Airborne Sensing Platform for CIAS
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Transcript of Airborne Sensing Platform for CIAS
• Requirements• Concept Development• Feasibility• Analysis• Synthesis• Projected Timeline
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
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
The winners are:– High Wing– Carbon & Fiberglass
Materials– Low tail– Front Engine– LiPoly Battery– No landing gear– Electric Engine
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
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
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
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
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
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)
AXI 4120/18 Motor• Power: 511 Watts
• Max. Efficiency: 86%
• RPM/Volt: 510 RPM/V
• Weight: 0.7 lb
• Propeller: 14”
Thunder Power “Dynamic Power” LiPo Electric Flight Pack
Rating: 5C Max Avg. DischargeOutput:18.5V Nominal, 8200mAhDimension: 50mm x 305mm x 28mm (772gr)
Questions????