1 / 15

SAE Brazil AeroDesign Challenge

SAE Brazil AeroDesign Challenge. Florida International University Department of Mechanical and Materials Engineering. Miguel Jimenez Ricardo Lugo Carlos Rojas Advisor: Andres Tremante. Overview. Problem Statement Competition Background Metrics Design Alternatives Wing Design

dillon
Download Presentation

SAE Brazil AeroDesign Challenge

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. SAE Brazil AeroDesign Challenge Florida International University Department of Mechanical and Materials Engineering Miguel Jimenez Ricardo Lugo Carlos Rojas Advisor: Andres Tremante

  2. Overview • Problem Statement • Competition Background • Metrics • Design Alternatives • Wing Design • Proposed Design • Stability and Servos • Timeline

  3. Problem Statement • Designing a remote-controlled aircraft for a competition in São Paulo, Brazil in late 2010. • Aircraft should lift the most possible weight with predefined constraints. • Competition is hosted by SAE Brazil, where universities from all around the globe meet for this event.

  4. Competition Background • Flight Path: • Airplane must take off within 61 meters • Land within 122 meters. * Image courtesy of SAE Brazil

  5. Metrics of Design • SAE Brazil sets the maximum dimensions for the aircraft according to the following formula: D: total dimension L: distance from front to back measured linearly H: maximum height (without propellers) Bi: span of lift-generating components n: number of lift-generating components

  6. Metrics of Design • Maximum weight: 20 kg, including gasoline

  7. Engine Specifications • Engine: O.S .61 FX • Specifications: • Displacement: 0.607 (cu in) • 1.9 horsepower at 16,000 RPM • RPM: 2,000-17,000 • Weight: 19.4 oz. • 0.866” stroke • MSRP: $170.00

  8. Design Alternatives • For an R/C aircraft, the most critical component is the wings. In this sense, the fuselage is not as critical as in full-size airplanes, therefore its design is less rigorous.

  9. Wing Design Parameters

  10. Proposed Design • Wing Type: Straight • Wing Position: High Wings (above fuselage) • Other Wing Considerations: Straight Dihedral • To be determined with CFD analysis

  11. Stability and Servos • Four servos will control the airplane’s attitude: Thrust, Yaw, Pitch, and Roll • Empennage • Yaw • Rudders • Pitch • Elevators • Wing • Roll • Ailerons

  12. Timeline

  13. Division of Responsibilities • Miguel Jimenez • Aerodynamic Design • Computational Fluid Dynamics • Propulsion Calculation • Prototype Construction • Ricardo Lugo • Aerodynamic Design • Control and Stability • Prototype Construction • Carlos Rojas • Radio Control survey • Servos and Channels • Competition parameters • Prototype Construction

  14. Conclusion • Structural Design and CFD analysis is planned for May-June 2010, months before the competition • Wing Design needs dihedral angle CFD testing before modeling • Funding is a key for prototype construction

  15. The End

More Related