1 / 50

AAE 451 Team V

Preliminary Design Review. AAE 451 Team V. Charlie Rush Zheng Wang Brandon Wedde Greg Wilson. Stephen Beirne Miles Hatem Chris Kester Jim Radtke. The Flying V Barn Owl. Outline. Market Design Requirements Present Concept Sizing Aerodynamics Performance Structures

smilo
Download Presentation

AAE 451 Team V

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. Preliminary Design Review AAE 451 Team V Charlie Rush Zheng Wang Brandon Wedde Greg Wilson Stephen Beirne Miles Hatem Chris Kester Jim Radtke The Flying V Barn Owl

  2. Outline • Market • Design Requirements • Present Concept • Sizing • Aerodynamics • Performance • Structures • Weight and Balance • Stability • Propulsion • Cost • Summary AAE 451 Team V

  3. GA Market Review • Product • 4 Seat Single Engine Piston Aircraft for Hobbyists, Training Fleets, and Fixed Base Operators • Powered by an Alternative Fuel • Customer Needs • 100LL Replacement • Current staple fuel for GA piston engines • Production uncertain after 2015 • Provides opportunity to be first to market • Petroleum fuel alternative for post peak oil AAE 451 Team V

  4. Design Requirements AAE 451 Team V

  5. Current Design The “Barn Owl” AAE 451 Team V

  6. Carpet Plot Stall (57 kts) Cruise (150 kts) Climb (1300 fpm) Takeoff (1500 ft) Aspect Ratio (increments of 0.5) Turn (n=2) Design Space Design point AR=10 Note: Sizing was done with a predetermined 200 hp engine AR=6 AAE 451 Team V

  7. I/O for Carpet Plot AAE 451 Team V

  8. New Airfoil Design • FVGA 5121-12.1% thick • Designed using Genetic Algorithm • Laminar flow • Large Laminar bucket • Performance comparable to 2412 when tripped • 30% less drag at cruise commpared to 2412 • Low penalty at high Cl AAE 451 Team V

  9. Wing Planform Design • Span = 33.87 • Taper ratio = 0.7 • Polynomial twist • Close to elliptical lift distribution • 1.51 degrees total twist AAE 451 Team V

  10. Cmarc Analysis • Used to acquire an accurate prediction of induced drag and parasite drag. • Detailed fuselage shaping to minimize interference drag • Bathtub style wing joint utilized, with smooth LE/TE junctions, possible with composite skin layover • 8 deg tail upsweep to minimize wake interference AAE 451 Team V

  11. CD0 Determination CD0 = 0.022 (Sref = 153) • Lower than Cessna 172 @ 0.027 • The FVGA5121 airfoil is laminar at low CL • Incompressible flight envelope • No wing struts • Aerodynamic fuselage • Close to elliptical loading AAE 451 Team V

  12. L/DMAX Determination L/DMAX = 10.4 • This is because the FVGA5121 airfoil is laminar at low CL • Most efficient cruise at 185 ft/s (109 kts) AAE 451 Team V

  13. 3D Lift Curve Wings oriented to have a level fuselage at max cruise speed. AAE 451 Team V

  14. Performance Design Limit Load 3.8 g per FAR 23.337 FAR Gust Velocities Under 20,000 ft 50 ft/s @ VCruise 25 ft/s @ VDive Design Loading Gust Loading AAE 451 Team V

  15. Performance AAE 451 Team V

  16. Structure • Material Selection • Aluminum frame with fiberglass skin selected • Cost savings expected • Slight weight savings achieved • Frame • “Big bones” approach • Manufacturing cost reduced due to fewer components and advanced joining • Skin • Fiberglass cured in large segments • Segments bonded to frame AAE 451 Team V

  17. Structural Layout I-Beam Spar C-Channels Ribs AAE 451 Team V

  18. Spar Carrythrough • Spar located at front of rear seats • Spar does not hinder cabin comfort AAE 451 Team V

  19. Component Weights • Began with Raymer’s Statistical Group Weights method • Replaced with known or calculated weights • Engine • Propeller • Wings • Fuselage AAE 451 Team V

  20. Component Weights • Engine • Total installed weight from DeltaHawk • Includes all pumps, turbocharger, lines, exhaust, and mount • 390 lbs • Propeller • Off the Shelf • 51 lbs AAE 451 Team V 20

  21. Wing Sizing • Cross-sectional optimization along span • Design Variables: • Constrained by: AAE 451 Team V

  22. Wing Sizing • Validation of sizing algorithm • Raymer statistical weight: 302 lbs • All-aluminum wing optimization: 300 lbs • Our design • S2-glass/epoxy skin • New weight: 286 lbs • Difference due to minimum gauge skin over outer 1/3 span AAE 451 Team V

  23. Fuselage • Preliminary model created and analyzed with I-DEAS • Ability to sustain limit load verified AAE 451 Team V

  24. Weight and Balance • Design gross weight from sizing • 2705 lbs • Detailed gross weight prediction • 2694 lbs AAE 451 Team V

  25. C.G. and Static Stability • Static Margin with full load 10.6% • Static Margin with no fuel, 1 pilot 19.6% 20% S.M. 10% S.M. C E D B F G A H AAE 451 Team V

  26. Fuel Selection • Bio-diesel chosen as alternative fuel • Reasons chosen: • BSFC of 0.439 lbs/(hp*hr) is bested only by hydrogen • Most developed technology of all of the proposed alternative fuels • Requires only minor modifications to available piston engines AAE 451 Team V

  27. Engine Design • Engine Requirements: • No more than 200 hp to remain “low performance” • Meet dimension constraints for the nose of the aircraft • Powerful enough to meet cruise speed target • An existing diesel aircraft engine meets our requirements • Development cost savings AAE 451 Team V

  28. Engine Design • Deltahawk V4 DH200V4 • Rated Power • 200 hp • Total installed Weight • 390 lbs • Dimensions: • 30x23x32 (inches) • Cost • $32,450 • Meets all desired requirements AAE 451 Team V

  29. Propeller • Existing Propeller • 2 Blade, constant Speed • Hartzell HC-C2YK-1 ( )/7666A-2 • Same Propeller as Piper Arrow • HP 200 • RPM 2700 • Cruise 145 kts • Specs. • Max constant HP = 250 • Max constant RPM = 2700 • Diameter = 74” AAE 451 Team V

  30. Acquisition Cost • Three cost estimating relationships: • GA Plane Library • Modified RAND DAPCA • Airframe Weight Relationship • Weighted average yields purchase price of ~$298,400.00 • RTD&E Break-Even set by DAPCA model at ~5 years (~2000 planes) • Reasonable with market that breakeven would be met. AAE 451 Team V

  31. Acquisition Cost Barn Owl AAE 451 Team V

  32. Operating Costs • Compiled data from web resources (Company websites; Plane Quest) • Allows for current fuel prices • 100LL ~ $4.27/gal • B100 ~ $3.00 - $3.25/gal • Gives Total Operating Cost of ~$81/hr (2006 USD)  AAE 451 Team V

  33. Operating Costs Barn Owl AAE 451 Team V

  34. Operating Costs • How does ~$81/hr compare? *Determined using DOC v. GTOW Relationship AAE 451 Team V

  35. Life Cycle Cost Estimate • Est. Cost for Owner over 12 year span of time? • Saves Owner over $100,000 than if same plane were powered by 100LL at current prices! (LCC $1,136k) AAE 451 Team V

  36. Design Requirements AAE 451 Team V

  37. Comparison to Current Competition AAE 451 Team V

  38. Summary • The Barn Owl will be a successful alternative fuel aircraft • The current design is feasible and meets all requirements • Next steps: • Controls sizing & dynamic stability • Refine and consolidate structure, aerodynamic, and layout models • Detailed production cost estimation AAE 451 Team V

  39. This Concludes the… Preliminary Design Review AAE 451 Team V Charlie Rush Zheng Wang Brandon Wedde Greg Wilson Stephen Beirne Miles Hatem Chris Kester Jim Radtke The Flying V Barn Owl

  40. Slide left intentionally blank… except for this. AAE 451 Team V

  41. References • Hartzell Propeller Data. “TYPE CERTIFICATE DATA SHEET NO. P-920 Available <http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgM akeModel.nsf/0/aac7773a13ad299186257114005a5cd0/$FILE/P- 920.pdf>. • Plane Quest. Plane Quest Website. Cited 4/1/06. Available <http://www.planequest.com/operationcosts/default.asp>. • Raymer, Daniel. Aircraft Design a Conceptual Approach. 3rd Ed. 1999. AIAA. Reston, VA. AAE 451 Team V

  42. CFD AAE 451 Team V

  43. CFD AAE 451 Team V

  44. Wing Structure Sizing Results AAE 451 Team V

  45. Wing Structure Sizing Results AAE 451 Team V

  46. Wing Structure Sizing Results AAE 451 Team V

  47. Wing Structure Sizing Results AAE 451 Team V

  48. Wing Structure Sizing Results AAE 451 Team V

  49. Propeller AAE 451 Team V

  50. Propeller AAE 451 Team V

More Related