Requirements Propulsion Analysis Airplane Design Construction Final Product

The College of Imaging Arts & 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 Accommodate 6 in. x 6 in. x 12 in. payload

Weight Motor = lb CIAS Payload = 3 lb Main Battery + Receiver + small battery = 2 lb Winter/Spring Project = 1 lb Tail = 1 lb Fuselage = 2.67 lb Wing = 2.9 lb Cowling =.13 lb Total = ~13.5 lb

AXI 4120/18 Motor Power: 511 Watts Max. Efficiency: 86% RPM/Volt: 510 RPM/V Weight: 0.7 lb Propeller: 13”

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)

alpha knot =4.775rho (SL) = Cd =0.006 alpha =4.085rho (cruise) = CL 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 TO (lb)=2.57mu (pavement) climb (ft*lbs/s) =110 CL = Re (fus) =9.06E+05 CD (wing) = Cf =4.76E-03 S = ftCD (fus) = b = ftD (fus) = lbs D (wing) = lbCD (AC) = V stall = ft/sD (AC) = lbs mphTR (cruise) = lbs V lo = ft/sPR (cruise) = ft*lbs/sec mph HP PE =12000ft*lbs Watt PR (to) = ft*lbs/secSlo = ft HPR/C = ft/s Watt

alpha knot =4.775rho (SL) = Cd =0.006 alpha =4.085rho (cruise) = CL max =1.8 Cl =1.4V (ft/s) =36.67mu =3.74E-07 e =0.9weight (lb) =13.5Lf (fus length) (ft) =4 AR =10time to TO (s ) =300dia of fuselage (ft) =0.5 TO (lb)=2.57mu (pavement) climb (ft*lbs/s) =110 CL = Re (fus) =9.06E+05 CD (wing) = Cf =4.76E-03 S = ftCD (fus) = b = ftD (fus) = lbs D (wing) = lbCD (AC) = V stall = ft/sD (AC) = lbs mphTR (cruise) = lbs V lo = ft/sPR (cruise) = ft*lbs/sec mph HP PE =13500ft*lbs Watt PR (to) = ft*lbs/secSlo = ft HPR/C = ft/s Watt

Lh = effective moment arm of horizontal stabilizer Sh = area of horizontal stabilizer c = wing chord S = wing area b = wing span Lv = effective moment arm of vertical stabilizer Sv = area of vertical stabilizer Vv = vertical tail volume coefficient Vh = horizontal tail volume coefficient Designs should have values of (larger meaning more stable): 0.3 < V h < < V v < 0.02

Team ran an endurance test using our battery specifications on the Telemaster. According to those tests, the performance expected based off of a 10lb plane is: Range: 80+km (50 miles) (at 26 mph) Endurance: 2 hours; 1 hour, 45 minutes with climb to altitude (1000 ft) (at 20 mph) Max. Rate of Climb: 10 m/s (meaning 90s egress to 1000 ft) Max. Speed: ~72 mph Loiter Speed: ~7 mph Even with a 13.5lb plane, the endurance will still be over an hour.

Can you see it?

Old Design New Design

Old Wing Length: 96 in. Wing construction: built up balsa core, fiberglass laminate Dihedral: 5º from center Wing segment: 2 piece joined wing New Wing Length: 120 in. Wing construction: foam core, bass wood spar, laminated with unidirectional carbon and one layer of fiberglass Dihedral: 13º at wing tips Wing segment: continuous piece with 2 joined 1 foot wing tips

Cutting out foam core… Lots of foam core…

Vacuum bagging an 8 foot wing More vacuum bagging…

Putting wing tips on wing… Cutting out control surfaces…

Failed foam mold  MDF mold much much better

Put both halves of mold together and bondo and sand and paint and sand and paint and sand…

All fiberglass lay up not so good…but two carbon lay ups are good

Customizing bulkheads… Putting two halves together… Making sure they stay together…

Forming the stabilizers… Tada! A tail is born!

Trust the trusses…

Molds for vacuum forming Vacuum formed cowling and motor pod

Questions????