Remote sensing of marine oil spills from airborne platforms using ...
Airborne Sensing Platform for CIAS
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Transcript of Airborne Sensing Platform for CIAS
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• Requirements• Concept Development• Feasibility• Analysis• Synthesis• Projected Timeline
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The College of Imaging Science (CIAS) requested an airborne platform to carry advanced sensing instrumentation and telemetering equipment in surveillance applications with these requirements:
Carry a 3lb payload
Has a cruise speed 15 – 30 mph
Has 1 hour endurance
Can climb 1000 ft
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Fuselage Materials- Carbon, Fiberglass, Wood
Engine Location- Front, Back, Top
Propulsion- Gas, Electric, Hybrid
Batteries- Nimh, NiCad, LiPoly
Landing Gear- Trike, Tail-dragger, None at all
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The winners are:– High Wing– Carbon & Fiberglass
Materials– Low tail– Front Engine– LiPoly Battery– No landing gear– Electric Engine
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Wing Location Feasibility Assessment
(On a scale from 1-10) Weighting High
R1: Sufficient Skills 0.1 8
R2: Sufficient Equipment 0.1 9
R3: Sufficient # of people 0.13 2
E1: Economically Feasible 0.07 9
S1: Meeting Intermediate Milestones 0.1 8
S2: Meeting PDR Requirements 0.1 7
S3: Meeting CDR Requirements 0.15 7
T1: Has similar technology been used before 0.12 9
T2: Plane stability 0.08 9
T3: Drag reducing 0.05 8
1 7.34
Fuselage Material Feasibility Assessment
(On a scale from 1-10) Weighting Carbon
R1: Sufficient Skills 0.1 6
R2: Sufficient Equipment 0.1 9
R3: Sufficient # of people 0.13 2
E1: Economically Feasible 0.07 9
S1: Meeting Intermediate Milestones 0.1 8
S2: Meeting PDR Requirements 0.1 8
S3: Meeting CDR Requirements 0.15 7
T1: Has similar technology been used before 0.09 9
T2: Durability 0.08 9
T3: Weight 0.08 7
Total: 1 7.13
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Tail Design Feasibility Assessment(On a scale from 1-10)
Weighting Low
R1: Sufficient Skills 0.1 9
R2: Sufficient Equipment 0.1 9
R3: Sufficient # of people 0.13 2
E1: Economically Feasible 0.07 8
S1: Meeting Intermediate Milestones 0.1 8
S2: Meeting PDR Requirements 0.1 8
S3: Meeting CDR Requirements 0.15 8
T1: Has similar technology been used before 0.12 8
T2: Plane stability 0.08 6
T3: Drag reducing 0.05 7
Total: 1 7.21
Engine Location Feasibility Assessment(On a scale from 1-10)
Weighting Front
R1: Sufficient Skills 0.1 8
R2: Sufficient Equipment 0.1 8
R3: Sufficient # of people 0.13 2
E1: Economically Feasible 0.07 8
S1: Meeting Intermediate Milestones 0.1 7
S2: Meeting PDR Requirements 0.1 8
S3: Meeting CDR Requirements 0.15 8
T1: Has similar technology been used before 0.12 9
T2: Plane stability 0.08 8
T3: Drag reducing 0.05 8
Total: 1 7.24
Propulsion(On a scale from
1-10) Weighting Electric
Vibration 0.3 9
Weight 0.2 8
Stability 0.2 9
Cost 0.1 7
Ease of Installation 0.2 9
Total: 1 8.6
Batteries(On a scale from 1-10) Weighting LiPoly
Energy Density (charge/mass) 0.4 9
Cost 0.1 6
Ease of use/installation 0.2 8
Recharge Ratio 0.3 7
Total: 1 7.9
Landing Gear(On a scale from
1-10) Weighting None
Aerodynamics 0.2 9
Ground Handling 0.2 0
Weight 0.3 10
Ease of Construction 0.3 10
Total: 1 7.8
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WeightMotor + Motor Shelf = 1 lbCIAS Payload = 3 lbMain Battery + Receiver + small battery = 2 lbWinter/Spring Project = 1 lbTail = .2 lbFuselage = 1.8 lbWing = 3 lbTotal = ~12 lb
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Some Important Equations…
D
LR
olL
L
C
CWT
S
bAR
CC
SCVL
2
2
2
1
VTP
DDD
eAR
CCC
SCVD
fuselagewingCA
LdD
D
*85.0
2
1
/
2
2
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alpha knot = 4.775 rho (SL) = 0.0023769 Cd = 0.006
alpha = 4.085 rho (cruise) = 0.0023081 CL max = 1.8
Cl = 1.4 V (ft/s) = 36.67 mu = 3.74E-07
e = 0.9 weight (lb) = 12 Lf (fus length) (ft) = 4
AR = 10 time to TO (s ) = 300 dia of fuselage (ft) = 0.5
T @ TO (lb)= 2.57 mu (pavement) = 0.02 PA @ climb (ft*lbs/s) = 110
CL = 1.197696 Re (fus) = 9.06E+05
CD (wing) = 0.056734 Cf = 4.76E-03
S = 6.456365 ft CD (fus) = 0.004634576
b = 8.035151 ft D (fus) = 0.106970646 lbs
D (wing) = 0.568434 lb CD (AC) = 0.072198593
V stall = 29.47609 ft/s D (AC) = 0.794593132 lbs
20.09733 mph TR (cruise) = 0.723374609 lbs
V lo = 35.37131 ft/s PR (cruise) = 26.52614691 ft*lbs/sec
24.1168 mph 0.048229358 HP
PE = 12000 ft*lbs 36.17201851 Watt
PR (to) = 40.09369 ft*lbs/sec Slo = 132.0693402 ft
0.072898 HP R/C = 2.484385668 ft/s
54.67321 Watt
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0
0.5
1
1.5
2
2.5
3
5 10 15 20 25 30 35 40 45 50
Velocity (ft/s)
R/C
(ft
/s)
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AXI 4120/18 Motor• Power: 511 Watts
• Max. Efficiency: 86%
• RPM/Volt: 510 RPM/V
• Weight: 0.7 lb
• Propeller: 14”
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Thunder Power “Dynamic Power” LiPo Electric Flight Pack
Rating: 5C Max Avg. DischargeOutput:18.5V Nominal, 8200mAhDimension: 50mm x 305mm x 28mm (772gr)
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Questions????