• 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

WeightMotor = 0.851 lbCIAS Payload = 3 lbMain Battery + Receiver + small battery = 2 lbWinter/Spring Project = 1 lbTail = 1 lbFuselage = 2.67 lbWing = 2.9 lbCowling = .13 lbTotal = ~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. DischargeOutput:18.5V Nominal, 8200mAhDimension: 50mm x 305mm x 28mm (772gr)

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      

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) = 13.5 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 = 7.263411 ft CD (fus) = 0.004119623  

b = 8.522565 ft D (fus) = 0.095085018 lbs

D (wing) = 0.639488 lb CD (AC) = 0.071592766  

V stall = 29.47609 ft/s D (AC) = 0.864203206 lbs

  20.09733 mph TR (cruise) = 0.806967773 lbs

V lo = 35.37131 ft/s PR (cruise) = 29.59150824 ft*lbs/sec

  24.1168 mph   0.053802742 HP

PE = 13500 ft*lbs   40.3520567 Watt

PR (to) = 45.10189 ft*lbs/sec Slo = 157.4636313 ft

  0.082003 HP R/C = 1.649684446 ft/s

  61.50258 Watt      

02.8*120*120

6*15*25

78.120*8*8

8*30*25

bS

SLV

cS

SLV

vvv

hhh

Lh = effective moment arm of horizontal stabilizerSh = area of horizontal stabilizerc = wing chordS = wing areab = wing spanLv = effective moment arm of vertical stabilizerSv = area of vertical stabilizerVv = vertical tail volume coefficientVh = horizontal tail volume coefficient

Designs should have values of (larger meaning more stable):

0.3 < Vh < 0.8

0.015 < Vv < 0.02

Team 05009 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 mphLoiter Speed: ~7 mph

Even with a 13.5lb plane, the endurance will still be over an hour.

Static Load Test

R2 = 0.9776

0

0.1

0.2

0.3

0.4

0.5

0.6

0 5 10 15 20 25 30 35

Load (lbs.)

Def

lect

ion

(in

.)

psi

I

M

lbsinlbsftWL

M

inI

tbhbdI

y

xc

xc

35.1873062455.

52.*225

22575.188

5*30

8

062455.12

25.4104.1*4

12

max

433

33

Can you see it?

psiI

M

lbsinWL

M

inI

y

xc

72.5994062455.

52.*720

7208

24*240

8

062455.

max

4

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????