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Wingman -22

30 th Annual American Helicopter Society Student Design Competition. Wingman -22. Arnab Roy Javier Bustamante Thuan Nguyen David Cycon Travor Stiner. RFP. Common requirements for 3 mission Payload: Useful Load: 6 Tons (Fuel, cargo, passengers, crew)

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Wingman -22

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  1. 30th Annual American Helicopter Society Student Design Competition Wingman -22 Arnab Roy Javier Bustamante Thuan Nguyen David Cycon TravorStiner

  2. RFP • Common requirements for 3 mission Payload: Useful Load: 6 Tons (Fuel, cargo, passengers, crew) Maximum Load: 15 Tons (include everything) Cruise speed: 240 knots at 6000 meters Min Climb rate: 2000 ft/min Max Altitude: Approach and return @ 6000 meters Flyover: @ 2000 meters

  3. RFP (continued) Additional points: On Board: T.A.W.S (Terrain Awareness and Warning System) T.C.A.S (Traffic Collision Avoidance System) Medical Equipments Hoists GPS Pressurized Cabin Rear Cargo Door Payload (boxes)

  4. RFP: Mission 1 (Fast deployment and rescue) Range: 600 km (approach, cruise speed 240 knots @ 6000 meters 600 km (flyover @ 120 knots @ 2000 meters) 600 km (return @ 180 knots) Crew : 3 members

  5. RFP: Mission 2 (Aid Distribution) Range: 600 km (approach, cruise speed 180 knots @ 6000 meters 600 km (flyover @ 80 knots @ 2000 meters) 600 km (return @ 140 knots) Crew : 3 members Time: Load/unload Maximum time allowed( 1hr/2tons)

  6. RFP: Mission 3 (SAR: Evacuation of casualties) Range: 600 km (approach, cruise speed 240 knots @ 6000 meters 10 km (decent, landing, take-off, climb) 600 km (return @ 240 knots) Crew : 3 members + 6 wounded Time: Load/unload max time (30 min/6 victims)

  7. Objective: • To create an aircraft that can perform the 3 missions with ease and try to exceed requirements with the least affect in cost to have a more competitive aircraft. To keep a customer centered aircraft that can achieve given requirements while maintaining a competitive cost with added capability.

  8. Choosing the configuration: • In choosing a configuration that best suits the mission requirements, we worked together on a design matrix. • The matrix design parameters and their weighted factors: • Range 1.00 • 40% Useful Load 0.60 • Cruise level vibrations 0.50 • Hover capability 0.40 • Cruise speed (240 kts) 1.00 • Altitude (6000m) 1.00 • Cost 0.20 • Complexity 0.40

  9. Choosing the configuration:

  10. Choosing the configuration:

  11. Choosing the configuration: After weighting the configurations, both tilt rotor designs out score the other configurations considered. Traditional tilt rotor design narrowly outscored the quad tilt rotor design, but also seemed more realistic and better suited our missions.

  12. Work breakdown & Gantt chart:

  13. Work breakdown & Gantt chart:

  14. Work breakdown & Gantt chart: • August 21 – September 27 • Identified proposal requirements • Created a selection matrix • Majority of time was spent determining selection criteria and weighting factors. • September 27th-Today • Divided work into 7 main areas of focus • Cost - Trevor • Weight and Balance - David • Performance (Forward Flight) - Arnab • Performance (Hover) - Javier • Stability –Thuan • CAD Drawing and analysis - Thuan • Vehicle Sizing - shared by all

  15. Performance: Aircraft mode First: Timeline of the performance calculations. Second: Final performance calculations. Third: Future calculations for the beginning of next semester.

  16. Timeline: • October 17th, 2012 • Power Vs. Velocity Curve Code • October 22nd, 2012 • Drag, Wing Area, Wing Loading, Velocity, Coefficient of lift • October 29th, 2012 • Mission 1 profile • Stall Speed @ 6000 meters and @2000 meters • Revised Power vs. Velocity • November 13th, 2012 • Excess Power • Climb Rate (power required) • Transition Mode, (On air and Take-off)

  17. Fall Semester Final • Drag (Revised) • Power Available Vs. Power Required (Revised) • Rate of climb • Mission 1 (Segments performance) • Fuel Weight

  18. Drag: • Configuration: 1 (240 knots flying at 6000 meter with 15 tons max weight)

  19. Power Required vs. Power Available

  20. Climb Rate

  21. Let’s Look at Mission 1 Profile Phase 7: Cruise at 180 knots Phase 3: Cruise 240 knots Phase 8: Descend (2000ft/min) Phase 6: Climb (2000ft/min) Phase 4: Descend (2000ft/min) Phase 2: Climb (2000ft/min) Phase 9: Hover Phase 5: Cruise 120 knots Phase 1: Hover

  22. Weight of the fuel • SFC = .35. • WE = 19841.6 lbs

  23. Transition Mode: Fz T (Thrust of Rotor) Lift of the wing θ Rotor V α wing Drag Fx Weight

  24. Force Balance equations: • Fz = T Cos(90-θ) –W +L(wing) • Fx = T sin(90- θ) –D cos(90-θ) • Power: P(plane) + P(helicopter) • X = Lift of wing to Weight factor

  25. Future Calculations:

  26. Mission 2 & 3 • Fuel weight • Power and drag calculations • Rolling Take-off and rolling landing • Force balance equations • Take-off velocity • Landing velocity • Take-off and landing distance

  27. Hover Hover mode was an important aspect of sizing the vehicle. Power Required Preliminary Size of Rotors Preliminary Size of Wing Rotor size was done by taking into consideration of the disk loading and the wing size.

  28. Power Calculations The early calculations were made with Ideal Power and sea level conditions. Since then a k = 1.15 has been implemented to account for power losses. Also for the measured power a drag was accounted for Cdo = .01

  29. Figure of Merit The Figure of Merit for our aircraft is .855. This is a bit high for a tilt rotor the reason is because the losses again were just assumed to be 15 percent. There are other things that would affect it, wing Downloading and the fountain effect.

  30. Engines We have picked the GE- 3000. This is the new version of the GE- T700, which has been successful for a number of years on the Apache and other aircraft. We are expecting a growth of 500 horse power for the GE-3000 engine.

  31. Engines With the 500 hp growth the total horse power for each engine would be 3500 hp. Rate of Climb Power Defined Hover 7000 hp

  32. Hover Ceiling Taking into account altitude, 15 metric ton gross weight, and a 7000 power installed power a hover ceiling was found.

  33. Stability • Volume Tail Ration of AW609

  34. Wingman-V22 From Dave graph Lt=26.5 Vertical tail surface:71 ft^2 Horizontal tail surface:53.8 ft^2

  35. Static margin vs Lt

  36. Downwash

  37. Finite Wing Correction

  38. Neutral Point

  39. Static Margin • C.G.=2.15ft for Dave

  40. Weight & Balance summery • RFP Maximum Empty Weight= 19,800 lbs. • Current Estimate is 16,344 lbs. • Center of Gravity • 23.89ft-24.32ft • Performance Index Rating =0.507 • 15000/MTOW CG Location

  41. Weight & Balance

  42. Center of Gravity • Mission #1 (20,060lbs) • CG Location • 24.17ft • Mission #2 (24,460lbs) • CG Location • 24.32ft • Mission #3 (21,260lbs) • CG Location • 23.89ft • Wing Location • 22ft-29.27ft

  43. Near Future Focus • Final Cabin Design • Includes pressurized cabin structure • Cargo Door Design • Aid Distribution System • Winch system for loading and unloading cargo • Locking mechanism for securing cargo during flight • Detailed Fuselage Design

  44. Cost • Cost Equations • Total Investment, TI = (Acquisition Cost)*(1 + spares allowance fraction) • TI = 37.45*(1+0.15) = 43.07 (in millions of dollars) • Utilization, U = (3750/(t + 0.5))*t (Using time for just mission 1 in the example calculations) • U = (3750/(5.85 + 0.5) )*5.85 = 3454.7 hours per year, seems unrealistic • Depreciation = 0.9*(TI)/(14*U) • Depreciation = 0.9*(43.07)/(14*3454.7) = 801.45 • Insurance premium = 0.005*(Aircraft Cost/U) • Insurance premium = 0.005*(37.45*106)/3454.7 = 54.20

  45. Cost • Trip-Cost Elements • Landing Fees = (7.8*Max Takeoff Weight)/t Landing Fees = (7.8*15)/5.85 = 20 Navigational Charges = ((0.5*range in km)/t)*sqrt(MOTW/50) Navigational Charges = ((0.5*1800)/t)*sqrt(15/50) = 84.27 Ground-handling Charges = (100*payload)/t Ground Handling Charges = (100*6)/5.85 = 102.56 Crew Costs = 200 Fuel Costs = ((Weight of Fuel consumed*1.2)/(6.76lbs/gal))*cost per gallon

  46. Cost

  47. Cost

  48. Cost Total DOC for first Mission = $1262.48 + fuel costs Expected DOC per hour = $3945.67

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