1. Group 3 Heavy Lift Cargo Plane
William Gerboth, Jonathan Landis, Scott Munro, Harold Pahlck December 21, 2009

2. Presentation Outline Project Objectives Competition Update
Phase I Summary
Phase II Summary
Design Approaches
Technical Analysis
Equipment Selection
Prototype Fabrication Plan
Updated Budget
Nugget Charts

3. Project Objectives
Design and build an airplane to successfully compete in the SAE Aero East competition
Plane must successfully take off from a runway of 200 feet and land on a runway 400 feet
Constraints of 55 pounds total weight, and the combined height, length, and width of 200 inches
Plane must make one complete 360° circuit of the field per attempt

4. Competition Updates Aero Design East competition is full
As of now Aero West is still open
In order to compete
Submission of design report with plans and payload prediction before January 21, 2010
Aircraft must be constructed and tested by February 22, 2010
Decision not to compete
Time needed to complete report and construct airplane

5. Phase I Summary Design concepts were decided upon
Airfoil Shape: Eppler 423
Wing Shape: Straight
Landing Gear: Tricycle
Tail shape: T-Tail

6. Phase II Summary
Calculated drag, lift, takeoff distance, & landing distance
Used equations from textbooks, White paper, online
Drag
Takeoff
Landing

7. Design Approaches CL vs. Angle of Attack CL available from Eppler 423
Determined flap angle of 8 deg. to prevent stall
CL,max = 1.4

8. Technical Analysis: Wing Loading
Wing subject lift force
Non uniform distributed load
22.5 lbs per wing
Max Stress = 886 psi
Yield Strength = 2000 psi
Max Displacement = 1.57 in

9. Technical Analysis: Fuselage Loading
Fuselage tested for relative strength
Cantilever static analysis done
Force of 1 lb used to test strength in x-y and x-z directions
Max Stressx-y= 314 psi
Max Stressx-z= 156 psi
Max Displacementx-y = .084 in.
Max Displacementx-z= .083 in.

10. Technical Analysis: Tail Analysis
The tail was analyzed for withstanding a 3ft drop and drag forces
Max Stress: 290 PSI
Max Displacement: .046 in

11. Technical Analysis: Landing Gear
Landing gear tested to withstand a 3ft drop
Max Stress: 22,874 PSI
Max Displacement: .023 in

12. Technical Analysis: Stability & Control
Longitudinal Static Stability
Criteria: Static Margin Must be Positive
Static Margin = hn- h
Neutral Point = hn =
Tail Volume Ratio =
Center of Gravity = h
Solidworks Used to Calculate C.G

13. Equipment Selection Engine Fuel Tank Propeller Servos
O.S. .61FX with E-4010 Muffler
Fuel Tank
Great Planes Fuel Tank 12 oz.
Propeller
APC 14x4W Propeller
Servos
5G TowerPro SG50 Micro RC Servos

14. Prototype Fabrication Plan

15. Updated Budget Item Estimated Cost Available Final Cost SAE Membership
$40 No
SAE Registration
$600
R/C Controller
$200
Yes $0
Engine w/ muffler
$180
Propeller
$20
Tires/Axle
$10
Batteries
Servos
$100
Push Rods
Fuel Tank $5
Balsa/Glue/Monokote
$150
$75
Travel
$2,000
Misc.
$139
Total
$3,474
$2,859

16. Plan for Phase IV Do further analysis on final design
Build and analyze a small scale airfoil for testing in the wind tunnel
Begin construction
Devise a testing plan

17. ME 423 Phase I Nugget Chart – Proposal & Conceptual Design
Title: Heavy Cargo Lift Plane Team Members: William Gerboth, Scott Munro, Jonathan Landis, Harold Pahlck Advisor: Professor Siva Thangam Project #: Date: 9/30/09
Project Objectives
Design and build an airplane that conforms to the SAE competition rules and regulations.
Plane must navigate a 360 degree after taking off from within a 200 foot runway, and then land successfully on a runway of 400 feet.
Constraints of 55 total pounds and a height, width, and length of 200 inches must be followed.
Conceptual Designs and Highlights
Airfoil Profile
Lift Force
Take-off and Landing
Ease of Construction
Stall Angle
Drag
Durable
Why This Project and State-of-the-art
A high lift ability to plane weight ratio is ideal for cargo, military, and medical transportation because cost will be reduced without sacrificing performance.
The technology can also be applied to unmanned aerial vehicles for military use.
Drawing and Illustration of Promising Concepts
Eppler 423 airfoil
What Are the Key Areas/Aspects to Solve
Lift force must be maximized from the wing design
Limited to the FX OS 0.61 engine which produces approximately 1.9 hp.
Design needs to maximize the weight that can be lifted while minimizing the weight of the plane.

18. ME 423 Phase II Nugget Chart – Design Selection and Technical Analysis
Title: Heavy Cargo Lift Plane Team Members: William Gerboth, Scott Munro, Jonathan Landis, Harold Pahlck Advisor: Professor Siva Thangam Project #: Date: 11/12/09
Project Objectives
Design and build an airplane that conforms to the SAE competition rules and regulations.
Plane must navigate a 360 degree after taking off from within a 200 foot runway, and then land successfully on a runway of 400 feet.
Constraints of 55 total pounds and a height, width, and length of 200 inches must be followed.
Results Obtained at This Point
Types and Focuses of Technical Analysis
Force analysis of structural members of wing, tail, and fuselage.
Stress analysis of materials to use for structural members
Deflection tests of landing gear
Static analysis for wing and tail design
Aerodynamic analysis to maximize lift and minimize drag
Propeller design to maximize the power available in the engine
Drawing and Illustration (about technical analysis performed)
Design Specifications
Wing span of 120 inches
Overall length of 68 inches
Height of 12 inches
Thrust of pounds
Estimated payload of 23 pounds
Plane weight of 12 pounds

19. ME 423 Phase III Nugget Chart – Analysis & Engineering Design
Title: Heavy Cargo Lift Plane Team Members: William Gerboth, Scott Munro, Jonathan Landis, Harold Pahlck Advisor: Professor Siva Thangam Project #: Date: 12/15/09
Project Objectives
Design and build an airplane that conforms to the SAE competition rules and regulations.
Plane must navigate a 360 degree after taking off from within a 200 foot runway, and then land successfully on a runway of 400 feet.
Constraints of 55 total pounds and a height, width, and length of 200 inches must be followed.
Results Obtained in the Semester
Height of 12 inches, Length of 68 inches
Wingspan of 120 inches, Chord length of 12 inches
Eppler 423 airfoil for main wing
NACA 0012 airfoil for tail wing
Coefficient of lift max = 1.4
Propeller of 14” diameter x 4.5” pitch
Takeoff distance = 190 at 46.5 ft/s and 25 pounds
Technical Analysis (cont.)
Stress analysis of materials
Aerodynamic analysis to maximize lift and minimize drag
Propeller design to maximize the power available in the engine
Drawing and Illustration
Engineering Design
Solidworks and COSMOSworks analysis
Confirmed analysis through Excel calculations
Prototype Plan and Purchase Requisition
Updated budget to exclude recycled materials
Took inventory of existing materials
Budget without travel is $859
Begin ordering and then construction