Stability in Static Stability Margin

7. Rail Exit Velocity • Minimum speed for stable flight- 43.99 ft/s Rail exit velocity: 49.87ft/s

8. Main Parachute- Outer Diameter- 96 in. No spill hole Descent Rate- 19 ft/s Drogue Parachute Outer Diameter-30 in. Descent Rate- 99.3 ft/s Parachute Sizes and Descent Rates

9. We launched our rocket and the flight was a success The procedures for assembling the rocket have been documented The experiment equipment has been prepared by testing the knob on the variable capacitor. We will use the dual deployment test chamber to simulate the experiment in the classroom Test Plans and Procedures

10. Full Scale Flight Test • We launched our rocket on March 6th and it was a success. • The rocket’s altitude was 4757ft and the launch weight was 26.1lbs • This showed that all of our rocket components are working and the rocket is able to function in a fully executed environment

11. Full Scale Documentation

13. We used the simulated pressure change and tested the rocket’s dual deployment ejection charges. We inserted two charges for every separation for redundancy The picture below is the simulated change in air pressure. Dual Deployment Avionics Test

14. Ejection Charge Amount Test • We calculated the black powder amounts using various sources from the internet • Then we tested the ejection charges while doing the avionics test. • The final amounts are 3 and 4 grams for the main parachute • 2 and 3 grams for the drogue.

15. Payload Integration Feasibility • A variable capacitor and capacitance meter will allow us to learn of how air density affects capacitance. • An altimeter will provide us of a graph for the altitude of the rocket throughout its flight. With this, we will find a correlation between air density and capacitance. • We can test our experiment on the ground using our dual deployment test chamber.

16. Final Rocket Flight

17. Summary of FRR • Our engine is going to be a K700W • We are close to being completely ready for Huntsville • We tested our rocket on March 6th and it was a success

18. Changes Since CDR • Rail Buttons decreased in size from 1.5” to .75” • No spill hole in our main parachute • We will use 2 igniters per charge • We calculated and confirmed the charge masses 2 and 3 for the drogue, 3 and 4 for the main