Excel Spreadsheet for Battery Calculations - PowerPoint

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					      Group 13
Heavy Lift Cargo Plane
           Stephen McNulty
       Richard-Marc Hernandez
            Jessica Pisano
             Yoosuk Kee
               Chi Yan

     Project Advisor: Siva Thangam
                       Overview
 Objectives
 Schedule

 Progress

 Design Concepts and Analysis
    –   Wing
    –   Fuselage
    –   Tail
    –   Landing Gear
   Goals
                   Objectives
   Competition Specs are finally posted for the 2004
    competition
   The plane meets the specifications of the 2004
    SAE Aero Design West competition
   Construct the plane to design specifications
   Test the plane and make optimizations
   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
Schedule
               Rules Comparison
  Design Specifications:   This Year (2004)   Previous Year (2003)

       Wing Span            Minimum 10 ft        Maximum 6 ft

      Wing Chord             No restriction      Maximum 1 ft

     Planform Area           No restriction    Maximum 1200in2

     Cargo Volume          Minimum 120 in3     Minimum 300 in3

Maximum Takeoff Distance         200 ft              200 ft

Maximum Landing Distance         400 ft              400 ft

         Engine               .61 FX-OS         .61 FX-OS or
                                               K&B .61 R/C ABC
         Battery           Minimum 500 mAh    Minimum 500 mAh
                  Approach
2003                    2004
 Limited wing           Unlimited wing
  planform area           planform area
                         Limited thrust
 Limited lift force
  produced                force produced
                         Optimize:
 Optimize:
                            – Wing span
    – Fuselage design       – Fuselage design
    – Materials used        – Materials used
   Goal:                  Goal:
    – Minimum drag          – Minimum weight
    – Minimum weight
             Design Achievements
 Breaking down the plane into smaller
  components
 Brainstorming different ideas for designs
 Team divided into smaller groups
 Areas studied in smaller group:
    –   Selection of airfoil
    –   Selection of wing shape
    –   Tail stabilizer (both horizontal and vertical)
    –   Landing gear analysis
    –   Fuselage design
   Detailed design of aircraft finalized
           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
             Sample Equations
                 Landing Run Distance

   Differential Equation of                 dS 
                                                   VdV
    Motion                                        A  BV 2
                                        1  B 2 
                           S landing    ln 1  VTD 
   Landing ground   runway            2B      A    
                                         T                  
                                   A  g  static  Crolling   0.966 ft / sec 2
                                          W                 
   Coefficients A and B
                                   B   Ap C D , g  CrollingC L , g 
                                       g 1                              
                                       W 2                              
                                                     1
                                                   2
                                         W         
   Stall Velocity        Vstall   
                                     1 A C
                                                      25.8494 ft / sec
                                                    
                                         p L , max 
                                    2              
            Sample Excel Caculations
Horizontal tail:                     Vertical Tail:



Re (NACA 0012)     175975.6          Re (NACA0012)      246365.9


chord (MAC)              7    in     chord (MAC)             9.8   in

Swet                     0    in^2   Swet                    189   in^2

Wing Span               40    in     Tail height              24   in

Sref                   280    in^2   Sref                  235.2   in

Clmax                    0           Clmax

Cf (laminar)       0.003166          Cf (laminar)       0.002675

t/c                    0.12          t/c                    0.12

x/c                   0.287          x/c                   0.287

FF                 1.271607          FF                 1.271607

Cdmin (laminar)          0           Cdmin (laminar)   0.0027339
     CAD model Achievements
 Team  finished Computer Aided
  Design on the aircraft with
  SolidWorks
 Animations were created

 Blueprint of the aircraft ready to be
  printed
                     Plane Design
Riser:
Selig 1223
Balsa Wood
Riser construction
Dihedral

Tail:
NACA 0009
Balsa Wood
Riser construction
Wing Construction
      Balsa Wood Risers
      Bass Wood Spars
      Dowel Leading Edge
      Balsa Wood Trailing Edge
      Horner Plate
                       Fuselage
Fuselage:
•Wooden panels
•Cargo bay (payload)                                           Fuselage cover
•Compartments
•Easily accessible



                                                                   Fuselage base


                                                           Payload

                                             Battery/ Receiver /Fuel tank

                               Engine: O.S. .61FX




                         Prop/ Nose
                        Tail Boom




Tail Boom:
•Carbon fiber tube
•Attached to fuselage
•12 degree incline
                  Plane Design
Landing gear:
•Aluminum
•Connecting Rod
•¾ in Tires
Final Design
                                Materials Budget
                 Material                          Size       Quantity     Item #      Cost
Balsa Sheets (16)                               1/16x4x36        3        TOWR1315    $11.99
Square Stick                                  3/8"x3/8"x36"      4        WOO408       $1.55
Wooden Dowel                                     1/4x36"         4        WOO363       $0.75
Trailing edge (8)                             3/8"x3/8"x36"      2        TOWR1655     $2.59
Plywood                                        1/16x12x24"       8        WOO392       $9.90
Composite                                         4.5 ft         1           *        $80.00
Foam Core                                            -           1           *        $80.00
Aluminum Plate                                       -           1           *        $20.00
Tires                                              3/4in         3           *         $4.29
Connecting Rods                                    48in          1         LXD863      $3.79
Engine                                           O.S. 61         1           *        $150.00
Props                                              11x7          1           *         $2.49
Servo                                                -           5           *        $21.00
Fuel Tank                                          22oz          1           *         $3.49
Battery                                          600mAh          1           *        $20.00
Radio Receiver                                   6 channel       1           *        $80.00
Controller                                       6 channel       1           *        $99.00

                                                                           Total
                                                                                     $786.19
                                                                         Semester
Items denoted with * for item number are already in stock                  Total     $133.34
Equipment Budget
                       Quanti   Item
       Equipment         ty     Cost


      Hobby Knife        3      $3.19


    #11 Blades (100)     1      $12.99


    ProCA+ Clue 4oz.
            Med.         3      $18.39


   Mono Cote Maroon      2      $7.49


       Mono Cote
         Aluminum        2      $7.49



         Misc.                  $50.00

                       Tot
                                $157.6
                        al           9
                    Goals
 This   Semester
  – Complete construction early
  – Test plane design
  – Modify to optimize
 Compete    in June
                       Summary
 Objectives
 Schedule
 Last Semester’s Achievements
 Design
    –   Risers
    –   Wing
    –   Fuselage
    –   Tail
    –   Landing Gear
   Goals
Thank You

				
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