requirements propulsion analysis airplane design construction final product
Post on 22-Dec-2015
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• Requirements• Propulsion• Analysis• Airplane Design• Construction• Final Product
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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
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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
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AXI 4120/18 Motor• Power: 511 Watts
• Max. Efficiency: 86%
• RPM/Volt: 510 RPM/V
• Weight: 0.7 lb
• Propeller: 13”
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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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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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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
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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
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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.
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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
.)
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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
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Can you see it?
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psiI
M
lbsinWL
M
inI
y
xc
72.5994062455.
52.*720
7208
24*240
8
062455.
max
4
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Old Design
New Design
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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
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Cutting out foam core…
Lots of foam core…
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Vacuum bagging an 8 foot wing
More vacuum bagging…
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Putting wing tips on wing…
Cutting out control surfaces…
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Failed foam mold
MDF mold much much better
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Put both halves of mold together and bondo and sand and paint and sand and paint and sand…
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All fiberglass lay up not so good…but two carbon lay ups are good
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Customizing bulkheads…
Putting two halves together…
Making sure they stay together…
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Forming the stabilizers…
Tada! A tail is born!
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Trust the trusses…
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Molds for vacuum forming
Vacuum formed cowling and motor pod
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Questions????