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UAA Rocketry

UAA Rocketry. PDR Presentation NASA Student Launch 2014-2015. Launch Vehicle. 1. Vehicle Dimensions. Overall Length 77.7 inches Body tube diameter 4 inches and 0.0625 inch thickness. 2. Vehicle Materials. 4 inch 5:1 VonKarmen Filament wound nose cone

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UAA Rocketry

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  1. UAA Rocketry PDR Presentation NASA Student Launch 2014-2015

  2. Launch Vehicle 1

  3. Vehicle Dimensions • Overall Length 77.7 inches • Body tube diameter 4 inches and 0.0625 inch thickness 2

  4. Vehicle Materials • 4 inch 5:1 VonKarmen Filament wound nose cone • Filament wound ProFusion body and coupler tubing 3

  5. Vehicle Materials • Fins and centering rings cut from 0.1875 inch structural fiberglass • Motor tube made from wound G12 fiberglass tubing • Bulkheads and payload compartment CNC cut from 0.125 inch structural fiberglass 4

  6. Vehicle Materials • ¼”-20 stainless steel full threaded rods • Grade-8 ¼ ”-20 Nylon-insert flanged locknuts • 0.25 inch foged steel Eyebolts 5

  7. Vehicle Materials • Epoxies • West System 105 Epoxy Resin • Henkel Loctite • JB Weld 6

  8. Vehicle Justifications • Conventional configuration: Nose cone/Payload Compartment, Central Section, and Booster Section • Aft Nose Cone/Payload section serves as payload ejection mechanism • Dual deployment; drogue and payload ejections simultaneous to simplify design 7

  9. Safety Testing Plans • AGSE components will be constructed with ample time left to thoroughly test system safety, effectiveness, and consistency • Extensive ground testing performed to ensure ejection charges perform deployment operations safely and consistently • Subscale and full-scale launch vehicles will be test launched early and often at Alaska Northstar (NAR) launch events 8

  10. Motor Selection Preliminary Motor Selection: Aero Tech J415W 54 mm Diameter 326 mm Length 9

  11. Justification for Selected Motor 10

  12. Stability Analysis • Center of Pressure: 59.28 inches from nose • Center of Gravity: 51.42 inches from nose • Static Stability Margin: 1.95 • Thrust-to-Weight Ratio: 5.5:1 • Rail Exit Velocity: 33.4 feet/second 11

  13. Test Plan Overview • AGSE components to be constructed and tested at UAA Design Studio • Ejection Charges to be tested outdoors adjacent to Design Studio • Subscale and full scale launch events at Lake Louise and Big Lake 12

  14. Launch Pad Drawing 13

  15. Launch Pad Discussion • Launch rail is 8020-1530 Aluminum extrusion 180 inches in length • Feet are adjustable to level the apparatus • Declination of launch rail is calibrated to 5 degrees from vertical • Blast pad safely deflects exhaust gases away from grass 14

  16. Motor Compartment Dimensions/Discussion • 54 millimeters in diameter and 13 inches in length to accommodate J sized motor • Motor compartment is G12 wound fiberglass made by ProLine Rocketry Inc. • Compartment is bonded to centering rings using JB Weld 15

  17. Drouge Parachute System Drawing 16

  18. Drogue Parachute Discussion • Located between booster and central sections • Parachute is a 2 foot Rocketman Parachute • Tethered to rocket with ¼” Aramid rope 17

  19. Deployment System Drawing 18

  20. Deployment System Discussion • Entire aft section will deploy simultaneously with main chute at 1000 feet AGL • Aft section will descend under a 3 foot Rocketman Parachute 19

  21. Payload Compartment Drawing 20

  22. Payload Compartment Discussion • Payload compartment is CNC cut from 0.125” structural fiberglass, bonded with West Systems Epoxy • Hatch is actuated by two servos at opposite ends of the compartment • Over-center geometry of hatch respective to servo motor prevents hatch from opening 21

  23. Main Parachute/Shock Cord Compartment Drawing 22

  24. Main Chute Discussion • The main chute will deploy at 1000 feet AGL • Chute is a 60 inch Iris Ultra Parachute made by Fruit Chutes • Parachute is sized to allow central and booster sections to descend with kinetic energy ≤ 75 ft-lbf • Chutes and rocket sections tethered with ¼ inch Aramid Rope 23

  25. Recovery System Drawing 24

  26. Recovery System Discussion • First ejection charge at apogee; booster section and central section separate to deploy drogue chute • Second and third ejection charges at 1000 feet AGL: • Aft nose cone/payload section descend separately • Central and booster sections descend under drogue chute and main chute 25

  27. Nose Cone Drawing/Discussion Image credit to performancehobbies.com [1] • 4 inch 5:1 Von Karmen Filament Wound Nose Cone • Connected to payload compartment 26

  28. Tail Fin Drawing/Discussion • Fins cut from 0.1875 inch structural fiberglass • Delta-style shape • Dimensions: • 12 inch root cord • 8 inch tip cord • 5 inch height • 2 inch sweep length 27

  29. AGSE Overview • Control • Spatial Constraints • Degrees of Freedom • Precision and accuracy • Components • Base Structure • Arm • End Effector 28

  30. Base Structure • Control Overview • Spatial Constraints • Retain rocket during payload insertion • fixed dimensional relationship • Precision and accuracy • Primary mounting point for the arm structure • Contains all electronics and power systems 29

  31. Arm • Control Overview • Spatial Constraints • Of sufficient height to remain clear of Launch Vehicle • 1 degrees of freedom • Boom: Rotation – Yaw • Precision and accuracy • Position switches/sensors 30

  32. Linear Motion System • Control • Spatial Constraints • Of sufficient length to clear the base station • Of sufficient length to reach the ground • 1 Degree of Freedom • LMS: Translation - Heave • Precision and accuracy • Ground sensing capability 31

  33. End Effector • Control • Spatial Constraints • Of sufficient width to capture a 6” area • Precision and accuracy • Closing pressure detection • Orientation of capture 32

  34. AGSE Integration and Testing • 3D component models • Assembly checks – QC • Iterative testing at subsystem and system levels • Sensor/program testing de-bugging 33

  35. References [1]https://www.performancehobbies.com/secure/store.aspx?groupid= 31820148555848 34

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