Transcript Slide 1

Group 13
Heavy Lift Cargo Plane
Stephen McNulty
Richard-Marc Hernandez
Jessica Pisano
Yoosuk 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 wingspan
120 inches
Takeoff limit
200 feet
Landing Distance
400 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 Comparison
Design 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 or
K&B .61 R/C ABC
Battery
Minimum 500 mAh
Minimum 500 mAh
Schedule 2nd Semester
Schedule
st
1
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 Equations
Landing Run Distance
• Differential Equation of
Motion
VdV
dS 
A  BV 2
• Landing ground runway
1  B 2 
S landing 
ln 1  VTD 
2B 
A

• Coefficients A and B
• Stall Velocity
T

A  g  static  Crolling   0.966 ft / sec 2
 W

g 1

B   Ap C D , g  CrollingC L , g 
W 2



W
Vstall  
 1 A C

p L , max
2
1
2


  25.8494 ft / sec



Sample Excel Calculations
Horizontal tail:
Re (NACA 0012)
Vertical Tail:
175975.6
Re (NACA0012)
246365.9
chord (MAC)
7
in
chord (MAC)
9.8
in
Swet
0
in^2
Swet
189
in^2
in
Tail height
in^2
Sref
Wing Span
Sref
Clmax
Cf (laminar)
40
280
0
0.003166
24
in
235.2
in
Clmax
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
Payload Weight [lds]
20.7
20.6
20.5
20.4
20.3
20.2
20.1
20
0
200
400
600
800
1000
1200
Density Altitude [ft]
[Payload Weight] = 20.60 – 5.15E-4 × [Density Altitude]
Wing Design and Construction
Rib
•Selig 1223
•SolidWorks Drawing
•Print and cut original
•Metal cut out template
•Final for placement in wing
Airfoil
S1223
OAF102
E423
Year 2000: E 211
Year 2001: E 423
Year 2002: OAF 102
Research: E 214
Research: S 1223
E214
–
–
–
–
–
E122
Important Factor
• Airfoil selection
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
Control
Surface Affect
Coefficient of Lift
No Flaps
Flaps +15
Flaps -15
3.5
coefficient of lift
3
2.5
2
1.5
1
0.5
0
-5
0
5
10
15
angel of attack
Coefficient of Drag
No Flaps
Flaps +15
Flaps -15
0.12
0.1
coefficient of drag
CL&CD
vs.
AoA
0.08
0.06
0.04
0.02
0
-5
0
5
angle of attack
10
15
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
New design
externally
Old design
Boom
Three 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