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UAA Rocketry Critical Design Review Presentation

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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

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Final AGSE Dimensions 3

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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

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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

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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

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Final Motor Verification 7

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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

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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

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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

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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

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Recovery Harness 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

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

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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

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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

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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

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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

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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

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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

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