XV-15 litho - NASA's History Office

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Figure A-8. General layout and major components of the XV-15 tilt rotor research aircraft. 126 1. Instrument boom 2. Pitot static probe 3. Door for emergency window release handle 4. Nose landing gear from Canadair CL-84 5. Bird-proof windshield 6. Rockwell LW-3B ejection seats 7. Avionics installation 8. Entry door, 2 ft 8 in opening 9. Phasing actuator for tilting mechanism 10. Cross-shaft between tilting actuators 11. Center gearbox for transmission cross-shaft 12. Bonded splice doublers 13. Upper and lower wing skins, 3/4 in honeycomb sandwich 14. Aluminum alloy extrusion front spar 15. Lightweight crash-resistant fuel tanks, total fuel 1,509lb 16. Aluminum alloy extrusion rear spar 17. Flaps, max deflection 75° 18. Flaperons, max deflection 47° 19. Actuator fairing 20. Navigation lights 21. Collective-pitch lever 22. Collective crosshead 38 For ferry operations, Bell developed a removable internal tank that extends the duration of flight to more than two hours. An environmental control system provides ventilation and temperature control. An air-cycle environmental control unit mounted in the aft fuselage is powered by bleed-air from the right engine. During hot day operation of the XV-15, the cooling capacity was found to be inadequate. To reduce crew station heating, the overhead windows were covered with an opaque coating during the late 1990s. Each crew seat is equipped with an oxygen system supplied from a 1,800-psi oxygen cylinder. Adequate oxygen for a one hour flight with a 20 percent reserve is carried onboard. The design of the XV-15 TRRA incorporates many features and system redundancies intended to enhance the safety of this vehicle. Some of these are not expected to be included in civil aircraft of its weight class and, therefore, must be considered when evaluating the XV-15’s weight and payload capacity. Among the additional items are the Rockwell International Model LW-3B ejection seats, capable of removing the crew members in flight or from a zero airspeed, groundlevel (zero-zero) normal attitude condition. The ejection seats can be triggered independently or simultaneously by pilot command. In addition, the overhead and side windows can be removed by a mild detonator cord placed around the window frames. The window removal can be initiated from within the cockpit or from an external lever located under a door on the nose cone. 40 24 37 21 36 22 23 20 39 25 16 19 18 23. Cyclic swash plate 24. Cyclic tube 25. Pitch-change lever 26. Gravity refueling point 27. Transmission cross-shaft 28. Rotor-tilt actuator, controlled by thumb switch on pilots collective lever 29. 25 ft diameter rotors (14 in chord) 30. Modified 1,550 h.p. Lycoming LTCIK-4K turboshafts 31. Main transmission 32. Main landing gear from Canadair CL-84 33. Cyclic mixing box 34. Collective mixing box 35. Controls to cockpit via cabin floor 36. Anti-collision light 37. VOR localizer aerial 38. VHF aerial 39. UHF aerial 40. Navigation light 32 35 17 15 33 13 34 11 12 10 8 9 6 7 26 14 15 27 5 2 4 3 31 28 30 1 29
A cutaway drawing showing the key components of the XV-15 is shown in figure A-8. Inboard profile drawings are provided in figures A-9 and A-10. 64 As an example of the overall performance capabilities of the XV-15, the heightvelocity flight envelope is shown in figure A-11. The variation of power with airspeed indicating the ability of the tilt rotor aircraft to operate over a broad range of airspeeds at power levels well below that required for hover is shown in figure A-12. 65 Although only two XV-15 aircraft were built, the Government Project Office took the unusual step of directing the Bell Helicopter Company, under the TRRA Contract, to develop a complete flight manual. These manuals 66 became a valuable source of systems information for the flight and ground crews during the flight program and served as a training and familiarization tool for the many guest pilots. 64 Martin D. Maisel, et al, “Tilt Rotor Research Aircraft Familiarization Document,” NASA TM X-62.407, January 1975. 65 W.L. Arrington, “Flight Test Report,” Vol. I-V, NASA CR 177406 and USAACSCOM TR-86- A-1, June 1985. 66 Anon., “XV-15 Flight Manual,” Bell Helicopter Textron Report TP-78-XV-15-1, August 15, 1980. 127
Page 1:
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
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68 Symmetric beam mode Antisymmetri
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Figure 55. XV-15 during short takeo
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Top: Figure 56. Flow visualization
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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 144 and 145: Figure A-3. Transcendental Model 2
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 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
Page 194 and 195: 168 Churchill, G. B.; Dugan, D. C.
Page 196 and 197: 170 Edenborough, H. K. “Investiga
Page 198 and 199: 172 Harendra, P. B.; Joglekar, M. J
Page 200 and 201: 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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