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 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 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 ftCWTgA rollingstatic

2BVAVdVdS

21ln

21

TDlanding VAB

BS

gLrollinggDp CCCA

WgB ,,21

sec/8494.25

21

21

max,

ftCA

WVLp

stall

Sample Excel CalculationsHorizontal 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]

Payl

oad

Wei

ght [

lds]

[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

  Important Factor

E122

E214

E423

OA

F102

S1223

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

ficie

nt o

f 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

ficie

nt o

f 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