Uninhabited Air Vehicle Team
Multi Purpose UAV
Team Members:
Faculty Advisors:
Maria Luviano
Roland Chen
Juan Pablo Barquero
Shing Chi Chan
Tom Guyette
Solomon Yitagetsu
Winston Young
Wess Gates
Dr. Chivey Wu
Dr. Helen Boussalis
1/28/10
Volunteers:
Keith Bacosa
Billy Barrios
Michael Doan
Rama Mbecke
Omar Miranda
NASA Grant NNX08BA44A
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KOSMOS HERMES 55
11/19/09
NASA Grant NNX08BA44A
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Overview
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Objective
Aircraft performance
Structures
Prototype
Computational fluid dynamics
Flight control system integration
Propulsion
Budget
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Objective
To design an autonomous, heavy payload, lightweight UAV that is
capable of carrying out multiple missions.
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Aircraft Performance
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Technical Data
Technical Data
1/28/10
Gross Weight
55
lbs
Wingspan
11
Ft
Length
7
Ft
Payload Weight
10
Lbs
Cruise altitude
3280
Ft
Cruise Speed
73.35
Ft/s
Endurance
3
Hrs
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Lift Curve Slopes and Coefficients
Wing Lift Curve Slope
CLa =
0.060298
Canard Lift Curve Slope
CLa =
0.018188
CLa =
Swing=
Scanard=
Stot=
Swet=
Cfe=
CD,O=
0.078486
23.91304
5
28.91304
75.35979
0.0055
0.017333
0.75
0.084882
0
0.028294
0.113177
Total Lift Curve Slope
Wing Plantform Area
Canard Plantform Area
Total Plantform Area
Total Wetted Area
Skin Fraction Coefficient
Zero Lift Drag Coefficient
Span Efficiency
Induced Drag Factor
assuming no wave drag
 Lift curve slope
1/28/10
e=
k3=
k2=
k1=
K=
CL ( Aircraft )  CL ( wing / Strakes )  CLC (1 
NASA Grant NNX08BA44A
ft^2
ft^2
ft^2
ft^2
 Sc
)
 S
7
Aircraft Performance
a (deg)
CL
CDi
CD
Lift (lb)
Tr (lbs
Pr(hp)
-4
-0.16
0.01625
0.02012
-29.30209
3.10653
0.41430
-2
0.00
0.01394
0.01733
0.00000
2.67599
0.35688
0
0.16
0.01207
0.02012
29.30209
3.10653
0.41430
2
0.31
0.01281
0.02849
58.60417
4.39817
0.58656
4
0.47
0.01711
0.04243
87.90626
6.55090
0.87365
6
0.63
0.02041
0.06195
117.20834
9.56472
1.27559
8
0.78
0.02486
0.08705
146.51043
13.43963
1.79236
10
0.94
0.03012
0.11773
175.81251
18.17564
2.42397
12
1.10
0.04097
0.15398
205.11460
23.77273
3.17042
14
1.26
0.03569
0.19581
234.41668
30.23092
4.03171
16
1.41
0.05045
0.24322
263.71877
37.55020
5.00783
 Lift to drag ratio (L/D)max = 11
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Engine Sizing
GW vs Power (HP)
10
9
8
7
Power (HP)
6
Dark line PS
5
4
Green line
UAV
3
2
1
0
30.00
40.00
50.00
60.00
70.00
80.00
90.00
100.00 110.00 120.00 130.00 140.00
Gross Weight (lbs)
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Power Curves
6
5
(PA)max
Power (hp)
4
3
2
1
Vmax
0
0
20
40
60
80
100
120
Velocity (Knots)
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Performance
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 Maximum climb angle
Vmax = 161 ft/s
♦ Sin Θmax = T/W – 1/(L/D)max
 Rate of climb
♦ (R/C)max = Excess power
W
♦ (R/C)max = 34.5 ft/s
♦ Θ = 27 deg.
 Flight velocity for maximum angle of
attack
 Flight velocity for maximum rate of climb
♦ V(L/D)max = (2/ρ)*((K/CD,O)^1/2)*(W/S)
♦ Vθmax = Max rate of climb
Sin Θmax
♦ Vθmax = 76 ft/s
♦ V(L/D)max = 70 ft/s
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Structures
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Aircraft Structures
 Aircraft structure is required to support two distinct classes of load
♦ Ground load: movement on the ground ( taxiing, landing, and towing)
♦ Air loads: loads during flight by maneuvers and gusts.
 Function of structural components:
♦ To transmit and resist loads to provide shape and protect passengers,
payload, systems, etc from the environmental conditions found during
flight.
 Current UAV structural objective:
♦ To have a semi-monocoque structure that has “minimal” structural
members.
♦ Have the skin of the UAV to be manufactured with different thicknesses
in order to achieve a lighter aircraft weight
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Concepts
Concept 1 – Rib and spar
configuration
Concept 2 – Lighter rib and
spar configuration
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Concepts
Concept 3 – Rib and spar
configuration assembled with an
uniform wing skin thickness
Concept 4 – Structural member
with an uniform wing skin
thickness
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Structural Concept
 This approach considers the following:
♦ Split the wing in two main sections
 Section 1 – have a semi-monocoque structure to absorb most of the loads
 Section 2 – completely monocoque where the loads decrease
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Section 1 – Semi-monocoque structure with skin
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Structural Concept
Section 1
Service panel
Fuselage
base plate
Section 2
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Next Steps
 Optimize wing internal structural concept
♦ Use of FEA (Finite Element Analysis)
♦ Decrease size of cross members
 Optimize skin thickness
 Define/design mounting brackets for wing and skin
 Define mounting points for control surfaces
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Prototype
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Prototype Objectives
 Validation of Current Aerodynamics
♦ Canard Design
♦ Aerodynamics of the Wing
♦ Balance and Stability
 Practice for Possible Fabrication Techniques
♦ Multiple Interchangeable Wings
 Conventional, Composite, etc.
 Identify the Proper Parameters for Control
♦ Control Surface optimization
 Test Current Landing Gear configuration
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Half Scale Prototype
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Specifications
 Dimensions:
♦ Length: 45.15 in (1.14 meters)
♦ Height: 17.316 in (0.43 meters)
♦ Wingspan: 63.44 in (1.611376 meters)
 Weight: 5-6 pounds (2.26 - 2.72 kilograms)
 Propulsion: Electric Motor
♦ Propeller Diameter: 12 in (0.30 meter)
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Manufacturing
 Fuselage and Canard
♦ Cut from Foam
♦ Sand to Final Shape
 Wing
♦ Version 1
 Built up from Balsa and Plywood
 Covered with film
♦ Future Versions
 Fiberglass or Carbon Fiber
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Computational Fluid Dynamics
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AVL
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Athena Vortex Lattice
Written by Mark Drela
Computes yawing moments, rolling moments, and stability
Models ailerons and flaps
Feeds into simulation effort
Verify hand calculations
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AVL editor
 The Cloud Cap Technology software includes an AVL editor for the end user to try
out different AVL configurations. The aerodynamic properties are then shown in the
AVL editor window along with the appearance of the wing structure.
Inputting Geometry into AVL
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AVL Model
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AVL Model
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Loading
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Flight Control System Integration
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T60 Piccolo Hardware Integration
Purpose: To learn everything about installing and flying Piccolo in an
inexpensive air vehicle so we’ll be ready when our new vehicle is complete.
Work completed:
 Manual test flight complete (Solomon, Juan, Maria)
 Communication issues are resolved
 Piccolo has been fit into fuselage (harder than it sounds!)
 Piccolo is roughly leveled / squared with fuselage
 Manual control through Piccolo link is verified
 Control surfaces are calibrated
Image source: towerhobbies.com, wikipedia.org
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T60 Piccolo Hardware Integration
Work remaining:
 Test running Ground Station from 12V power inverter
 Calibrate throttle servo
 Gather vibration data
 Test GPS
 Test comm range
 Some remaining mechanical maintenance
 Design Deadman power system
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NASA Grant NNX08BA44A
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T60 Piccolo Simulation
Purpose: To tell Piccolo everything it
needs to know to pilot the vehicle.
Available from other sources:
Masses, some dimensions, AVL
model, rough propulsion model
Work remaining:
 Model in AVL simulator and XFoil
 Measure squareness angles
 Measure additional dimensions
 Re-calculate and measure CG
 Calculate mass moments of inertia
(easy, but values are rough)
 Measure moments of inertia?
(complicated / better values)
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Propulsion
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Overview
 Engine break in
 Engine bench test
 SolidWorks model
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Break in Engine Mount
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Bench Test Design
Strain gage
 Three kinds of test will
be performed
♦ Thrust
♦ RPM
♦ Fuel flow
 Test the propeller’s
performance
 Compare the result
 Which propellers have
good efficiency
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Side View
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Top View
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Diagonal View
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Instrumentation
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Budget
3/12/2016
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3/12/2016
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New Materials
 Total budget $13,500
3/12/2016
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Reference
 Corke C. Thomas. Design of Aircraft. 2003. Prentice Hall
 Anderson Jr, John D. Aircraft Performance and Design. Mcgraw Hill 1999
 Beer P. Ferdinand, Johnson E. Russell, and Dewolf T. John. Mechanics of Materials.
4th Edition. McGraw Hill. 2003
 T.H.G. Megson. Aircraft Structures for Engineering Students. 3rd Edition. Butterworth
Heinenmann. 1999
 Raymer, Daniel P, Aircraft Design: A Conceptual Approach. 3rd Edition. AIAA
Education Series 1999
 http://www.sierracomposites.com/carbon-fiber-square-tube-with-2-sidesp/cfst284.htm
 http://dragonplate.com/docs/DPSpecRecTube.pdf
 http://www.safetycitystore.comhttp://www.bagking.com/Merchant2/merchant.mvc?Scr
een=PROD&Product_Code=TDH6&qts=googlebase&qtk=TDH6
 http://www.delta7bikes.com/shop-bike.htm
 Anderson Jr, John D. Aircraft Performance and Design. Mcgraw Hill 1999
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Reference
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http://www.powerelectronics.com
http://www.sengpielaudio.com/calculator-cross-section.htm
http://www.batteryuniversity.com/partone-5A.htm
http://www.mpoweruk.com/performance.htm
http://en.wikipedia.org/wiki/Torque
http://www.copperhillmedia.com/VisualSizer/MotorSizingArticles.html
http://www.electricmotors.machinedesign.com/guiEdits/Content/bdeee3/bdeee3_1.as
px
http://rmsmotion.com/resources/step_basics_v1_0.pdf
A Comprehensible Guide to Servo Motor Sizing by Wilfried Voss
http://www.powerstream.com/Wire_Size.htm
http://www.66pacific.com/calculators/wire_calc.aspx
AVL. Mark Drela, Harold Youngren. MIT Aero and Astro
Cloud Cap Technology user guide, software simulation manual, and checklist
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Thank You
Advisors
Dr. Boussalis
Dr. Wu
Dr. Guillaume
Dr. Pham
Dr. Liu
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