Group 3 Heavy 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

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

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 C.G

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

Prototype Fabrication Plan

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

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

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: 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.

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: 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 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 #: 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