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Group 13 Heavy Lift Cargo Plane

Group 13 Heavy Lift Cargo Plane. Stephen McNulty Richard-Marc Hernandez Jessica Pisano Yoosuk Kee Chi Yan Project Advisor: Siva Thangam. Overview. Objectives Schedule Design Concept Summary Construction Wing Fuselage Tail Landing Gear Boom Testing Problems/Suggestions

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Group 13 Heavy Lift Cargo Plane

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  1. Group 13 Heavy Lift Cargo Plane Stephen McNulty Richard-Marc Hernandez Jessica Pisano Yoosuk Kee Chi Yan Project Advisor: Siva Thangam

  2. Overview • Objectives • Schedule • Design Concept Summary • Construction • Wing • Fuselage • Tail • Landing Gear • Boom • Testing • Problems/Suggestions • Competition Goals • Website

  3. 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

  4. 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

  5. Design Specs Comparison

  6. Schedule 2nd Semester

  7. Schedule 1st Semester

  8. 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

  9. Sample EquationsLanding Run Distance • Differential Equation of Motion • Landing ground runway • Coefficients A and B • Stall Velocity

  10. Sample Excel Calculations

  11. Payload Weight vs. Density Altitude [Payload Weight] = 20.60 – 5.15E-4 × [Density Altitude]

  12. Wing Design and Construction

  13. Rib • Selig 1223 • SolidWorks Drawing • Print and cut original • Metal cut out template • Final for placement in wing

  14. Airfoil • Airfoil selection • Year 2000: E 211 • Year 2001: E 423 • Year 2002: OAF 102 • Research: E 214 • Research: S 1223

  15. CL&CD vs.AoA Control Surface Affect

  16. Wing Stress Analysis Max stress = 330.9 psi

  17. Wing • 10 ft wing span • 1 ft cord • Flap 3 ft

  18. Fuselage • Shortened to 2’-1” long • Made from plywood and balsa wood • Attached to boom externally Old design New design

  19. Boom Three Spar • Connects tail to fuselage • Two Booms create wobble • Carbon Fiber • 5ft length • ½ in inner Diameter

  20. Tail Section • NACA 0012 Airfoil • Similar Construction to Wing • Controls: • Horizontal Stabilizer • Vertical Flaps

  21. Tail Section • Wooden Beam to Carbon Fiber Attachment • Design Limits tail AoA • Servos built inside tails

  22. 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

  23. Final Plane

  24. Budget

  25. Testing

  26. Problems/Suggestions • Design Changes • Have to alter design somewhat once construction is started • Construction vs. Drawings • Attachments

  27. Goals • Compete in June

  28. Website

  29. Summary • Objectives • Schedule • Design Concept Summary • Construction • Wing • Fuselage • Tail • Landing Gear • Boom • Testing • Problems/Suggestions • Competition Goals • Website

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