XV-15 litho - NASA's History Office

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Figure A-3. Transcendental Model 2 cutaway drawing. 118 Model 2 Characteristics Powerplant One Lycoming . . . . . . . . . . . . . . . . . O-435-23 Brake horsepower . . . . . . . . . . . . . . . 250 HP@ 3200 RPM Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 ft 1 in Wing Span. . . . . . . . . . . . . . . . . . . . . . . . . . 22 ft 9 in Area. . . . . . . . . . . . . . . . . . . . . . . . . . 100 sq ft Airfoil section . . . . . . . . . . . . . . . . . . NACA 23015 Width. . . . . . . . . . . . . . . . . . . . . . . . . 39 ft (to outer tip of rotor disc) Height . . . . . . . . . . . . . . . . . . . . . . . . 9 ft 5 in Rotor No. of rotors . . . . . . . . . . . . . . . . . . . 2, interconnected Type. . . . . . . . . . . . . . . . . . . . . . . . . . articulated Blades/proprotor . . . . . . . . . . . . . . . . 3 Diameter . . . . . . . . . . . . . . . . . . . . . . 18 ft Chord (constant) . . . . . . . . . . . . . . . . 0.356 ft Disc loading . . . . . . . . . . . . . . . . . . . 4.4 lb/sq ft Weight Empty . . . . . . . . . . . . . . . . . . . . . . . . 1579 lb Gross . . . . . . . . . . . . . . . . . . . . . . . . . 2249 lb Useful load . . . . . . . . . . . . . . . . . . . . 670 lb No. of seats . . . . . . . . . . . . . . . . . . . . . . . . . . 2
Bell XV-3 The XV-3 63 (figures A-4 and A-5) is a fixed mid-wing VTOL research aircraft developed to explore the flight characteristics of the tilt rotor aircraft. A two-bladed proprotor is mounted on a shaft assembly at each wing tip. The proprotors can be rotated over a range of 90 degrees to permit hover and helicopter-, conversion-, and airplane-modes of flight. The aircraft has a conventional empennage plus a ventral fin below the vertical fin and rudder and uses a skid type landing gear. Small wheels can be attached for rolling takeoff and landing tests. The wing incorporates half-span 20 percent wing chord flaps and 22.5 percent wing chord ailerons. Fuselage-to-wing tip struts are incorporated to increase the stiffness of the wing. A supercharged Pratt and Whitney R-985-AN-1 reciprocating radial engine is mounted in the fuselage aft of the wing center section. The standard rating for this engine is 450 BHP at 2300 rpm but, to increase performance for test purposes, the manufacturer authorized operation at 2400 rpm for takeoff, hovering and STOL flight conditions. Power is transferred from the engine to the proprotors through a short flexible-coupled drive shaft to the main (center) transmission located between the wing center section spars. From the main gear box, flexible-coupled shafts extend spanwise to the outboard wing tip (outboard) transmissions. The proprotor shafts extend from the outboard transmissions normal to the input drive shaft. The outboard transmissions are mounted on yokes which enable the proprotor shafts to be pivoted from the vertical to the horizontal. The cockpit contains helicopter-type controls: a cyclic control stick, a collective pitch stick with a twist grip throttle, and rudder pedals. The longitudinal cyclic proprotor controls are mechanically reduced as the airplane mode configuration is approached. In the airplane mode no longitudinal cyclic response is provided. The differential collective controls (lateral stick inputs) are also reduced but onethird of the helicopter mode control is retained in airplane flight to increase maneuverability. The collective pitch is also automatically increased in the airplane mode to correspond to the required operating range. The longitudinal, lateral, and collective controls are hydraulically boosted. There is no stability or control augmentation installed in the XV-3 and it does not have lateral cyclic proprotor controls. The conversion system is powered by an electromechanical linear actuator connected to each outboard transmission yoke and is controlled by a “beep” switch on the cyclic stick. An interconnect shaft links the right and left conversion systems to ensure synchronization and to permit the conversion cycle to be 63 The XV-3 configuration described in this section (from Deckert and Ferry, footnote 7) reflects the characteristics of aircraft number 2 (tail number 4148) as flown during evaluations at the NASA Dryden Flight Research Center and the NASA Ames Research Center (from 1959 through 1962). 119
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The History of The XV-15 Tilt Rotor
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Contents Prologue . . . . . . . . .
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Dedication The story of the success
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Foreword The development of tilt ro
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List of Figures Figure 1 Leonardo d
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Figure 41 Simultaneous static test
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Figure A-2 Transcendental Model 2 t
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List of Acronyms AARL Army Aeronaut
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TRENDS Tilt Rotor Engineering Datab
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Figure 2. Illustration of vertical
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Figure 4. McDonnell XV-1 compound h
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Figure 7. Henry Berliner tiltpropel
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Top: Figure 9. The Baynes Heliplane
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Figure 13. Illustration from the Ha
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Figure 17. Bob Lichten, extreme lef
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Figure 20. Tiedown tests of the XV-
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16 Research and Engineering), obtai
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18 management continued to show int
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20 Building the Technology Base Aer
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Figure 25. Bell 25-ft. diameter pro
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Figure 28. Performance tests of 5-f
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Figure 31. Bell 25-ft. diameter pro
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28 Tilt Rotor Research Aircraft Pro
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30 During the late 1960s and early
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32 range of loading conditions and
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34 The initial projected cost of $4
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Figure 35. Illustration of the Boei
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Figure 36. 1/5 scale XV-15 model in
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40 under the contract. To accomplis
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42 Aircraft Development The primary
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44 Test stand angle box Test stand
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Figure 40. Proprotor response to co
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Figure 41. Simultaneous static test
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50 helicopters. For the conversion
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52 Prior to the start of flight ope
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Figure 44. Initial Bell tiedown sho
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56 degrees 25 and a brief assessmen
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Figure 45. XV-15 in the Ames Resear
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60 NAVAIR managers as a means of de
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Figure 46. Government and Bell pers
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Figure 49. Tiedown test facility at
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66 Wheel height Top: Figure 51. Met
Page 94 and 95: 68 Symmetric beam mode Antisymmetri
Page 96 and 97: Figure 55. XV-15 during short takeo
Page 98 and 99: Top: Figure 56. Flow visualization
Page 100 and 101: 74 during “degraded” flight con
Page 102 and 103: Figure 59. Hover acoustics tests du
Page 104 and 105: 78 Nose weight Top: Figure 61. Typi
Page 106 and 107: 80 Following the completion of cont
Page 108 and 109: 82 After the proprotors stopped, th
Page 110 and 111: 84 sudden stoppage of the right eng
Page 112 and 113: 86 A reconversion to the helicopter
Page 114 and 115: 88 Paris Air Show By early 1981, th
Page 116 and 117: 90 enroute from Farnborough to Fran
Page 118 and 119: Top: Figure 66. Senator Goldwater i
Page 120 and 121: Figure 69. Shipboard evaluations of
Page 122 and 123: Figure 71. XV-15 at the New York Po
Page 124 and 125: 98 Crash (October 16 and 17, 1991).
Page 126 and 127: 100 The End of an Era By the mid 19
Page 128 and 129: Top: Figure 73. XV-15 at the Dallas
Page 130 and 131: 104 management system was very effe
Page 132 and 133: 106 could make use of the same flig
Page 134 and 135: Figure 76. The Bell tilt rotor eagl
Page 136 and 137: 110 demonstrations two years earlie
Page 138 and 139: 112 Future Tilt Rotor Aircraft By t
Page 140 and 141: 114 tiltrotor aircraft program. Thi
Page 142 and 143: 116 Model 1-G Characteristics Power
Page 146 and 147: Figure A-4. XV-3 three-view drawing
Page 148 and 149: Figure A-5. XV-3 inboard drawing, s
Page 150 and 151: Nacelle angle (degrees) 124 120 90
Page 152 and 153: Figure A-8. General layout and majo
Page 154 and 155: Figure A-9. Side view inboard profi
Page 156 and 157: Figure A-11. XV-15 height-velocity
Page 158 and 159: 132 Weight Design . . . . . . . . .
Page 160 and 161: 134 WBS LEVEL: Bell Army/NASA I II
Page 162 and 163: 136 US Army Air Mobility Research a
Page 164 and 165: 138 Army/NASA (continued) Staff (19
Page 166 and 167: 140 Appendix C—Chronology 1452-15
Page 168 and 169: 142 1968 Boeing Vertol awarded cont
Page 170 and 171: 144 November, Initial piloted simul
Page 172 and 173: 146 24 March 1982 XV-15 demonstrate
Page 174 and 175: 148 30 July 1987 FAA/NASA/DOD Tilt
Page 176 and 177: 150 21 August 1990 V-22 reached 340
Page 178 and 179: 152 14 June 1993 The Department of
Page 180 and 181: 154 Appendix D—Awards and Records
Page 182 and 183: Figure D-1. Jean Tinsley, first wom
Page 184 and 185: Figure E-3. XV-15 flying by the Sta
Page 186 and 187: Figure E-7. Bell test pilots Roy Ho
Page 188 and 189: Figure E-11. Ken Wernicke, Bell til
Page 190 and 191: 164 Appendix F—Bibliography Tilt
Page 192 and 193: 166 Ball, J. C. “XV-15 Shipboard
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168 Churchill, G. B.; Dugan, D. C.
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170 Edenborough, H. K. “Investiga
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172 Harendra, P. B.; Joglekar, M. J
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174 Kvaternik, Raymond G. “Studie
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176 Magee, J. P.; Pruyn, R. “Pred
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178 Martin, Stanley, Jr.; Erb, Lee
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180 Rutledge, Charles K.; George, A
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182 Tischler, M. B.; Leung, J. G. M
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184 Whitaker, H. L.; Cheng, Yi. “
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186 Daniel C. Dugan Daniel Dugan gr
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188 Carnet, 88 Carpenter, Ron, 91 C
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190 Moffett Airfield, Moffett Field
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Monographs in Aerospace History Lau
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National Aeronautics and Space Admi
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