1. UAA Rocketry Critical Design Review Presentation

2. Final Rocket Dimensions Overall Length: 77.7 inches Body Tube Diameter: 4 inches Weight Before Burn: 16.4 lbs Weight After Burn: 15.5 lbs 2

3. Final AGSE Dimensions 3

4. Important Design Features ●Linear Motion System o Stepper motor mounting solutions o Belt drive system o Ball nut/threaded rod interface to actuate linear motion ●Rotation o Stepper motor mounting solutions o 2:1 gearing ratio - 25 steps = 90 degrees o Allows convenient access to components 4

5. Important Design Features ●End Effector o Wide range of motion o Simplicity; one degree of freedom actuation o Robustness of design o Accommodates payload misplacement/misalignment ●Electronics Housing & Rocket Cradle o Storage for microcontroller, power supply, and other sensitive components o Convenient mounting solution for indicators/switches o Ensures repeatable alignment of AGSE elements 5

6. Final Motor Decision Aerotech J800T ●Propellant weight: 595 grams ●Total weight: 1134 grams ●Average thrust: 790 Newtons ●Peak thrust: 1256 Newtons ●Total impulse: 1265 Newton seconds 6

7. Final Motor Verification 7

8. Rocket Flight Stability in Static Margin Diagram Center of Pressure: 51.42 inches from nose Center of Gravity: 59.275 inches from nose Static Stability Margin: SSM = (CG-CP)/OD = (59.275-51.42)/4 SSM = 1.95 8

9. Other Flight & Stability Metrics ● Thrust-to-Weight Ratio: 9.2:1 ● Rail Exit Velocity: 86.4 feet/second o Based on 96 inch rail length ● Maximum Velocity: 494 feet/second ● Maximum Mach Number: 0.44 ● Maximum Acceleration: 484 feet/second^2 ● Apogee: 3206 feet o Allows for 23 oz. mass growth ● Stable Velocity: 43.9 feet/second ● Distance to Stable Velocity: 1.8 feet 9

10. Mass Statement/Mass Margin Final motor selection allows for 23 oz mass growth, or +10% current mass. After final assembly, mass will be added to target 3,000 foot apogee goal. SectionMass (oz) Nose/Payload62.09 Central470.76 Booster86.08 Total226.43 10

11. Parachute Sizes and Descent Rates and Kinetic Energy Main Parachute: Fruity Chutes 60 inch Iris Ultra Drogue Parachute: Fruity Chutes 24 inch Elliptical Nosecone/Payload Parachute: Rocketman 36 inch 11

12. Recovery Harness ●⅜ inch Aramid rope ●Load limit 1480 lb ●Length: ○10 ft between forward section and main parachute ○30 ft between aft section and forward section 12

13. Predicted Drift Wind Speed (mph) Rocket Drift (ft) Payload Drift (ft) 000 5512399 101024798 1515351197 2020471596 13

14. Test Plans and Procedures ●System integration plan ●Component testing o Utilize FEA stress analysis of machine components ●Static and functional testing ●Use accelerometer flight data to verify the efficacy of our designs ●Test procedures o Safety o Checklists o Regimented testing schedule 14

15. Scale Model Flight Test ●Gained experience & expertise in: o Simulation accuracy o Accelerometer data recover and analysis o Parachute & harness packing o Launch procedures o Building methods 15

16. Staged Recovery System Tests ●Tested in flight configuration ●Charges sized: dependent on section volume ●Ensure separation: o Sub-scale: ensures coupler fits are not too tight o Full-scale: ensure shear pins fracture 16

17. Final AGSE Design Overview ●Subsystems: o Base Plate: platform for rigid attachment of components o Cradle: ensures rocket is placed within operating limits, enhances reliability, aids interfacing between AGSE and rocket. o Electronics compartment: weather-proof, allows for convenient access to microcontroller, power supply, switches and indicator lights 17

18. AGSE/Payload Integration ●Return to home position ●LMS system lowers end effector ●Servos actuate to close the end effector around the payload ●LMS raises the end effector to maximum height ●Stepper motor actuates rotation ●LMS lowers the payload into the payload bay ●Servos actuate to open the end effector, releasing the payload ●LMS raises the end effector to maximum height ●Servos on the payload hatch actuate to close the hatch ●Return to home position 18

19. Requirement Completion Status ●Mission success criteria: o Contain and ingress payload o Achieve desired apogee o Successful parachute and payload deployment o Achieve all criteria while adhering to competition rules, regulating authorities, and pre-determined safety practices (set forth in RFP and PDR) ●Methods of verification o CAD modeling o Ground testing o Field testing 19

20. Thank You! Questions? For more information: https://www.facebook.com/uaarocketry http://www.uaarocketry.com/