D-SUAVE

1
D-SUAVE

• Deployable Small UAV Explorer

University of Colorado at Boulder
D S U A V E
Interim Review 1 Spring 2007
2
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
3
Overview

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

4
RFAWing Deployment Spring Length
5
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.
8
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

9
Design Changes

• Vehicle and wing deployment

10
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

11
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)

12
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.)

13
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

14
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.)

15
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

16
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.)

17
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
Issue Plan
Orientation of aircraft before wing deployment Pre-testing of system using non-destructive tests.
Not enough rolling stability Increase dihedral to 100
Mass budget Mass parts as manufactured
Deployment servo speed On-ground testing of servo and software
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Schedule ProgressMajor Tasks
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Schedule ProgressMajor Tasks
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Schedule ProgressParts Progress
  Number of Parts Fabrication Status ()
Finished 5 11
Purchased 16 --
In-Work 10 23
Not Started 29 66
Total 60 100
Deployment Package Deployment Package
DS-DP-01 Vehicle Connection Back
DS-DP-02 Servo Rotor
DS-DP-03 P Servo
DS-DP-04 Thick Bearing
DS-DP-05 Vehicle Connection Front
DS-DP-06 Release Rod
DS-DP-100 ARES Mount Assembly
DS-DP-101 ARES Mount Front
DS-DP-102 ARES Mount
DS-DP-103 Slider Bearing
DS-DP-104 Slider Front
DS-DP-105 Mounting Plate
DS-DP-106 P Spring
DS-DP-200 Vehicle Deployment Rod Assembly
DS-DP-201 Spring Stopper
DS-DP-202 Slider
Aerodynamic Surfaces Aerodynamic Surfaces
DS-AS-WS-100 Right Wing and foam assembly
DS-AS-WS-101 Foam
DS-AS-WS-102 Wing Surface
DS-AS-WS-200 Left Wing and foam assembly
DS-AS-WS-201 Foam
DS-AS-WS-202 Wing Surface
DS-AS-TS-100 Tail Boom Assembly
DS-AS-TS-101 Vertical Tail
DS-AS-TS-102 Tail Ring
DS-AS-TS-103 Rudder Surface
DS-AS-TS-104 Elevator Surface
DS-AS-TS-105 P Control Arm
DS-AS-TS-106 Servo Casing
DS-AS-TS-107 P Servo
DS-AS-TS-110 Tail Assembly
DS-AS-TS-120 Horizontal Tail Assembly
DS-AS-TS-121 Horizontal Skin Left
DS-AS-TS-122 Horizontal Skin Right
DS-AS-TS-123 Shim
DS-AS-TS-124 Horizontal Spar
Structure Swing Mechanism Structure Swing Mechanism
DS-ST-SM-01 Backbone
DS-ST-SM-02 Swing Mechanism Mount
DS-ST-SM-03 Swing Mechanism Slider
DS-ST-SM-04 Spring Stopper
DS-ST-SM-05 Pin
DS-ST-SM-06 Pivot Joints 13 Pins
DS-ST-SM-07 Pusher Rod
DS-ST-SM-08 Pivot Joint 2 Pin
DS-ST-SM-09 Locking Mechanism
DS-ST-SM-10 Wing Release Mechanism
DS-ST-SM-11 Slider Bushing
DS-ST-SM-100 Spar Assembly
DS-ST-SM-101 Main Wing Spar
DS-ST-SM-102 Dihedral Joint
DS-ST-SM-103 Spar Pivot Interface
Fuselage Nose Fuselage Nose
DS-FN-00 Fuselage Assembly
DS-FN-01 Main Fuselage
DS-FN-02 Dummy Payload
DS-FN-03 Fuselage Cradle Front
DS-FN-04 Fuselage Cradle Rear
DS-FN-100 Propeller and Motor Assembly
DS-FN-101 P Motor
DS-FN-102 P Propeller
DS-FN-103 P Propeller Blade
DS-FN-EC-01 P Onboard Receiver
DS-FN-EC-02 P Flight Dynamics Board
DS-FN-EC-03 P ESC/BEC
DS-FN-EC-04 P Battery
DS-FN-EC-05 P Gnd Radio Transmitter
DS-FN-EC-06 P GPS Antenna
DS-FN-EC-07 P Xbee-Pro Development SW
DS-FN-EC-08 P Xbee-Pro Development Board
DS-FN-EC-09 P U.FL Cable
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Project Management PlanCost Budget
Subsystem Expenditure () Pending Expense ()
Wing Construction 540 250
Propulsion 287 150
Electronics 720 100
Wing Deployment 110 100
Vehicle Deployment 0 500
Miscellaneous 160 N/A
TOTAL 1800 1100
Current Budget Estimate Current Budget Estimate 2900
CDR Budget Estimate CDR Budget Estimate 2400