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RIT MAV Team Project 05-001 2004-2005
RIT Micro Air VehiclePreliminary Design Presentation
Brian Gillis
Team Leader
Mechanical Engineering
Joshua Baker
Mechanical Engineering
Victoria Schoennagel
Mechanical Engineering
Aimee Lemieux
Mechanical Engineering
Aaron Grilly
Mechanical Engineering
Tzu-Chie Fu
Computer Engineering
Cuong Le
Computer Engineering
David Hein
Mechanical Engineering
Atul Phadnis
Electrical Engineering
J.E.D. Hess
Mechanical Engineering
Dr. Jeffrey Kozak
Team Advisor
Mechanical Engineering
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RIT MAV Team Project 05-001 2004-2005
OutlineI. BackgroundII. Design ObjectivesIII. Work TimelineIV. Airframe SelectionV. Electronics SelectionVI. Propulsion Selection MAV Team
05-001
Airframe Electronics Propulsion
Joshua BakerAaron GrillyDavid HeinJED Hess
Cuong LeTzu-Chie FuAtul Phadnis
Aimee LemieuxVictoria Schoennagel
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RIT MAV Team Project 05-001 2004-2005
Background According to DARPA, a Micro
Air Vehicle (MAV) has a maximum linear dimension of 6 inches.
Primarily being researched for surveillance and reconnaissance operations.
Other possible uses include forest fire detection, Bio-Chemical detection, etc.
Annual MAV competition where various teams compete in surveillance missions and flight performance tests.
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RIT MAV Team Project 05-001 2004-2005
Design Objectives Vehicle with a minimum linear dimension of 15 inches Vehicle can be scaled down in size and still produce
acceptable flight Vehicle must be a new design, not rely on last years design Airframe should be built out of composite materials if deemed
reasonable Vehicle must have GPS navigation capabilities along with
video surveillance Performance Goals
15 Minutes of flight time 600 Meter range
Attend International MAV Competition in Seoul, Korea Remain within $3,000 budget (excluding travel funding)
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RIT MAV Team Project 05-001 2004-2005
Work Timeline
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RIT MAV Team Project 05-001 2004-2005
Work Timeline
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RIT MAV Team Project 05-001 2004-2005
Airframe Selection
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RIT MAV Team Project 05-001 2004-2005
Airframe Main Objectives
1. Flying Wing Configuration2. Modular Design3. Maximum Linear Dimension of 15 Inches4. Research and Test Unconventional Ideas5. Scalable Platform Upon Which to Base
Future Designs
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RIT MAV Team Project 05-001 2004-2005
Airframe - Airfoils E174 E186 EH2012 EH3012 FX63-137 GOE417a M10 M12 M14
MH46 RAF6 S1210 S2027 S4022 S4083 S5010 S5020 SD7080
E174 E186 EH2012 EH3012 FX63-137 GOE417a M10 M12 M14
MH46 RAF6 S1210 S2027 S4022 S4083 S5010 S5020 SD7080
GOE417a
S1210
S4022 S4083
To Be Tested in the Wind TunnelSurvived First Round of CutsXFLR5 Testing (Computer Simulation)
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RIT MAV Team Project 05-001 2004-2005
S1210
S4022
S4083
GOE417a
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RIT MAV Team Project 05-001 2004-2005
XFLR5 Data - Cl vs. Angle of Attack for Airfoils at Reynolds Numbers
-1.00
-0.50
0.00
0.50
1.00
1.50
2.00
2.50
-10 -5 0 5 10 15 20
Angle of Attack (Degrees)
C
l
(
D
i
m
e
n
s
i
o
n
l
e
s
s
)
GOE417a, 100,000
S1210, 100,000
S4022, 100,000
S4083, 100,000
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RIT MAV Team Project 05-001 2004-2005
A irfo il
S
4
0
8
3
S
1
2
1
0
S
4
0
2
2
G
O
E
4
1
7
a
N o rm alized S co re 100% 94% 91% 79% R ela tiv e R an k 1 2 3 4
Evaluation of each concept against the baseline: 1 = much worse than baseline 2 = worse than baseline 3 = same as baseline 4 = better than baseline 5= much better than baseline
E
1
7
4
E
1
8
6
E
H
2
0
1
2
E
H
3
0
1
2
F
X
6
3
1
3
7
G
O
E
4
1
7
a
M
1
0
M
1
2
M
1
4
M
H
4
6
R
A
F
6
S
1
2
1
0
S
2
0
2
7
S
4
0
2
2
S
4
0
8
3
S
5
0
1
0
S
5
0
2
0
S
D
7
0
8
0
R
R
e
e
l
l
a
a
t
t
i
i
v
v
e
e
W
W
e
e
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g
g
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t
t
LLooww RReeyynnoollddss nnuummbbeerr aaiirrffooiill 3.0 3.0 3.0 2.0 1.0 5.0 3.5 1.0 2.0 3.0 1.0 5.0 3.0 5.0 5.0 4.0 5.0 4.0 8% KKnnoowwnn pprriioorr uussee oonn aann MMAAVV 1.0 1.0 3.0 3.0 1.0 5.0 1.0 1.0 1.0 4.0 1.0 5.0 1.0 4.0 5.0 4.0 4.0 3.0 11%MMaannuuffaaccttuurriinngg eeaassee aanndd aaccccuurraaccyy 3.0 3.0 3.0 3.0 3.0 5.0 3.0 3.0 3.0 3.0 4.0 4.5 3.0 4.5 4.0 4.0 3.5 4.0 6% MMaannuuffaaccttuurriinngg ttiimmee 3.0 3.0 3.0 3.0 3.0 3.0 3.0 3.0 3.0 3.0 3.0 3.0 3.0 3.0 3.0 3.0 3.0 3.0 0% RReeaassoonnaabbllee ccaammbbeerr ((11%%--88%%)) 3.0 1.0 1.0 1.0 1.0 4.0 1.0 1.0 3.0 2.5 1.0 5.0 2.0 4.0 5.0 2.0 2.0 2.0 11%SSoommee rreefflleexx iinn ddeessiiggnn 1.0 4.0 3.0 3.0 1.0 2.0 3.0 2.0 3.0 3.0 1.0 2.0 2.0 3.0 3.0 3.0 4.5 2.0 14%RReeaassoonnaabbllee,, llooggiiccaall ggrraapphhss ((XXFFLLRR55)) 3.5 3.0 3.5 3.5 3.0 2.0 2.0 3.5 3.0 3.0 4.0 5.0 3.0 4.0 5.0 3.0 3.0 4.0 19%
CCll//CCdd 3.5 3.0 3.0 3.0 4.8 5.0 2.0 2.8 3.2 3.0 3.0 5.0 3.5 5.0 4.8 3.0 3.0 3.0 19%CCmm 3.0 1.0 3.0 2.0 4.9 3.0 2.0 3.0 3.0 3.0 2.5 3.0 3.0 4.6 5.0 3.0 3.0 3.0 11% WWeeiigghhtteedd SSccoorree 2.7 2.5 2.9 2.7 2.7 3.7 2.1 2.3 2.7 3.1 2.3 4.3 2.6 4.2 4.6 3.1 3.4 3.1
NNoorrmmaalliizzeedd SSccoorree 58% 53% 62% 58% 58% 79% 45% 50% 59% 66% 50% 94% 57% 91% 100% 68% 74% 67%
Airfoil Feasibility Assessment
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RIT MAV Team Project 05-001 2004-2005
Airframe - Planform
Rectangular Zimmerman Inverse Zimmerman Circle/Elliptical Modified Inverse
Zimmerman
Most Likely Design: Straight Leading Edge Approximation of the Inverse Zimmerman Planform
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RIT MAV Team Project 05-001 2004-2005
Airframe - Composition Balsa Wood with Canvas Foam (Polystyrene) Foam with Single Fiberglass
Layer Carbon Fiber Carbon Fiber with Lightening
Holes Composite (Kevlar, Fiberglass)
Foam and Fiberglass Combination will be Used for Testing, Composition of Final MAV Airframe Still to be Determined
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RIT MAV Team Project 05-001 2004-2005
Airframe Pod Location
Mounted Above Wing Mounted Below Wing Between Bi-Wing Suspended Below Wing
Most Likely Design: Mounted Below Wing
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RIT MAV Team Project 05-001 2004-2005
Airframe Control Surfaces Options Considered
Vertical Tail (and Elevator) Single (High or Low Orientation Possible) Double (High or Low Orientation Possible) Angled Vertical Tail
Winglets Vertical Winglets Angled Winglets
Canards Elevators Ailerons Elevons
Current Approach: V-Tail Protruding from Pod, Extending Beneath Wing. Elevator to be Integrated if Necessary
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RIT MAV Team Project 05-001 2004-2005
Future Analysis
Test Airfoils Control Surface
Sizing and Location Airframe Prototype
(March 14th) Refine Design Evaluate and Test
Radical Ideas
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RIT MAV Team Project 05-001 2004-2005
Electronics Selection
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RIT MAV Team Project 05-001 2004-2005
Full System Design
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RIT MAV Team Project 05-001 2004-2005
Components Onboard RF Controller/Receiver Onboard Speed Controller Onboard Servos (Actuators) Onboard Video System
Video Transceiver & Camera Passive Antenna Array Onboard GPS System
Onboard GPS Receiver Onboard GPS Video Overlay Board
Batteries
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RIT MAV Team Project 05-001 2004-2005
Onboard RF Controller/Receiver RF Controller Selected:
Futaba 6YGE 72 MHz RF Controller Onboard RF Receiver Selected:
GWS NARO R-6NH/V Receiver Channels: 6 Size: 20 x 30 x 9.5 (mm) Weight: 8.8 g
We selected the GWS NARO R-6N receiver due to its 6 channel design. This allowed for improvements in the form of additional onboard feature/control devices.
Compatibility of the controller/receiver has been verified since both use the Futaba data transmission format.
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RIT MAV Team Project 05-001 2004-2005
Onboard Speed Controller
Onboard Speed Controller Selected: Phoenix-10
The Phoenix-10 speed controller is the leading candidate to be chosen due to its compatibility with the DC motor that is being recommended by the propulsion subgroup.
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RIT MAV Team Project 05-001 2004-2005
Onboard Servos (Actuators)
Onboard Servos Selected: Wes-Technik LS-2.0
Time to Full Deflection (sec): 0.15 Max Output Force: 160 g Dimensions (mm): 21 X 13 X 9 Load Current: < 100 mA Weight: 2 g
The LS-2.0 is the suitable choice for this project since weight is considered to be one of the most important factors.
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RIT MAV Team Project 05-001 2004-2005
Onboard Video System Video System Selected:
Black Widows 200 mw Brown Bag Kit 200 mw transmitter/receiver set NTSC 5V Color CCD Camera 8 dbi Circular Polarized Patch Antenna
The 200 mw transmitter/receiver set has been selected to increase the transmission range of the video signal from the MAV to the base station. This increase in range is a critical solution to a previous performance issue of signal propagation failure.
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RIT MAV Team Project 05-001 2004-2005
Passive Antenna Array
Passive Antenna Array Selected: Leading candidate Hyperlink
HG2414P Horizontal/Vertical Beamwidth (deg): 30/30 Gain (Directivity): 14 dB
It is ideal to have an antenna that has a balance between the coverage area and the gain. Therefore, the HG2414P is chosen for its fairly good coverage area and an acceptable gain.
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RIT MAV Team Project 05-001 2004-2005
Onboard GPS System GPS System Selected:
UNAV PICO-GPS-SS (GPS Receiver)
Size: 1.8 x 1.25 x 0.6 Weight: 28 g
UNAV OSD-GPS (GPS Video Overlay Board)
Size: 2.5 x 2.5 x 0.5 Weight: 22.4 g
We selected the UNAV GPS system due to its small size and weight. Also, the UNAV GPS receiver is complimented by the UNAV video overlay board. These components have already been tested and represents a completely integrated system for GPS data acquisition.
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RIT MAV Team Project 05-001 2004-2005
Batteries Onboard Battery Cells
Leading Candidate Kokam SLPB433452 Capacity: 740 mAh Voltage: 3.7 V Dimensions (mm): 52 X 33.5 X 4.35 Volume (mm3): 7577.7 Weight: 15 g
We have selected the Kokam battery family to supply the onboard current and voltage requirements. Battery packs can be custom made in serial or parallel configurations based on power requirements. Once the total power needs are known, a final battery package can be selected.
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RIT MAV Team Project 05-001 2004-2005
Propulsion Selection
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RIT MAV Team Project 05-001 2004-2005
Propulsion Brainstorming
Power System Options IC Engine
Electric Motor
Rocket Propulsion
Propeller Options Off The Shelf Item
Modified Off The Shelf
In House Fabrication
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RIT MAV Team Project 05-001 2004-2005
Computation
eARd
dCddC
ddC
l
l
L
2
1801
+
=eARCCC LDD
2
0 +=L
D
CCWT = v
PT 97.101=
Initial Values Revised Values
All Estimated ValuesVariables 2004 2005dC l /d 0.1 0.1
AR 1.422 1.422S (m 2 ) 0.048 0.102b (m) 0.26 0.381
e 0.9 0.9dC L /d 0.041 0.041
AOA (deg) 9 9C L 0.95 0.95
W (g) 97.9 202.35C D 0.243 0.252C D0 0.018 0.027T (g) 25 53.598
Based on Chosen ElectronicsVariables 2004 2005dC l /d 0.1 0.1
AR 1.422 1.422S (m 2 ) 0.048 0.102b (m) 0.26 0.381
e 0.9 0.9dC L /d 0.041 0.041
AOA (deg) 9 9C L 0.95 0.95
W (g) 97.9 198.48C D 0.243 0.252C D0 0.018 0.027T (g) 25 52.573
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RIT MAV Team Project 05-001 2004-2005
Feasibility AssessmentEvaluate each additional concept against the baseline, score each attribute as: 0 = much worse than baseline concept 1 = worse than
baseline 2 = same as baseline 3 = better than baselinePropeller
T
h
r
u
s
t
C
o
s
t
W
e
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h
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V
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A
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1
A
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S
c
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N
o
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S
c
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r
e
T = 105-130 g; C = $20-80; W = 15-20 g; I = 0.8-1 A; V = 7-9 V ----- 2 2 2 2 2 2 2 2.00 94%GW/EDP-50XC Direct Drive Power System with 2/EP-3020 EP3020 0 3 2 1 2 0 0 1.40 66%GW/EDP-50XC Direct Drive Power System with 2/EP-3020 EP3020 0 3 2 2 3 0 0 1.60 75%Feigao 1208430S 12x22mm Brushless Motor EP7060 2 2 3 1 2 0 0 2.13 100%GW/EDP-150 Motor w/Capacitor & 2-Pin Black Motor Connector EP4530 1 3 0 1 3 0 0 1.27 59%B2C Light Power System (GW/LPS-B2C-C) EP7035 0 3 3 3 2 0 0 1.93 91%B2C Light Power System (GW/LPS-B2C-C) EP7060 0 3 3 2 3 0 0 1.87 88%B2C Light Power System (GW/LPS-B2C-C) EP7060 0 3 3 2 2 0 0 1.80 84%RXC Light Power System (GW/LPS-RXC-A) EP7060 0 3 1 2 3 0 0 1.33 63%RXC Light Power System (GW/LPS-RXC-A) EP7060 0 3 1 1 3 0 0 1.20 56%RXC Light Power System (GW/LPS-RXC-A) EP8043 1 3 1 1 3 0 0 1.53 72%RXC Light Power System (GW/LPS-RXC-A) EP8060 0 3 1 2 3 0 0 1.33 63%Astro Mighty Micro Brushless 010 (801 V 14T Direct Drive Motor) 5.5 x 4 MAS 3 1 0 1 2 0 0 1.47 69%Astro Mighty Micro Brushless 010 (801 V 14T Direct Drive Motor) 5.5 x 4 MAS 3 1 0 1 2 0 0 1.47 69%Astro Mighty Micro Brushless 010 (801 G 14T Geared Motor) APC 9 x 6E 2 1 0 1 2 0 0 1.13 53%Astro Mighty Micro Brushless 010 (801 G 14T Geared Motor) APC 9 x 6E 3 1 0 1 2 0 0 1.47 69%Astro Mighty Micro Brushless 010 (801 G 14T Geared Motor) APC 10 x 7E 3 1 0 1 2 0 0 1.47 69%Astro Mighty Micro Brushless 010 (801 G 14T Geared Motor) APC 10 x 7E 3 1 0 1 2 0 0 1.47 69%Sensorless 16 mm dia, Brushless, 15 W (EC 16, 266523) Not Given 0 1 0 1 1 0 0 0.40 19%Sensorless 22 mm dia, Brushless, 20 W (EC 22, 200858) Not Given 1 1 0 3 1 0 0 1.00 47%16 mm dia, Graphite Brushes, 4.5 W (RE 16, 118730) Not Given 0 1 0 3 1 0 0 0.67 31%25 mm dia, Precious Metal Brushes CLL, 10 W (RE 25, 118743) Not Given 0 1 0 2 1 0 0 0.53 25%Feigao 1208436L 12x30mm Brushless Motor EP3020 1 2 2 1 2 0 0 1.53 72%
Relative Weight 33% 20% 27% 13% 7% 0% 0%
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RIT MAV Team Project 05-001 2004-2005
Propulsion Static Testing1) Calibration of load cell
2) Static Propeller TestingThrust to Current Ratio
3) Static Motor TestingThrust to Current RatioMotor Body Temperature
Load Cell Calibration
y = 0.0056x + 0.9795R 2 = 1
0
0.2
0 .4
0 .6
0 .8
1
1 .2
1 .4
1 .6
1 .8
0 20 40 60 80 100 120
Load ( grams)
V
o
l
t
a
g
e
(
V
)
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RIT MAV Team Project 05-001 2004-2005
Propulsion Dynamic Testing Drag of test setup
FD = FSG2 FSG1 Dynamic propeller testing
Dp = Dt Dm Dsetup Dynamic motor testing
Dm = Dt Dp Dsetup
T1 T2 T3 T1 T2 T3 T1 T2 T3 T1 T2 T3 T1 T2 T3 T1 T2 T305
1005
10: : :4 15 10
Voltage (V) Wind Speeds (m/s)
Propeller EP7060
4
T/W Ratio T/D RatioAOA (deg) Drag (g) Thrust (g) RPM
8
9
Current Draw (A)
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RIT MAV Team Project 05-001 2004-2005
Will it Buckle?
cmLcmycmx
gFgF
y
x
08.553.4145.20
458200
1
1
=====
mNT = 73.1mNq /56.3910 =
cmt 0508.02 =55.4=FS
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RIT MAV Team Project 05-001 2004-2005
Questions?
Thank you for your time!
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RIT MAV Team Project 05-001 2004-2005
Sneaker Slides
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RIT MAV Team Project 05-001 2004-2005
Airframe - Concerns
Location of Center-of-Gravity Produce Required Lift Reduce Drag
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RIT MAV Team Project 05-001 2004-2005
Master - Airfoil Data - Command Sheet
Choose Airframe(s)
CL 50,000 E174 CD 75,000 E186 Cm 100,000 EH2012 CL/CD 125,000 EH3012
150,000 FX63137175,000 GOE417a200,000 M10225,000 M12250,000 M14275,000 MH46
RAF6S1210S2027S4022S4083S5010S5020SD7080
Check One Characteristic Choose Reynolds Number Value(s)
Plot SelectedClear
Select All Re
Select All Airfoils
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RIT MAV Team Project 05-001 2004-2005
XFLR5 Data - Cl/Cd vs. Angle of Attack for Airfoils at Reynolds Numbers
-50.00
0.00
50.00
100.00
150.00
200.00
250.00
300.00
350.00
400.00
450.00
-10 -5 0 5 10 15 20
Angle of Attack (Degrees)
C
l
/
C
d
(
D
i
m
e
n
s
i
o
n
l
e
s
s
)
GOE417a, 100,000
S1210, 100,000
S4022, 100,000
S4083, 100,000
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RIT MAV Team Project 05-001 2004-2005
XFLR5 Data - Cl vs. Angle of Attack for Airfoils at Reynolds Numbers
-1.00
-0.50
0.00
0.50
1.00
1.50
2.00
2.50
-10 -5 0 5 10 15 20
Angle of Attack (Degrees)
C
l
(
D
i
m
e
n
s
i
o
n
l
e
s
s
)
GOE417a, 100,000
S1210, 100,000
S4022, 100,000
S4083, 100,000
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RIT MAV Team Project 05-001 2004-2005
XFLR5 Data - Cd vs. Angle of Attack for Airfoils at Reynolds Numbers
0.00
0.05
0.10
0.15
0.20
0.25
0.30
-10 -5 0 5 10 15 20
Angle of Attack (Degrees)
C
d
(
D
i
m
e
n
s
i
o
n
l
e
s
s
)
GOE417a, 100,000
S1210, 100,000
S4022, 100,000
S4083, 100,000
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RIT MAV Team Project 05-001 2004-2005
XFLR5 Data - Cm vs. Angle of Attack for Airfoils at Reynolds Numbers
-0.30
-0.25
-0.20
-0.15
-0.10
-0.05
0.00
-10 -5 0 5 10 15 20
Angle of Attack (Degrees)
C
m
(
D
i
m
e
n
s
i
o
n
l
e
s
s
)
GOE417a, 100,000
S1210, 100,000
S4022, 100,000
S4083, 100,000
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RIT MAV Team Project 05-001 2004-2005
GOE417a Data - Cl vs. Angle of Attack for Airfoils at Reynolds Numbers
-0.60
-0.40
-0.20
0.00
0.20
0.40
0.60
0.80
1.00
1.20
1.40
1.60
-10 -5 0 5 10 15 20
Angle of Attack (Degrees)
C
l
(
D
i
m
e
n
s
i
o
n
l
e
s
s
)
100,000 - XFLR5
200,000 - XFLR5
99,500 - Experimental
198,500 - Experimental
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RIT MAV Team Project 05-001 2004-2005
XFLR5 Data - Cl vs. Angle of Attack for Airfoils at Reynolds Numbers
-0.05
0.00
0.05
0.10
0.15
0.20
0.25
-10 -5 0 5 10 15 20
Angle of Attack (Degrees)
C
l
(
D
i
m
e
n
s
i
o
n
l
e
s
s
)
100,000 - XFLR5
200,000 - XFLR5
99,500 - Experimental
198,500 - Experimental
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RIT MAV Team Project 05-001 2004-2005
Onboard RF Controller/Receiver
100.0%100.0%82.5%70.0%45%66.7%Normalized Normalized
ScoreScore
4.04.03.32.81.82.66666667Mean ScoreMean Score
332315RX RangeRX Range
333434Voltage NeededVoltage Needed
544312VolumeVolume
345311WeightWeight
553111Current NeededCurrent Needed
553343ChannelsChannels
GWSGWS--NARO NARO
RR--6N/H6N/H
GWSGWS--NARO NARO
RR--6N/V6N/V
GWSGWS--PICO R4PPICO R4P--
JSTJST(Last year)(Last year)
HitecHitecFeatherFeather
AirtronicsAirtronics92515Z92515Z
HitecHitecHFSHFS--04MG04MGFactors/Candidates
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RIT MAV Team Project 05-001 2004-2005
Onboard Speed Controller
72.7%100.0%90.9%Normalized ScoreNormalized Score
2.02.82.5Mean ScoreMean Score
133Dimensions (mm):Dimensions (mm):
511CompatibilityCompatibility
143Current NeededCurrent Needed
133WeightWeight
PhoenixPhoenix--1010WesWes--TechnikTechnik
YGEYGE--33(Last Year)(Last Year)
WesWes--TechnikTechnikYGEYGE--66Factors/Candidates
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RIT MAV Team Project 05-001 2004-2005
Onboard Servos (Actuators)
91.3%95.7%100.0%Normalized ScoreNormalized Score
3.03.13.3Mean ScoreMean Score
325WeightWeight
333Load CurrentLoad Current
333DimensionsDimensions
333Operating VoltageOperating Voltage
453Max Output ForceMax Output Force
233Time to Full DeflectionTime to Full Deflection
333Max DeflectionMax Deflection
WesWes--TechnikTechnikLSLS--2.42.4
WesWes--TechnikTechnikLSLS--3.03.0
WesWes--TechnikTechnikLSLS--2.02.0Factors/Candidates
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RIT MAV Team Project 05-001 2004-2005
Onboard Video System
100.0%95.2%Normalized ScoreNormalized Score
3.02.857142857Mean ScoreMean Score
33DimensionsDimensions
23WeightWeight
23Current DrainCurrent Drain
33Operating VoltageOperating Voltage
33Number of ChannelsNumber of Channels
52Transmission PowerTransmission Power
33Operating FrequencyOperating Frequency
BWAV240200BWAV240200200 mw TX/RX200 mw TX/RX
BWAV240050BWAV24005050 mw TX/RX50 mw TX/RXFactor/Candidate
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RIT MAV Team Project 05-001 2004-2005
Passive Antenna Array
100.0%81.8%90.9%81.8%100.0%Normalized ScoreNormalized Score
3.73.03.33.03.7Mean ScoreMean Score
15433Gain (Directivity)Gain (Directivity)
52334Vertical Vertical BeamwidthBeamwidth
52334Horizontal Horizontal BeamwidthBeamwidth
HG2409PHG2409PHG2424GHG2424G(Last Year)(Last Year)HG2416PHG2416PHG2414DHG2414DHG2414PHG2414PFactors/Candidates
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RIT MAV Team Project 05-001 2004-2005
Onboard GPS System
80.0%73.3%100.0%Normalized ScoreNormalized Score
2.42.23.0Mean ScoreMean Score
213Current DrainCurrent Drain
233Operating VoltageOperating Voltage
223DimensionsDimensions
123WeightWeight
533AccuracyAccuracy
UNAVUNAVPICOPICO--GPSGPS--SSSS
SarantelSarantelSmart AntennaSmart Antenna
FurunoFurunoGHGH--7979Factors/Candidates
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RIT MAV Team Project 05-001 2004-2005
Batteries
57.1%71.4%100.0%85.7%Normalized ScoreNormalized Score
2.02.53.53.0Mean ScoreMean Score
3142WeightWeight
1153VolumeVolume
1333VoltageVoltage
3524CapacityCapacity
iRateiRateLP500LP500
KokamKokamSLPB523459SLPB523459
KokamKokamSLB452128SLB452128
KokamKokamSLPB433452SLPB433452Factors/Candidates
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RIT MAV Team Project 05-001 2004-2005
ComputationVariables 2004 2005dC l /d 0.1 0.1
AR 1.421697 1.421697 Assume same shape for both years so AR remains the sameS (m 2 ) 0.047549 0.102104 For 2004, assume 90% of 8" x 26 cm rectangular wing is remainingb (m) 0.26 0.381 For 2005, assume 15" wing span
e 0.9 0.9 Assume 0.9dC L /d 0.041231 0.041231
AOA (deg) 9 9C L 0.95 0.95 @ 9 deg AOA, est. from Figure 33 on pg 46 of PDR
W (g) 97.9 202.35 Actually a Mass; 2004 from Table 16 on pg 73 of CDRC D 0.242594 0.251634C D0 0.018078 0.027117 2005 is about 1.5x the size of 2004 so increase CD0 by that muchT (g) 25 53.59796
eARd
dCddC
ddC
l
l
L
2
1801
+
=eARCCC LDD
2
0 +=L
D
CCWT = v
PT 97.101=
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RIT MAV Team Project 05-001 2004-2005
Feasibility AssessmentPairwise Comparison:
Place an "R" if the row is more important. Place a "C" if the column is more
importantT
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Thrust R R R R 4 0 5 33%Cost C R R 2 0 3 20%Weight R R 2 1 4 27%Current R 1 0 2 13%Voltage 0 0 1 7%Additional 1 0 0 0 0%Additional 2 0 0 0 0%
Column Total 0 0 1 0 0 0 0 15 100%
*Added 1 to each total to allow each parameter to have some percentage (except for undefined parameters)
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RIT MAV Team Project 05-001 2004-2005
Propulsion Concept Development Propulsion subsystem must produce enough thrust to accomplish our project goals.
Weighted scale showed an electric motor is the best of the three power options for our MAV.
Based on time limits, and lack of experience making precise molds, off the shelf propellers will be used.
Off the shelf propellers will be tested with modified shapes and in original shapes to achieve the highest efficiency.
Once our team has a working MAV, we may return to propeller design.
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RIT MAV Team Project 05-001 2004-2005
Buckling CalculationsCalculations to determine t2
Variable Value Unit Value Unit Variable Value Unit Value UnitL 2 inches 5.08 cm X1 8.052 in 20.45 cmh 1 inch 2.54 cm Y1 16.35 in 41.53 cmt2 0.02 inch 0.0508 cm Fx 0.441 lbf 200 gramt1 0.125 inch 0.3175 cm Fy 1.010 lbf 458 gram
Acs 0.02 in^2 0.129 cm^2c 1.2 --- 1.2 ---E 10300000 psi 71 GPaSy 10000 psi 70 MPa
l/k 346.410(l/k)1 156.198
Pcr 20.331 lbs 90.434 N
t2 Sy (psi) l/k (l/k)1 Method0.03 10000 346.410 156.198 Euler0.03 30000 346.410 90.181 Euler
CalculationsM = T = 15.34 lbf-in 1.73 N-mqo 2.24 lbf/in 391.56 N/m
4.47 lbf 19.89 NFS = 4.55
Calculated values
Determining Buckling Method to use for Various Sy values
Force in compressed side =
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RIT MAV Team Project 05-001 2004-2005
Load Cell Mount Drawing
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RIT MAV Team Project 05-001 2004-2005
New Back Upright Drawing
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RIT MAV Team Project 05-001 2004-2005
New Front Upright Drawing
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RIT MAV Team Project 05-001 2004-2005
Strain Gage Box Drawing
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RIT MAV Team Project 05-001 2004-2005
DC 6V EE Power Supply 5V +/- 12V Serial #EE1015
Load Cell SMD Sensor S250 1kg
100ohms
INA114 Instrumentation Amplifier Burr Brown w/ 100ohm Resistor
Oscilloscope TetronixSerial #B012473
Vc
Ref
Multimeter (// to Oscilloscope) Craftsman Serial #CCL02079157
DC 12V EE Power Supply 5V +/- 12V Serial #EE1015
25Kohm 25Kohm
25Kohm
25Kohm 25Kohm
25Kohm
DC 6V EE Power Supply 5V +/- 12V Serial #EE1015
Load Cell SMD Sensor S250 1kg
100ohms
INA114 Instrumentation Amplifier Burr Brown w/ 100ohm Resistor
Oscilloscope TetronixSerial #B012473
Vc
Ref
Multimeter (// to Oscilloscope) Craftsman Serial #CCL02079157
DC 12V EE Power Supply 5V +/- 12V Serial #EE1015
25Kohm 25Kohm
25Kohm
25Kohm 25Kohm
25Kohm
Propulsion Load Cell Calibration Electrical Schematic
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RIT MAV Team Project 05-001 2004-2005
Propulsion Motor Testing Electrical Schematic
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R L
Motor
MPJA Multimeter Serial # CCL010412272
R1
Shenzhen Mastech DC Power Supply: HY3003-3
Note: R1 is dependent on the internal resistance (R) of the motor
T