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Heavy Lift Cargo Plane Proposal Presentation

February 17 th , 2005. Matthew Chin. Heavy Lift Cargo Plane Proposal Presentation. Aaron Dickerson. Brett J. Ulrich. Tzvee Wood. Advisor: Prof. S. Thangam. Coming Up. Review previous work on the project New, refined calculations First steps for construction Interior configurations Wing

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Heavy Lift Cargo Plane Proposal Presentation

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  1. February 17th, 2005 Matthew Chin Heavy Lift Cargo PlaneProposal Presentation Aaron Dickerson Brett J. Ulrich Tzvee Wood Advisor: Prof. S. Thangam

  2. Coming Up... • Review previous work on the project • New, refined calculations • First steps for construction • Interior configurations • Wing • Tailboom • Project Scheduling & Budget

  3. Project Review

  4. Project Objective Review • Design and build a remote controlled, “heavy lift” aircraft for competition • Society of Automotive Engineers Aero East Design, April 8th-10th, 2005 • Regular Class Competition • Standard Engine: OS 0.61X • Wing Span Limit: 5 ft • No Planform Area Restriction • Maximum Take Off Distance: 200ft • Maximum Landing Distance: 400ft

  5. Recap of Design VII • Performed calculations for the design of: • Primary airfoil size • Takeoff and landing distances • Tailplane stabilator size • Selected airfoil/tail plane profiles: • Airfoil: Eppler 423 • Stabilator: NACA 0012

  6. Recap of Design VII • Wing Design & Material Selection: • Balsa wood ribs • Lite plywood reinforcement • Carbon fiber support rods • Stabilator Design & Material Selection: • Entirely made of foam core • Solid piece simplifies construction

  7. Recap of Design VII • Registered all 4 members and advisor for the April 8-10 competition • Examined previous construction problems • Evaluated methods to avoid experiencing similar occurrences during construction

  8. Overcoming Fabrication Problems • Previous year utilized a high-lift Selig foil • Lifting condition relies on a very fine trailing edge • Poor construction of foil can severely hinder performance • Eppler 423 foil trailing edge is easier to construct • Landing gear & Engine mount construction eliminated; parts available commercially

  9. Initial Parts Order • Varying sizes of balsa sheets, lite plywood • Carbon fiber rods • Dubro Treaded wheels • Ohio Superstar Cover Tugger • Top Flite Monokote Hot Sock Iron Cover • Sealing Iron/Hot Sock Combo • Top Flite Hot Glove Covering Tool • Top Flite Trim Seal Tool • Top Flite Monokote SmartCut Trim Tool • Top Flite Monokote Trim Solvent • Dubro Super Strength Landing Gear

  10. Design Refinement: Calculation

  11. Calculation of Aileron Size • Calculation adapted from Perkins’s Airplane Performance & Control & NACA TR 635 • Non-dimensional parameter for lateral control • p: rate of roll (rad/s) • b: wing span (ft) • V: true speed (ft/s) • Typical Values: Cargo/Bombardment: 0.07 Fighters: 0.09

  12. Calculation of Aileron Size • Lower maneuverability coefficient required for this project • Smaller ailerons result in larger fixed wing surfaces • Will not be performing aerobatics, or performing military operations • Chose coefficient value of 0.035

  13. Calculation of Aileron Size • Coefficient is used to calculate aileron size: • Clδ: Change in Rolling Coefficient with aileron angle • τ: Aileron Effectiveness • δa: Elevator Deflection • Clp: Damping Derivative • All coefficients are presented in graphical form in NACA report #635

  14. Calculation of Aileron Size Change in Rolling Coefficient per Degree divided by Elevator Effectiveness Elevator Effectiveness vs. Aileron Chord/Wing Chord Ratio Damping Coefficient as a function of Aspect Ratio

  15. Calculation of Aileron Size

  16. Calculation of Aileron Size • EES software used for calculations • Two variables had to be solved for • Aileron Chord • Aileron Span • Parametric studies conducted with varying aileron span • Final Sizing: • Chord: 6.5 in, 27% of Wing Chord • Span: 40% of Wing Semi-Span • Rules of thumb: • Chord: 15-30% of Wing Chord • Span: 25-30% of Wing Semi-Span

  17. Construction: First Steps

  18. Wing Construction • Use templates to cut balsa wood ribs • Use X-Acto knife or balsa cutter for manufacturing • Assemble one side of wing, then place on a 1.5° angle for dihedral design

  19. Wing Construction • Ailerons to be attached to third support spar • Aileron hinge placed at 5.418 inches from trailing edge (To be explained) • Lite plywood used for ribs in the central portion of the wing • Stronger fuselage attachment • Better overall wing stability

  20. Rib Template • Wing Dimensions: • Chord increased by 4 in. to 24 in. • More overall lift due to increased wing area • Increase in total lift greater than effect of add’l weight • Allows a greater margin of error • Span: 60 in. • Template made out of 1/8 in. Aluminum • Nine ribs per wing semi-span extending beyond fuselage • Holes placed at 4 inches and 12 inches from leading edge for carbon fiber support spar • Additional carbon fiber spar at 5.418 inches from trailing edge (used as pivot for ailerons)

  21. Wing Interior Configuration

  22. Tailboom Configuration • Balsa wood • I-Shape reinforcements • Allows for slight twist • Decreases shear stress • Plywood components still under consideration

  23. Project Scheduling & Budgeting

  24. Gantt Chart

  25. Gantt Chart • Ahead of schedule in our Design refinement section • Debugged primary EES file • Boom design selected • Behind by approximately 1 week on construction phase • Rib template for main airfoil received • Most of the ordered parts came in • Major construction to begin during week of 2/20 • Engine mount and landing gear problems solved • SAE Report Submission due on March 1st is well underway

  26. Budget * Depends largely on the purchase of a new remote ** Depends upon many variables such as - Early reservations - Number of attendees - Transportation expenses

  27. To Be Continued... • Final Design • Report for SAE competition • Construction • Plans for testing

  28. Questions?Comments?

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