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University of Nebraska - Lincoln
Advisors
Team Overview
MissionDesign and build a launch vehicle to reach an altitude of
5,280-Feet AGLDeploy Scientific payload Recover all components in a reusable condition
Management
Team Leaders
Faculty AdvisorDr. Kevin Cole
NAR/TRA MentorThomas Kernes
Project DirectorMatthew Mahlin
Safety CoordinatorPaul Kubitschek
Outreach Coordinator
Bryan Kubitschek
Airframe TeamPaul Kubitschek Avionics Team Payload Team Propulsion Team
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Mission Profile
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Vehicle System Overview
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Vehicle Overview - Deimos
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: 98mm 37” long – rear retaining ring
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Assembly
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NoseconeCharacteristics
Von Kármán (LD-Haack)1:5 Fineness
CommunicationsBRB 900
900 MHz100 mW
Eagle Tree Systems2.4 GHz500 mW
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Sustainer AssemblyComponents
Avionics bay MountingSide Hatch
MaterialBlue TubeFiberglass (8oz)Glass Sock
DimensionsLength - 48 inAV bay length - 12in
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Avionics Components
Perfectflite StrattoLoggerFeatherweight Raven
Concept of OperationAccess from Side hatchActivated by external key switchesPrimary charge fired by both altimetersSecondary charge fires 5 seconds later by Raven
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Raven
StrattoLogger
LiPo
LiPo
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Wiring
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RecoveryComponents
MountingNosecone Tethered to SustainerSustainer Tethered to BoosterForged U-Bolts
Concept of OperationsDrogue @ ApogeeMain @ 1,000-Feet
Component Characteristic Dimension CommentMain Parachute 108” 18ft/s descent rate, 24” Spill hole
Drogue 36” 77ft/s descent rate, X-FormShock Cord 52’ and 30’ 1” Tubular Nylon
Nomex Wadding 24” Fireproof protection
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Booster AssemblyComponents
98mm MMT + Retaining RingFins x 3Coupler
MaterialBlue TubeFiberglass (8oz)Glass Sock
DimensionsLength 48 in
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FinsMaterial
5mm thick Tri-PlywoodFiberglass Vinyl Ester Resin
ConstructionLaser cuttingHand sandingVacuum Bagging
AssemblyMounting to MMTBond to boosterTip to tip
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Analysis Discussion
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Kinetic Energy - Recovery
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Event Section weight (lbf) Speed(ft/s) Energy (ft-lbf)
Apogee 1Nosecone + Sustainer 10.6 77.9 998.8
2 Booster 12.6 77.9 1187.3 3 UAV(Tethered) 9.5 77.9 895.2 Main 1000' 1 Nosecone 4 18 20.1 2 Sustainer 6.6 18 33.2 3 Booster 12.6 18 63.4 4 UAV(Released) 9.5 5 3.7
University of Nebraska - Lincoln
Stability Characteristics
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Altitude Prediction
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Altitude Prediction
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Wind speed (MPH) Predicted Altitude (Feet AGL)5 534010 533115 531420 5263
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Launch CharacteristicsCandidate Motor
Aerotech L1170FJ-P75mm motor
Simulation Parameters12 foot guide rail
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Drift Analysis
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DescentTime (s)Wind
Speed(MPH)(Ft/s)
Drift Distance(ft
(1000’ Deployment)108.1 0 0 0108.1 5 7.3 792.7108.1 10 14.6 1585.4108.1 15 22 2378.2
(500’ Deployment) 88.1 20 29.3 2584.2
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Drift Analysis
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Launch Vehicle Verification
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Subsystem Test Plan Verification Metric Status
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
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Test Flight Results
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Primary Flight Computer Data
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Secondary Flight Computer Data
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Test Flight Recovery
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Lessons Learned
Altitude ComparisonActual = 3341’Simulated = 3592’Actual is 7% less than Simulate
Drag Characteristics
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Scientific Payload Discussion
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Baseline payload design
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Payload
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University of Nebraska - Lincoln
Baseline payload design
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Subsystem Pre-Flight Test Plan Verification Metric Target 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 2012
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Interface with GCS
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Activity Plans
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University of Nebraska - Lincoln
Outreach• Upcoming
• Engineering Week 2012• Astronomy Day 2012
• Current Collaborations• Water Rocketry
• Demonstration• Construction• Launch
• Stomp Rockets
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University of Nebraska - Lincoln
Outreach
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Questions?
