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AeroCats Team #006

AeroCats Team #006. SAE AeroDesign East 2006 21-23 April 2006 Regular Class. Team Members. Outline. Mission Basic Configuration Aerodynamics Structural Design Weights & Balance Stability & Controls Propulsion Performance & Optimization Conclusion. Mission.

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AeroCats Team #006

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  1. AeroCats Team #006 SAE AeroDesign East 2006 21-23 April 2006 Regular Class

  2. Team Members

  3. Outline • Mission • Basic Configuration • Aerodynamics • Structural Design • Weights & Balance • Stability & Controls • Propulsion • Performance & Optimization • Conclusion

  4. Mission The mission of the group defines the motivating factors behind the effort and time spent on this design project

  5. Mission • Gain a much deeper understanding of the progression from conception to fabrication of an aircraft • Score the most points at the SAE AeroDesign East competition • Require $0.00 out-of-pocket from the students involved

  6. Software MathCAD SolidWorks Rhinoceros 3D XFLR5 Athena Vortex Lattice (AVL) Microsoft Project Processes Composite Lay-up Monokote + Balsa R/C Electronics Small Gas Engines Airfoil Design Mission

  7. Mission Raw Weight Score = Actual Payload*4 Prediction Bonus = 20 – (Predicted Payload – Actual Payload)^2 Score = Raw Weight Score + Prediction Bonus

  8. Mission ADVERTISING/COPIES: $ 359.76 TRANSPORTATION: $ 950.41 GAS/OTHER RELATED TRANSPORTATION COSTS: $ 440.00 HOTEL/LODGING: $ 1,290.24 FOOD/BEVERAGES: $ 1,800.00 COMPETITON REGISTRATION: $ 350.00 CONSUMABLES: $ 1,764.93 DURABLE GOODS: $ 1,036.42 TOTAL $ 7,991.76

  9. Basic Configuration Entails a three dimensional model of the propulsion system and the entire aircraft structure

  10. Basic Configuration Propulsion System

  11. Basic Configuration (clearly in the works)

  12. Basic Configuration

  13. Aerodynamics Defining the main wing, tail, and airfoil geometries and determining aerodynamic coefficients

  14. Aerodynamics • MAIN WING • Required Wing Span • 94.488 ± 0.5 in • Wing Area Decrease → AR Increase • High Lift Airfoils • Advantages • Reduced wing area • Increased AR • Disadvantages • Tend to have higher Cm • Increased tail size

  15. Aerodynamics • Airfoil: Eppler E423 • Advantages • High Lift • Low Re • Low Wing Area • Higher AR • Ease of Construction • Disadvantage • High Cm • Large Tail • 2D Analysis: XFOIL • Finite Wing Analysis: VLM • XFLR5 • Combines XFOIL and VLM • Athena Vortex Lattice (AVL) • Stability and Control • 4.5° Dihedral

  16. Aerodynamics

  17. Aerodynamics Re = 300,000 • TAIL • NACA 0014 (0012 maybe?) • Relatively High CL • Widest of Drag Buckets Viewed • Allows for smaller elevator • Produces minimal CD throughout operating conditions • 2D XFoil Data

  18. L/D Max: 8.1 Stall Max Climb Lift Off L/D Max L/D Max Lift Off Max Climb Stall Aerodynamics Lift and Drag Polars

  19. Aerodynamics Lift and Drag Polars Stall Stall Max Climb Lift Off Max Climb L/D Max Lift Off L/D Max whoopsy-doodles

  20. Structural Design Insert this later ELISE

  21. Structural Design Main Wing Spar Structure Options • D spar • Pros • Hold leading edge shape • Lighter (number) • Cons • Requires possible second spar (at least by ailerons) • Torsion may become a factor

  22. Structural Design Main Wing Spar Structure Options • Box • Pros • Reduces torsion • Accounts for first and second spars • Cons • More structure • Still requires material to hold leading edge shape

  23. Structural Design Main Wing Spar Structure Options • Foam • Pros • Pink • Lighter (number) • Cons • Blue • I hate foam

  24. Structural Design Main Wing Structure • D spar • Weight: 2 lbs • Pink Foam Wing • Weight: 3.8 lbs • Spyder Foam Wing • Weight: 5.4 lbs

  25. Structural Design Main Wing Spar • Carbon Fiber or Fiber Glass • Placed at quarter chord • Height • Minimum Thickness • Wing loading • Shear and bending strength (pictures…..or else)

  26. Structural Design Horizontal Tail Structure • Spyder Foam Core • Strong in shear and compression • Fiber Glass Veil Composite Skin

  27. Structural Design • This needs a conclusion • Or say “ongoing” or some BS

  28. Weights and Balance Defining the center of gravity to enable stability and performance benefits

  29. Stability and Controls Enabling steady flight at all times during the competition

  30. Stability and Controls Moment vs. Alpha Cm as a function of AOA for three elevator deflections: 0º, and ± 5º Cm as a function of AOA for three centers of gravity: nominal CG ± 1 inch whoopsy-doodles

  31. Stability and Controls • Aircraft meets the Level 1, Class 1, Category B requirements for level flight and Category C requirements for landing • The Dutch Frequency and Dampening ratio: ~Wdr=2.3322 (rads/s) ~zdr=0.4636 • The Phugoid frequency and Dampening ratio: ~Wnp=4.95 (rads/s) ~znp=0.216 • Spiral Mode: ~

  32. Propulsion The propulsion group defines the performance characteristics of the engine through rigorous experimental testing and thorough numerical investigation.

  33. Propulsion Requirements Engine OS .61 FX engine with E-4010 Muffler Engine tear-down and inspection may be performed Gear boxes, Drives, and Shafts A one-to-one propeller to engine RPM must be maintained Competition Supplied Fuel Common grade, ten percent (10%) nitro methane fuel Fuel Tanks May be pressurized by a stock fitting on the engine muffler only Gyroscopic Assist Prohibited No gyroscopic assist of any kind is allowed

  34. Propulsion • Compression Ratio = 9 • Displacement = .607 in3 • Rated RPMs = 16,000 RPM

  35. Propulsion • Static Torque test stand for data acquisition and model validation

  36. Propulsion Propeller • Prop Thrust = 11.2 lbf • Prop Power = 1.44 hp • Prop diameter = 14.2 in • 14.5x4 Cam Prop from Graupner

  37. Propulsion Propulsion Model • Blade tip Mach number is 0.5769 • Matched power = 1.01 hp • Matched thrust = 8.85 lbf

  38. Propulsion Fairing • Drag reduction • Directed air intake • Directed exhaust

  39. Propulsion • Static stand • Torque • Thrust • RPM

  40. Propulsion • Dynamic stand • Thrust with fuselage skin friction • Tests for servo actuation

  41. Performance Investigating the benefits and disadvantages of the proposed design (i.e. Optimized beyatch)

  42. Proposed Trade Study Weight that intersects limits will give max design weight Performance

  43. Extra Thrust for accel Max Velocity Performance • Thrust and Drag versus Velocity • Acceleration • Gives maximum velocity

  44. Flight Plan Times manuevers Ensures enough velocity to make turns Performance

  45. Backup slides

  46. Performance

  47. J8J Jonesyfoil

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