Group 3Heavy Lift Cargo Plane

William Gerboth, Jonathan Landis, Scott Munro, Harold Pahlck

December 21, 2009

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

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

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

Phase I Summary

• Design concepts were decided upon– Airfoil Shape: Eppler 423– Wing Shape: Straight– Landing Gear: Tricycle– Tail shape: T-Tail

Phase II Summary• Calculated drag, lift, takeoff distance, & landing

distance• Used equations from textbooks, White paper, online

– Drag

– Takeoff

– Landing

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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 C_L vs. AoA

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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

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.

Technical Analysis: Tail Analysis

• The tail was analyzed for withstanding a 3ft drop and drag forces

• Max Stress: 290 PSI• Max Displacement: .046 in

Technical Analysis: Landing Gear

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

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

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Equipment Selection

• Engine– 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

Prototype Fabrication Plan

Updated Budget

Item Estimated

CostAvailable Final

Cost

SAE Membership $40 No $40

SAE Registration $600 No $600

R/C Controller $200 Yes $0

Engine w/ muffler $180 Yes $0

Propeller $20 Yes $0

Tires/Axle $10 Yes $0

Batteries $20 Yes $0

Servos $100 Yes $0

Push Rods $10 Yes $0

Fuel Tank $5 No $5

Balsa/Glue/Monokote $150 Yes $75

Travel $2,000 No $2,000

Misc. $139 No $139

Total $3,474 $2,859

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

Title: Heavy Cargo Lift Plane Team Members: William Gerboth, Scott Munro, Jonathan Landis, Harold Pahlck Advisor: Professor Siva Thangam Project #: 3 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 HighlightsAirfoil ProfileLift ForceTake-off and LandingEase of ConstructionStall AngleDragDurable

• 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.

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 #: 3 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 11.86 pounds• Estimated payload of 23 pounds• Plane weight of 12 pounds

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 #: 3 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

ME 423 Phase III Nugget Chart – Analysis & Engineering Design