CDR Presentation 26 Nov Dust Thrusters Dain Christensen Julene Forner Jessica Howe Jonathan Newhall David Roman Michael Straka Kyle Vonnahmen

Transcription

1 CDR Presentation 26 Nov 2007 Dust Thrusters Dain Christensen Julene Forner Jessica Howe Jonathan Newhall David Roman Michael Straka Kyle Vonnahmen

2 Overview Constraint Analysis Jonathan Newhall Structures Julene Forner Propulsion Kyle Vonnahmen Aerodynamics Michael Straka Stability and Control Jessica Howe Performance David Roman Configurations Jonathan Newhall Operation and Cost Dain Christensen Newhall - 2

3 Initial designs- Twin boom pusher, VTOL, Flying wing Configurations Newhall - 3

4 Constraint analysis Design point at W/S 11, T/W.3 Configurations Newhall - 4

5 Structures Julene Forner Forner-5

6 Fuselage Structure Requirements Designs Considered Monocoque Semi-Monocoque Veneer Truss The Final Decision Structures Forner-6

7 Wing Attachment Requirements Possible Designs Foldable Wing Detachable Wing and Tail Detachable Wing The Two Designs The Wing Box Structures Forner-7

8 Materials Requirements Choices Composites Wood Steel Aluminum The final decision Structures Forner-8

9 Requirements Configurations Considered The Decision Landing Gear Structures Forner-9

10 Structures Forner-10

11 Propulsion Kyle Vonnahmen Vonnahmen - 11

12 Design Requirements Engine Choices Selected Engine Fuel System Future Work Overview Propulsion Vonnahmen - 12

13 T/W Ratio of 0.3 Design Requirements Cruising speed of 88 ft/s Engine size of at least bhp Propeller size less than 5.30 ft Propulsion Vonnahmen - 13

14 Engine Choices Narrowed down to Piston Engine or Wankel (Rotary) Engine Piston Engine the traditional choice for aircraft Wankel Engine newer engine mostly used in UAVs Propulsion Vonnahmen - 14

15 Wankel Engine Propulsion Vonnahmen - 15

16 Engine Comparison Chart Rotax 912 S Rotamax 650cc Type Piston Rotary HP RPM Weight (lbs) Cost 18,000 11,000 Fuel Burn (gal/hr) D prop (in) T static (lbf) T forward (lbf) Propulsion Vonnahmen - 16

17 Selected Engine Decided on a Rotary Engine Cheaper & More Power Smaller Size & Less Weight Fewer moving parts Designed for high RPMs Readily Available Propulsion Vonnahmen - 17

18 Selected Engine (cont.) Turbocharger gives engine extra power Still Cheaper than piston engine Decided to go with a bigger engine Propulsion Vonnahmen - 18

19 Fuel System Designed for a 1½ hour flight Rotary engines can use a variety of fuels Est. 5.5 gal/hr Need 1.47 ft 3 of fuel space in wings Propulsion Vonnahmen - 19

20 Future Work More engine research Possible engine size change More detailed fuel system Propulsion Vonnahmen - 20

21 Aerodynamics Michael Straka Straka - 21

22 Wing Geometry Considerations: simple design, low cost, easy to maintain Rectangular low-wing Span: 25 feet Chord: 3.6 feet Wing tips: cut-off design Aerodynamics Straka - 22

23 Airfoil Selection Desired: stable over a wide range of angles High stall angle of attack High lift/low drag Similar to sailplane Aerodynamics Straka - 23

24 Airfoil Selection S4083 airfoil Max C L = 1.57 (14 degrees) Lift coefficient=.42 (α=0) C Lα =4.49 Aerodynamics Straka - 24

25 Airfoil Performance Calculated stall speed: 24.4 fps No high-lift devices required Low overall drag High angle of attack before stall Aerodynamics Straka - 25

26 Drag Polar Using Raymer drag buildup Rough estimate of parabolic drag Includes landing gear, accounts for protuberances Aerodynamics Straka - 26

27 Stability and Control Jess Howe Howe - 27

28 Main Components Sizing of tail surfaces/control surfaces Location of neutral point Location of center of gravity Static Margin Stability and Control Howe - 28

29 Tail Sizing AR c c AR v ht vt h ls h = cs ls v v = bs = h b S 2 h h b = 1.55 v S 2 v Where.4b<l v =l h <.5b or 2.5c<l v =l h <3.5c Where 4<AR h <5 and 2.5<AR v <3 Stability and Control Howe - 29

30 Tail Sizes to Scale Stability and Control Howe - 30

31 Determination of Neutral Point Sh α F h pα α p Cm α = CL α( Xcg Xacw) + Cm α fus ηh CL αh ( Xach Xcg ) + ( Xcg X p ) S α qs α Setting C ma =0 and solving for X cg yields the neutral point Sh α F h pα α p CL αxacw Cm α fus + ηh CL αh Xach + X p S α qs α X np = S F h α h pα α p CL α + ηh CL αh + α α S qs Stability and Control Howe - 31

32 Static Margin SM.. = ( X X ) np cg Static Margin must be positive in order to have static stability This implies that X cg must be in front of the neutral point X cg was found using weight*moment arm Stability and Control Howe - 32

33 Static Margin 7 6 Flight Condition Power Off Power On Static Margin [%] Stability and Control Howe - 33

34 Trade Study T-Tail Configuration Static Margin - T-Tail Flight Condition Power Off Power On Static Margin [%] Stability and Control Howe - 34

35 Performance David Roman Roman - 35

36 Mission Profile Crop Duster Not regulated by FAR Only one propeller Focus is simplicity Crop Dusting Mission Ferry Mission Performance Roman - 36

37 Start up and Taxi Take Off Newton force analysis Numerical integration Climb 50 foot climb 13 climb angle Take-Off and Climb ΔV dv 1 = T D μ W L Δt dt m ΔV V ( t+δ t) = V ( t) + Δt Δt ( ) ( +Δ ) = ( ) + ( ) + ( +Δ ) S t t S t V t V t t dv T D 1 dh g = dt W V dt Δt 2 Performance Roman - 37

38 Cruise Crop Dusting Mission 30 feet spray width Travels along length of rectangular field 34 Passes Ferry Mission Up to 2 miles with no payload Performance Roman - 38

39 Turns Turn Steady level turn desired Maximum load factor, n = 4.28 Maximum bank angle, φ = 76 ϖ = g V R = g n n V Performance Roman - 39

40 Descent and Landing Descent Decreasing rate of climb 13 descend angle Landing Numerical integration until v = 0 ft/s 64% of Take Off Gross Weight at Landing μ = 0.6 to account for brakes Performance Roman - 40

41 Configurations Jon Newhall Newhall - 41

42 First design iteration Second design iteration Smaller, more rounded fuselage Configurations Newhall - 42

43 Final design iteration- redesigned tail, addition of landing gear, wheels, and propeller Configurations Newhall - 43

44 Configurations Newhall - 44

45 Operation and Cost Dain Christensen Operation and Cost Christensen - 45

46 Spray System Uses existing equipment 2 11 foot ATV booms Gallon Tank 1 pump 54 ft of Hose Total cost of $2,175 Operation and Cost Christensen - 46

47 Operation and Avionics Computer based operation Similar to current R/C aircraft 3 Cameras GPS system Operation and Cost Christensen - 47

48 Fly away costs 2 Methods used, Raymer, and Roskam Raymer $58,000 Roskam $31,000 Flyaway cost of $50,000 to $40,000 Operation and Cost Christensen - 48

49 $36 per hour of flight Operating costs Assumes Farmer operation and maintenance $20 an hour in fuel costs (5.5 gallons an hour at $3.50 a gallon) Operation and Cost Christensen - 49

50 References [1] AIAA Undergraduate Team Aircraft Design Competition, Retrieved November 2008 [2] Teichmann, Frederick, Design of the Wing, The Fuselage, Airplane Design Manual, Pitman Publishing Corporation, New York, 1939, pp , [3] Pomilio, Ottorino, Structure of the Airplane Airplane Design and Construction, McGraw-Hill Book Company Inc., New York, 1919, pp [4] Younger, John, Airplane Construction and Repair, McGraw-Hill Vocational Texts, New York, [5] Raymer, D.P., Aircraft Design: A Conceptual Approach, AIAA Education Series, J.A. Schetz, Ed., American Institute of Aeronautics and Astronautics, Inc., Reston, VA, 4th Ed. 2006, pg [6] Rotary Aircraft Engines, [online], October 2007, [retrieved 8 October 2007] [7] Rotomax Engines, [online], October 2007, [retrieved 8 October 2007] [8] Raymer, D.P., Aircraft Design: A Conceptual Approach, AIAA Education Series, J.A. Schetz, Ed., American Institute of Aeronautics and Astronautics, Inc., Reston, VA, 4th Ed. 2006, pg [9] Raymer, D.P., Aircraft Design: A Conceptual Approach, AIAA Education Series, J.A. Schetz, Ed., American Institute of Aeronautics and Astronautics, Inc., Reston, VA, 4th Ed. 2006, pg [10] UIUC Airfoil Coordinates Database Version 2.0 Updated 11/29/ Retrieved November 2008 Christensen - 50

51 References [11] Roskam, Jan, Methods for Estimating Drag Polars of Subsonic Airplanes, University of Kansas, Lawrence, KS, [12] Roskam, Jan, Airplane Design Part III Layout Design of Cockpit, Fuselage, Wing and Empennage: Cuttaways and Inboard Profiles, Roskam Aviation and Engineering Corporation, Ottawa, KS, 1985 [13] Richgruber, Chris, Stability and Control University of Illinois, Champaign, IL 2007 [14] Raymer, D.P., Aircraft Design: A Conceptual Approach, AIAA Education Series, J.A. Schetz, Ed., American Institute of Aeronautics and Astronautics, Inc., Reston, VA, 4th Ed. 2006, pg [15] Anderson, J.D., Jr., Aircraft Performance and Design, McGraw-Hill, [16] McCormick, B.W., Aerodynamics, Aeronautics and Flight Mechanics, John Wiley & Sons, 2nd Ed [17] Raymer, D.P., Aircraft Design: A Conceptual Approach, AIAA Education Series, J.A. Schetz, Ed., American Institute of Aeronautics and Astronautics, Inc., Reston, VA, 4th Ed. 2006, pg [18] Raymer, D.P., Aircraft Design: A Conceptual Approach, AIAA Education Series, J.A. Schetz, Ed., American Institute of Aeronautics and Astronautics, Inc., Reston, VA, 4th Ed. 2006, pg [19] Raymer, D.P., Aircraft Design: A Conceptual Approach, AIAA Education Series, J.A. Schetz, Ed., American Institute of Aeronautics and Astronautics, Inc., Reston, VA, 4th Ed. 2006, pg [20] Raymer, D.P., Aircraft Design: A Conceptual Approach, AIAA Education Series, J.A. Schetz, Ed., American Institute of Aeronautics and Astronautics, Inc., Reston, VA, 4th Ed. 2006, pg Christensen - 51

52 References [21] Roskam, Jan, Airplane Design Part VIII Airplane Cost Estimation Design, Development, Manufacturing and Operating, Roskam Aviation and Engineering Corporation, Ottawa, KS, 1985 [22] Water Quality Update, University of Idaho, Volume 3, Number 4, August 1993, [23] Quick Silver Aircraft, GT500, Retreived November Christensen - 52

53 Questions Christensen - 53