DSUAVE

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D-SUAVE

• Deployable Small UAV Explorer

University of Colorado at Boulder
D S U A V E
Interim Review 1 Spring 2007
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Meet the Team
Burhan Muzaffar..Project
Manager Miranda MeslohAssistant Project
Manager Nathan Sheiko...Systems
Engineer David Goluskin.Fabrication
Engineer Jastesh Sud..CFO Yoshi
Hasegawa........Safety Engineer Brandon
Bobian.Electronics/Webmaster Michael
Lapp..Vehicle Design Lead
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Overview

• Changes in Design RFA
• Design Summary
• Test Plan
• Current Issues
• Schedule Progress
• Budget Progress

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RFAWing Deployment Spring Length
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RFAWing Deployment Spring Length
Deflection
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RFAWing Deployment Spring Length
Force applied to Piece 3 when Piece 2 hits Piece3
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RFAWing Deployment Spring Length

• Shear stress analysis

Shear stress (MPa)
Epoxy (Shear stress is13.8MPa) - connects
backbone and pieces. Assume that epoxy can
connects backbone and pieces perfectly.
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Design Changes

• Wing deployment mechanism
• Spring in compression when maximally extended
• Triggered by onboard servo
• Vehicle deployment mechanism
• Triggered by onboard servo
• Two vehicle connection points
• Protective tube eliminated

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Design Changes

• Vehicle and wing deployment

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ElectronicsChanges Since CDR

• FM instead of PCM RC receiver
• Futaba R168DF 8-Channel FM DC 75MHz
• Release servo
• One servo to release vehicle and deploy wings
• Changes to Onboard Software
• Deploy vehicle with an RC command

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Subsystem TestsW-01 Wing Structural Test

• Requirements
• Wingtip deflection less than 5 wingspan under
  worst case (2.5g)
• Verification Tests
• Measure tip deflection of loaded spar-only and
  complete wing
• Needed for Test
• Half-Wing
• Measurement Grid and Camera
• Clamp Capable of 25N Force
• 50-gram Masses (10)

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Subsystem TestsWD-01 Wing Deployment Timing and
Locking

• Requirements
• Wing deployment time lt0.4s
• Correct operation of locking mechanism
• Verification Test
• Wing deployment under flight conditions (12m/s)
• Wing remains fully locked after deployment
• Video recording of test to verify timing
• Needed for Test
• Complete swing mechanism mounted on backbone
• Truck with an open bed
• Video camera
• Test location (N. 55th St.)

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Subsystem TestsWD-02 Release Servo Timing

• Requirements
• Time between vehicle release and wing deployment
  lt0.3s
• Verification Test
• Initiate release sequence to time the servo
• Video recording of test to verify timing
• Needed for Test
• Complete release mechanism and the swing
  mechanism mounted on backbone
• Video camera

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Subsystem TestsE-01 Electronics Range Test

• Requirements
• Communications range must be gt1km
• Correct control surface and throttle operation
  at max range
• Ground station reception of velocity at max
  range
• Verification Test
• Determine maximum range at which communication
  work correctly
• Needed for Test
• Complete electronics package
• Ground station
• Test location with range gt1km (N. 55th St.)

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Subsystem TestsP-01 Propulsion Thrust and
EfficiencyP-02 Battery Capacity
P-01
P-02

• Requirements
• Battery capacity gt1280mAh
• Run time gt27.5min
• Verification Test
• Determine the actual battery capacity
• Determine the run time at cruise power
• Needed for Test
• Complete propulsion subsystem
• RC wattmeter
• Wood dowel to mount motor

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Subsystem Tests RM-01 Release Mechanism Test

• Requirements
• Uninhibited vehicle release
• Aircraft maintains correct orientation
• Verification Test
• Drop the aircraft from the release mechanism to
  verify correct operation
• Needed for Test
• Complete release mechanism and swing mechanism
  mounted to the backbone
• Release test apparatus
• String
• Video camera
• Test location (N. 55th St.)

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Subsystem Tests DP-01 Deployment Apparatus Test

• Requirements
• Pole must be structurally sound at release speed
  (12m/s)
• Pole must not vibrate
• Verification Test
• Video record the pole at 12m/s to verify
  structural integrity
• Needed for Test
• Complete deployment pole
• Truck with an open bed
• Video camera
• Test location (N. 55th St.)

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System TestsDS-01 Complete System Mass

• Requirements
• Complete aircraft and release mechanism mass
  lt750g
• Complete aircraft mass lt650g
• Verification Test
• Weigh complete aircraft and release mechanism
  separately
• Needed for Test
• Complete aircraft and release mechanism
• Digital Scale

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System TestsDS-02 Preliminary Flight Test

• Requirements
• Stable Controllable
• Verification Test
• Hand-launched powered flight to verify flying
  qualities
• Record test with video camera for later analysis
• Needed for Test
• Complete aircraft
• Incidence Meter and Protractor
• RC test pilot (James Mack)
• Video camera
• Boulder RC Airfield

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System TestsDS-03 Velocity and Turn Radius
VerificationDS-04 Endurance Verification
DS-03
DS-04

• Requirements
• Aircraft capable of flight for 25min at 12m/s
• Verification Test
• Flight test
• Ground station display of velocity
• Time endurance
• Needed for Test
• Complete aircraft
• Ground Station
• Stop watch
• RC test pilot (James Mack)
• Boulder RC Airfield

• Requirements
• Aircraft capable of 12m/s
• Turn radius lt50m
• Verification Test
• Short flight test
• Ground station display of velocity
• Markers on ground to verify turn radius
• Needed for Test
• Complete aircraft
• Ground Station
• RC test pilot (James Mack)
• Boulder RC Airfield

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System TestsDS-05 Preliminary Deployment
TestDS-06 Final Deployment Test
DS-05
DS-06

• Requirements
• Uninhibited vehicle release
• Wing Deployment
• Initiate transition to stable flight
• Verification Test
• Vehicle deployment test with safety tether
• Identify any problems with deployment
• Needed for Test
• Complete aircraft and deployment pole
• Truck with an open bed
• RC test pilot (James Mack)
• Test location (N. 55th St.)

• Requirements
• Uninhibited vehicle release
• Wing Deployment
• Transition to stable flight
• Verification Test
• Vehicle deployment test without safety tether
• Verify transition to stable flight
• Needed for Test
• Complete aircraft and deployment pole
• Truck with an open bed
• RC test pilot (James Mack)
• Test location (N. 55th St.)

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Vehicle Deployment Testing

• Pole Structural Integrity
• Verify the structural integrity of the pole prior
  to mounting the plane on top
• Verify the pole does not tip over
• Test should take approximately 2 hours

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Current Issues to Be Resolved
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Schedule ProgressMajor Tasks
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Schedule ProgressMajor Tasks
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Schedule ProgressParts Progress
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Project Management PlanCost Budget