Post on 01-Jan-2016
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Group 13 Heavy Lift Cargo Plane
Stephen McNultyRichard-Marc Hernandez
Jessica PisanoYoosuk Kee
Chi Yan
Project Advisor: Siva Thangam
Overview
• Objectives • Schedule• Design Concept Summary • Construction
– Wing– Fuselage– Tail– Landing Gear– Boom
• Testing• Problems/Suggestions• Competition Goals• Website
Objectives
• The plane meets the specifications of the 2004 SAE Aero Design West competition
• To complete construction by mid April to allow time for testing and modifications
• To compete well at competition and improve Stevens reputation
• For the team to improve and expand their knowledge of the design and construction of airplanes
Design Specifications
• Minimum allowed wingspan120 inches
• Takeoff limit200 feet
• Landing Distance400 feet
• Minimum cargo area 6 in x 5 in x 4 in
• Engine– unmodified FX O.S. 2 stroke
motor– 0.61 cubic inches– 1.9 hp– E-4010 muffler
Design Specs ComparisonDesign Specifications: This Year (2004) Previous Year (2003)
Wing Span Minimum 10 ft Maximum 6 ft
Wing Chord No restriction Maximum 1 ft
Cargo Volume Minimum 120 in3 Minimum 300 in3
Maximum Takeoff Distance 200 ft 200 ft
Maximum Landing Distance 400 ft 400 ft
Engine .61 FX-OS .61 FX-OS orK&B .61 R/C ABC
Battery Minimum 500 mAh Minimum 500 mAh
Schedule 2nd Semester
Schedule 1st Semester
Calculation Achievements
• Calculation of every component completed• Equations and resources from:
– textbooks– online researching– white paper (Provided by SAE)
• Calculations done with Excel Spreadsheet– Easy to link one value to another– Graphs were easy to compare which design is more efficient– Change around numbers
• compare which aircraft design performs best upon constructing and testing
• Results used in selection of airfoil, wing shape, and tail stabilizer
• Calculations of Landing and Take-off
Sample EquationsLanding Run Distance
• Differential Equation of Motion
• Landing ground runway
• Coefficients A and B
• Stall Velocity
2sec/966.0 ftCW
TgA rolling
static
2BVA
VdVdS
21ln
2
1TDlanding V
A
B
BS
gLrollinggDp CCCA
W
gB ,,2
1
sec/8494.25
2
1
2
1
max,
ftCA
WV
Lp
stall
Sample Excel Calculations
Horizontal tail: Vertical Tail:
Re (NACA 0012) 175975.6 Re (NACA0012) 246365.9
chord (MAC) 7 in chord (MAC) 9.8 in
Swet 0 in^2 Swet 189 in^2
Wing Span 40 in Tail height 24 in
Sref 280 in^2 Sref 235.2 in
Clmax 0 Clmax
Cf (laminar) 0.003166 Cf (laminar) 0.002675
t/c 0.12 t/c 0.12
x/c 0.287 x/c 0.287
FF 1.271607 FF 1.271607
Cdmin (laminar) 0 Cdmin (laminar) 0.0027339
Payload Weight vs. Density Altitude
Payload Weight vs. Density Altitude
20
20.1
20.2
20.3
20.4
20.5
20.6
20.7
0 200 400 600 800 1000 1200
Density Altitude [ft]
Pay
load
Wei
gh
t [l
ds]
[Payload Weight] = 20.60 – 5.15E-4 × [Density Altitude]
Wing Design and Construction
Rib
•Print and cut original
•Metal cut out template
•Final for placement in wing
•Selig 1223•SolidWorks Drawing
Airfoil
• Airfoil selection– Year 2000: E 211– Year 2001: E 423– Year 2002: OAF 102– Research: E 214– Research: S 1223
Imp
orta
nt F
ac
tor
E1
22
E2
14
E4
23
OA
F1
02
S1
22
3
Cl 5 1 2 2 3 5
Cd 2 5 4 4 3 2
Construction 3 5 5 4 4 3
Overall 50 30 33 30 33 38
CL&CD
vs.AoA Coefficient of Lift
0
0.5
1
1.5
2
2.5
3
3.5
-5 0 5 10 15
angel of attack
coef
fici
ent
of
lift
No Flaps Flaps +15 Flaps -15
Coefficient of Drag
0
0.02
0.04
0.06
0.08
0.1
0.12
-5 0 5 10 15
angle of attack
coef
fici
ent
of
dra
g
No Flaps Flaps +15 Flaps -15
Control Surface Affect
Wing Stress Analysis
Max stress = 330.9 psi
Wing• 10 ft wing span • 1 ft cord• Flap 3 ft
Fuselage
• Shortened to 2’-1” long• Made from plywood and
balsa wood• Attached to boom
externally New design
Old design
BoomThree Spar
•Connects tail to fuselage •Two Booms create wobble•Carbon Fiber •5ft length•½ in inner Diameter
Tail Section
• NACA 0012 Airfoil• Similar Construction to Wing• Controls:
– Horizontal Stabilizer– Vertical Flaps
Tail Section
• Wooden Beam to Carbon Fiber Attachment• Design Limits tail AoA• Servos built inside tails
Landing Gear Analysis• SolidWorks models
– Deflection Analysis– Stress Analysis– Deformation Analysis
• Top fixed• Force applied to bottom
of legs– Force applied = 45lbs– Force = Weight of plane
•Max Deflection .0196 in•Stress Max 1.651 Psi
Final Plane
Budget
Item Company Name Unit Price Quantity Total Price
1 Pro CA+ Glue Tower Hobbies 11.99 3 35.97
2 Balsa Sheet Tower Hobbies 11.99 3 35.97
3 Fuel Filter Tower Hobbies 2.79 1 2.79
4 Carbon Fiber Tubing GraphiteStore.com 47.60 2 95.20
5 RX NICD Battery Tower Hobbies 18.39 1 18.39
6 Monocot Tower Hobbies 9.99 4 39.96
7 Glow Plug #8 Tower Hobbies 5.49 1 5.49
8 Aircraft Plywood Ridgefield Hobby 12.45 1 12.45
9 Light Plywood Ridgefield Hobby 5.00 2 10.00
10 Wooden Dowels Ridgefield Hobby 5.75 1 5.75
11 Balsa Bars Ridgefield Hobby 9.75 1 9.75
12 Nose Cone America's Hobby Center 6.40 1 6.40
13 Nuts, Bolts, Screws Home Depot 10.43 1 10.43
Subtotal 288.55
14 Engine .61FX w/ Muffler Tower Hobbies 144.99 1 144.99
15 RealFlight Simulator Tower Hobbies 199.98 1 199.98
Total 633.52
Testing
Problems/Suggestions
• Design Changes– Have to alter design somewhat once
construction is started
• Construction vs. Drawings
• Attachments
Goals
• Compete in June
Website
Summary
• Objectives • Schedule• Design Concept Summary • Construction
– Wing– Fuselage– Tail– Landing Gear– Boom
• Testing• Problems/Suggestions• Competition Goals• Website