2. Requirements Concept Development Feasibility Analysis Synthesis Projected Timeline

3. 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

5. 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

6. The winners are: –High Wing –Carbon & Fiberglass Materials –Low tail –Front Engine –LiPoly Battery –No landing gear –Electric Engine

7. Wing Location Feasibility Assessment (On a scale from 1-10)WeightingHigh R1: Sufficient Skills0.18 R2: Sufficient Equipment0.19 R3: Sufficient # of people0.132 E1: Economically Feasible0.079 S1: Meeting Intermediate Milestones0.18 S2: Meeting PDR Requirements0.17 S3: Meeting CDR Requirements0.157 T1: Has similar technology been used before0.129 T2: Plane stability0.089 T3: Drag reducing0.058 17.34 Fuselage Material Feasibility Assessment (On a scale from 1-10)WeightingCarbon R1: Sufficient Skills0.16 R2: Sufficient Equipment0.19 R3: Sufficient # of people0.132 E1: Economically Feasible0.079 S1: Meeting Intermediate Milestones0.18 S2: Meeting PDR Requirements0.18 S3: Meeting CDR Requirements0.157 T1: Has similar technology been used before0.099 T2: Durability0.089 T3: Weight0.087 Total:17.13

8. Tail Design Feasibility Assessment (On a scale from 1-10) Weighti ngLow R1: Sufficient Skills0.19 R2: Sufficient Equipment0.19 R3: Sufficient # of people0.132 E1: Economically Feasible0.078 S1: Meeting Intermediate Milestones0.18 S2: Meeting PDR Requirements0.18 S3: Meeting CDR Requirements0.158 T1: Has similar technology been used before0.128 T2: Plane stability0.086 T3: Drag reducing0.057 Total:17.21 Engine Location Feasibility Assessment (On a scale from 1-10) Weighti ngFront R1: Sufficient Skills0.18 R2: Sufficient Equipment0.18 R3: Sufficient # of people0.132 E1: Economically Feasible0.078 S1: Meeting Intermediate Milestones0.17 S2: Meeting PDR Requirements0.18 S3: Meeting CDR Requirements0.158 T1: Has similar technology been used before0.129 T2: Plane stability0.088 T3: Drag reducing0.058 Total:17.24 Propulsion (On a scale from 1-10)WeightingElectric Vibration0.39 Weight0.28 Stability0.29 Cost0.17 Ease of Installation0.29 Total:18.6 Batteries (On a scale from 1-10)WeightingLiPoly Energy Density (charge/mass)0.49 Cost0.16 Ease of use/installation0.28 Recharge Ratio0.37 Total:17.9 Landing Gear (On a scale from 1-10)WeightingNone Aerodynamics0.29 Ground Handling0.20 Weight0.310 Ease of Construction0.310 Total:17.8

10. Weight Motor + Motor Shelf = 1 lb CIAS Payload = 3 lb Main Battery + Receiver + small battery = 2 lb Winter/Spring Project = 1 lb Tail =.2 lb Fuselage = 1.8 lb Wing = 3 lb Total = ~12 lb

11. Some Important Equations…

12. alpha knot =4.775rho (SL) =0.0023769Cd =0.006 alpha =4.085rho (cruise) =0.0023081CL max =1.8 Cl =1.4V (ft/s) =36.67mu =3.74E-07 e =0.9weight (lb) =12Lf (fus length) (ft) =4 AR =10time to TO (s ) =300dia of fuselage (ft) =0.5 T @ TO (lb)=2.57mu (pavement) =0.02PA @ climb (ft*lbs/s) =110 CL =1.197696 Re (fus) =9.06E+05 CD (wing) =0.056734 Cf =4.76E-03 S =6.456365ftCD (fus) =0.004634576 b =8.035151ftD (fus) =0.106970646lbs D (wing) =0.568434lbCD (AC) =0.072198593 V stall =29.47609ft/sD (AC) =0.794593132lbs 20.09733mphTR (cruise) =0.723374609lbs V lo =35.37131ft/sPR (cruise) =26.52614691ft*lbs/sec 24.1168mph 0.048229358HP PE =12000ft*lbs 36.17201851Watt PR (to) =40.09369ft*lbs/secSlo =132.0693402ft 0.072898HPR/C =2.484385668ft/s 54.67321Watt

17. AXI 4120/18 Motor Power: 511 Watts Max. Efficiency: 86% RPM/Volt: 510 RPM/V Weight: 0.7 lb Propeller: 14”

18. Thunder Power “Dynamic Power” LiPo Electric Flight Pack Rating: 5C Max Avg. Discharge Output:18.5V Nominal, 8200mAh Dimension: 50mm x 305mm x 28mm (772gr)

20. Questions????