Heavy Lift Cargo Plane Proposal Presentation

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

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

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Project Review
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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

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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

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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

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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

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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

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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

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Design Refinement Calculation
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Calculation of Aileron Size

• Calculation adapted from Perkinss 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

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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

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Calculation of Aileron Size

• Coefficient is used to calculate aileron size

• Cld Change in Rolling Coefficient with aileron
  angle
• t Aileron Effectiveness
• da Elevator Deflection
• Clp Damping Derivative

• All coefficients are presented in graphical form
  in NACA report 635

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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
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Calculation of Aileron Size
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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

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Construction First Steps
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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

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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

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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
  addl 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)

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Wing Interior Configuration
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Tailboom Configuration

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

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Project Scheduling Budgeting
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Gantt Chart
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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

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Budget
Spent () Anticipated ()
Hardware 431.62 400.00
Competition 350.00 TBD
Depends largely on the purchase of a new
remote Depends upon many variables such as
- Early reservations - Number of attendees -
Transportation expenses
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To Be Continued...

• Final Design
• Report for SAE competition
• Construction
• Plans for testing

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Questions?Comments?