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