Design and Launch of a Balloon Re-Entry Vehicle for Near Space Experimentation

Transcription

1 Design and Launch of a Balloon Re-Entry Vehicle for Near Space Experimentation Mechanical Team: Michelle Wilson Nate Herrmann Caleb Barnes Electrical Team: Mark Falknor Adam Kelly Brent Guenther Advisors: Dr. Joseph Slater Dr. Mitch Wolff Steve Mascarella Dr. Ruby Mawasha Dr. John Wu

2 Update Outline Introduction/Background Design Criteria Payload System Improvements Release Mechanism Parachute Deployment Payload Geometry Launch Summaries Concluding Remarks 2

3 Background Purpose: Exploration and experimentation of near space for scientific and educational purposes Stable freefalling vehicle for use by ILC Dover in Rapid Eye Program Project Criteria Improve Launch Readiness: Balloon enclosure, Filling process, Connection integrity Cut-down mechanism Opens doors to industry collaboration: Cornerstone Research Group ILC Dover AFOSR/Sensors Directorate L Garde Boeing Air Force Materiel Command Shape for stable freefall Parachute deployment 3

4 Normal Configuration New Configuration 4

5 Balloon Enclosure Balloon Enclosure Enables easier, hands-free filling Enables launching in higher winds Allows more launches Protects balloon during launch delays Results More balloons have been sent up by the current team than any in the past Weather less of a factor 5

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7 Flow Meter Reading (L) Flow Meter FMA 1844 Omega flow meter with totalizer Poor factory calibration Recalibration curve determined Volume Prediction Flow Meter Original MATLAB program used an inaccurate free-lift value MATLAB program was rewritten using more accurate volume prediction methods Results Tested and verified at multiple launches Eliminated uncertainty in filling process Flow Meter Reading vs. Actual Volume y = x R² = Actual Volume Obtained (L) 7

8 Release Mechanism Release Mechanism Primary release: servo Back-up release: nichrome wire Servo and nichrome release activated remotely by user command Both systems tested in a vacuum chamber and on dry ice Servo mechanism has been successfully flight tested Backup release: nichrome wire Primary release: servo 8

9 Payload Rigging Upgrade Components individually strength tested in lab Springs integrated to slow the rate of loading Tangling issues Swivels Spreader ring Launch simulation Weight 9

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11 Parachute Deployment Design Specifications Light weight Powerful Reliable in -50 C and 6.7kpa pressure Redundancy Payload compatible Design Inspiration High powered model rocketry Current Deployment Tube 3 diameter cardboard tube 3/8 thick plywood plug Male and Female PVC fixtures Aluminum U-bolt and nuts 11

12 Parachute Testing Ground tests All successfully deployed the parachute Vacuum Testing - Containment Methods PVC fixture with epoxy containment Latex surgical tubing FFFG ground to fine powder Custom machine aluminum canister with electrical tape containment 1.75 grams FFFG powder Conclusions from Vacuum Tests Slower burn rate Lack of air as heat transfer medium Expanding gases cool Self extinguishing effect Containment is the key 12

13 Payload Design Design Specifications Aerodynamically stable during freefall Low terminal velocity Light weight Design Inspiration Nose cones Missiles Tension cones NASA reentry vehicles Our Reentry Vehicle Hemisphere base Conic tail Effects of tail angle investigated 13

14 CFD Analysis for Payload Design Modeling 15, 25, and 35 half-angle Flow velocity: 55.8 m/s Velocity inlet (55.8 m/s) Pressure outlet (6910 Pa) Air properties at 60k ft Inviscid flow Tests Pressure drag Turbulent wake Stability 14

15 CFD Analysis - Wake 15 angle 25 angle 35 angle 15

16 CFD Analysis Drag 15 angle 21.6 N drag force 43.8 mph 25 angle N drag force 36.3 mph 35 angle 68.1 N drag force mph 16

17 Launch 1: Summary Goals Test balloon enclosure Flow meter Results Successes Balloon Enclosure worked Payload was recovered Complications Under-filled balloon Winds shifted South Balloon filling reinvestigated Release Mechanism became a priority 17

18 Launch 2: Summary Goals Test both release mechanisms Monitor temperatures in payload Results Complications Trusted rigging components failed Tracking equipment failure Payload recovered after a month What was learned Release mechanism worked Payload rigging reconsidered 18

19 Launch 3: Summary Goals Test servo release mechanism again Test parachute deployment system Test rip and go launching system Results Successes Servo released First rip and go launch a success Onboard video obtained Payloads recovered 20 miles west of Marysville, OH Complications Parachute did not deploy Release line tied a magic knot What was learned Thermal issues need to be addressed 19

20 Overall launch readiness Team Contributions Recalibrated flow meter & volume prediction Rip and go launch system Payload rigging upgraded Launch simulation More launches Payload additions Release system Parachute deployment New payload shape Improved payload capabilities 20

21 Future Work Build a working prototype of new payload system More stability analysis / testing Implement payload components into vehicle geometry Fall tested Launch freefall payload 21

22 Gantt Chart 22

23 Budget Project Expenses Flow Meter & Calibration $1, Balloon Enclosure $ Release Mechanisms $ Parachute Deployment $ Payload Design $ Total Launch Expenses $2, Miscellaneous Project Expenses $ Total $4,

24 Thank You for Your Attention Questions/Comments? 24

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