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Advisors Mission Design and build a launch vehicle to reach an altitude of 5,280-Feet AGL Deploy Scientific payload Recover all components in a reusable.

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Presentation on theme: "Advisors Mission Design and build a launch vehicle to reach an altitude of 5,280-Feet AGL Deploy Scientific payload Recover all components in a reusable."— Presentation transcript:

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2 Advisors Mission Design and build a launch vehicle to reach an altitude of 5,280-Feet AGL Deploy Scientific payload Recover all components in a reusable condition Management Team Leaders Faculty Advisor Dr. Kevin Cole NAR/TRA Mentor Thomas Kernes Project Director Matthew Mahlin Safety Coordinator Paul Kubitschek Outreach Coordinator Bryan Kubitschek Airframe Team Paul Kubitschek Avionics TeamPayload TeamPropulsion Team 2 University of Nebraska - Lincoln

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5 Length:124.5” Diameter:5.5” Nose Cone:27.5”Von Kármán (LD-Haack), 1:5 Fineness Fin Span:14.5”(3-fin configuration) Weight:23.7lbs(No Motor – No Payload – Estimated) Motor Mount:98mm37” long – rear retaining ring 5 University of Nebraska - Lincoln

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7 Characteristics Von Kármán (LD-Haack) 1:5 Fineness Communications BRB MHz 100 mW Eagle Tree Systems 2.4 GHz 500 mW 7 University of Nebraska - Lincoln

8 Components Avionics bay Mounting Side Hatch Material Blue Tube Fiberglass (8oz) Glass Sock Dimensions Length - 48 in AV bay length - 12in 8 University of Nebraska - Lincoln

9 Components Perfectflite StrattoLogger Featherweight Raven Concept of Operation Access from Side hatch Activated by external key switches Primary charge fired by both altimeters Secondary charge fires 5 seconds later by Raven 9 University of Nebraska - Lincoln Raven StrattoLogger LiPo

10 10 University of Nebraska - Lincoln

11 Components Mounting Nosecone Tethered to Sustainer Sustainer Tethered to Booster Forged U-Bolts Concept of Operations Apogee 1,000-Feet ComponentCharacteristic DimensionComment Main Parachute108”18ft/s descent rate, 24” Spill hole Drogue36”77ft/s descent rate, X-Form Shock Cord52’ and 30’1” Tubular Nylon Nomex Wadding24”Fireproof protection 11 University of Nebraska - Lincoln

12 Components 98mm MMT + Retaining Ring Fins x 3 Coupler Material Blue Tube Fiberglass (8oz) Glass Sock Dimensions Length 48 in 12 University of Nebraska - Lincoln

13 Material 5mm thick Tri-Plywood Fiberglass Vinyl Ester Resin Construction Laser cutting Hand sanding Vacuum Bagging Assembly Mounting to MMT Bond to booster Tip to tip 13 University of Nebraska - Lincoln

14 14 University of Nebraska - Lincoln

15 15 University of Nebraska - Lincoln EventSection weight (lbf)Speed(ft/s)Energy (ft-lbf) Apogee1 Nosecone + Sustainer Booster UAV(Tethered) Main 1000'1Nosecone Sustainer Booster UAV(Released)

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17 17 University of Nebraska - Lincoln

18 18 University of Nebraska - Lincoln Wind speed (MPH)Predicted Altitude (Feet AGL)

19 Candidate Motor Aerotech L1170FJ-P 75mm motor Simulation Parameters 12 foot guide rail 19 University of Nebraska - Lincoln

20 20 University of Nebraska - Lincoln DescentTime (s) Wind Speed(MPH) (Ft/s ) Drift Distance(ft (1000’ Deployment) (500’ Deployment)

21 21 University of Nebraska - Lincoln

22 22 University of Nebraska - Lincoln Subsystem Test PlanVerification MetricStatus Altimeter Accuracy -Subscale Test flights-Agreement between altimeters Completed March Recovery System Deployment -Ground Simulation -Test flights -Components ejected forcefully -Visually confirm deployment -Vehicle recovered intact -Completed February - Completed March Tracking Equipment -Ground distance test -Test flights -Line of sight transmission at least 1 mile -Successful tracking after launch -Completed March 1.5 mile range -Completed March Motor integration -Test fit -Fit adapter if needed -No shifting of motor -Motor housed internally Completed February Altitude -Full scale test flight for both candidate motors -Add ballast as needed -Compare recorded altitudes with that of simulations Completed March: 7% difference

23 23 University of Nebraska - Lincoln

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25 25 University of Nebraska - Lincoln

26 26 University of Nebraska - Lincoln

27 Altitude Comparison Actual = 3341’ Simulated = 3592’ Actual is 7% less than Simulate Drag Characteristics 27 University of Nebraska - Lincoln

28 28 University of Nebraska - Lincoln

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30 30 University of Nebraska - Lincoln

31 31 University of Nebraska - Lincoln

32 Subsystem Pre-Flight Test PlanVerification MetricTarget Date Payload Airframe Drop test Visually verify wind deployment February 2012 Primary and secondary windbelt systems Detect induced voltage in coils Airspeed/resonance relationship Voltage detected in coil > 30mV and exhibits period structure (not noise) December 2011 Active windbelt tension control system Interface micro with servo/belt Interface micro with anemometer Frequency of voltage waveform = expected frequency for known wind speed January 2012 Sensors and transmitter Compare sensor data to know values Transmit data Sensor output values (received data ) w/in 1% of known values (transmitted data) January 2012 Power conversion system Input several AC waveforms and verify DC conversion/smoothing via scope Measure via micro and compare to scope value Visually verify smoothed DC waveform/micro measurement w/in 1% of scope measurement February

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35 Upcoming Engineering Week 2012 Astronomy Day 2012 Current Collaborations Water Rocketry Demonstration Construction Launch Stomp Rockets 35 University of Nebraska - Lincoln

36 36 University of Nebraska - Lincoln

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