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 o West System 105 Epoxy Resin o Henkel Loctite o 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: o Aft nose cone/payload section descend separately o 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: o 12 inch root cord o 8 inch tip cord o 5 inch height o 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