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Sound Test

Sound Test. Testing and Integration of a Rocket-Launched Video Imaging Platform. IniTech Engineering. Apoorva Bhopale Susan Schmidt Rob Wingo Brian Love. 1 May 2002. Project Background. Project is sponsored by Applied Research Labs Main Objective:

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Sound Test

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  1. Sound Test

  2. Testing and Integration of a Rocket-Launched Video Imaging Platform IniTech Engineering Apoorva Bhopale Susan Schmidt Rob Wingo Brian Love 1 May 2002

  3. Project Background • Project is sponsored by Applied Research Labs • Main Objective: • Prove the validity of a rocket launched balloon as a telecommunications platform • Possible uses, disaster relief, drug interdiction, inexpensive “throwaway” satellites • Rocket is to be launched this summer

  4. Overview of the Presentation • Goals to accomplish • Description of each goal • Work completed for each goal • Future work • Questions

  5. Semester Goals • Design and build payload canister with mountings for electronics • Size and build drogue chute • Test balloon buoyancy • Test Electronics • Test balloon deployment

  6. Flight Profile

  7. Chute Sizing Brian Love

  8. Drogue Chute • Required to deploy balloon after ejection • Will be used to slow descent after operations

  9. Previous work concluded that a small chute will deploy the balloon Limiting factors for design are descent constraints Considerations Weight of payload Altitude Allowable impact velocity Sizing

  10. D = drag force W = weight ρ = air density Cd = coefficient of drag A = area Vt = terminal velocity r = chute radius d = chute diameter m = mass g = gravitational acceleration Algorithm

  11. Calculations Standard Atmosphere

  12. Chute Design 108” 116” Weight: 14.2 oz.

  13. Balloon Tilt • Weight drop of 11 oz. from 25 to 14 oz. • Balloon used was ~1/4 scale

  14. Neutral Buoyancy

  15. Calculations Need mass air inside balloon 4kg less than the STP value for neutral buoyancy

  16. Temperature Difference

  17. Considerations • Absorbed solar energy • Air circulation inside balloon • Descent rate of inflated balloon vs. chute • Thermal updrafts • Need experimental data to prove theoretical • Testing difficult on ground

  18. Payload Canister Susan Schmidt

  19. Initial Avionics CanisterDesign Canister made of 4.25 inch PVC pipe Covered in carbon fiber Electronic components secured with bubble wrap Plexiglas bottom for camera

  20. Previous Canister Design Changes • Components hit canister walls and each other • Bubble wrap was not sufficient vibration control • Foam was then used to secure items

  21. Issues with Past Designs • Carbon fiber blocks radio waves • Electrical components not secure • Plexiglas fogs at higher altitude • Plexiglas cracks easily • Component constraints cannot handle temperatures of high altitudes

  22. Requirements for the Avionics Canister Structural integrity Limit component vibration Airtight seal Temperature control

  23. Structural IntegrityExternal Material Options • Metals • Possible Shrapnel • Weight • Porous materials, i.e. wood • Airtight seal • Plexiglas • Cracks easily • Lexan • High cost • Availability And the winner is…

  24. PVC • Weather Resistant • High strength to weight ratio • Corrosion Resistant • Good thermal insulator • Self-extinguishing • Low cost!!

  25. High impact resistance Used to stabilize internal components Used for the camera viewing area Internal Structure

  26. Limit Component Vibration • Two 0.09” thick Lexan perpendicular boards • Secured components with nuts and bolts • Ends capped with hobby plywood

  27. Airtight Seal • Change in pressure from sea level to higher altitudes cause fogging on the Lexan • Seal end of canister with Teflon Tape • Teflon tape for extruding connections • Pump in Nitrogen through a gas fitting • Inert gas replaces the water vapor

  28. Temperature Control • Camera’s operating range: -1.1°C to 37.77°C • Above 8,000 feet the temperature drops below this operating range • The rocket test in summer will not reach this altitude • The temperature limits of the components must be evaluated for higher flights

  29. Electronics Rob Wingo

  30. Electronic Components • Accelerometer board • GPS/Video Overlay board • GPS receiver • Video camera • Telemetry system • Batteries

  31. Semester Objectives • Connect all of components and make work • Range test telemetry system • Find problem with power source • Determine how to use accelerometer board as an event trigger • Mount electronics in canister

  32. Component Connectivity • Successfully connected all components

  33. Range Test: First try • Unsuccessful • Assumed power problem

  34. Range Test: Second try • Made adjustments to power supply and connectivity board • Still unsuccessful

  35. Range Test: Third try • Re-soldered connectivity board • Still unsuccessful • Contacted transmitter manufacturer • Discovered range can be drastically reduced by ground effects

  36. Ground Effect Problem • Transmitter designed for aerial use only • Will not be able to accomplish range test on ground

  37. Balloon Deployment Apoorva Bhopale

  38. Balloon Deployment • Objectives • Determine a method to pack the balloon • Determine an adequate amount of black powder to eject the canister

  39. Balloon Size

  40. Suggested Method

  41. Pyrotechnic Ejection • Advantages • Reliable • Lightweight • Used extensively

  42. Possible Failure Modes of the Ejection • Too Little Black Powder • Does not clear ejection tube • Inhibits the rockets main chute deployment • Payload crashes with the rocket • Too much Black Powder • Rocket tube explodes • Drogue chute rips from balloon • Burnt drogue chute or balloon

  43. Theory of Pyrotechnic Ejection • Wp =Weight of Black Powder (lbs) • dP = Ejection Charge Pressure in Psi • V = Free volume in cubic inches • R = Combustion gas constant 22.16 ft- lbf/lbm-R • T = Combustion gas temperature, 3307 degrees R

  44. Test Footage

  45. Conclusions From Test • Place Canister closest to the ejection charge • Use 7 grams of Black Powder

  46. Conclusion • Design and build payload canister with mountings for electronics • Size and build drogue chute • Test balloon buoyancy • Test Electronics • Test balloon deployment

  47. Future Work • Verify range of the transmitter another way • Possibly send it back to manufacturer • Test the deployment method in a rocket • Determine a way to sever connection between balloon and canister • Neutral Buoyancy test • Setup accelerometer board to be used as event trigger

  48. Dr. Ronald Stearman Dr. Martin Barlett Dr. Jennifer Lehman Danny Linehan Daniel Parcher Rick VanVoorhis Lixin Gong Acknowledgements

  49. Questions

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