The Art of the Helicopter John Watkinson - Karatunov.net

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Lockheed flybar system, 309–13 AMCS (advanced mechanical control system), 312 CL-475 test bed, 309 Model 286(XH-51) four-bladed hingeless system, 311–12 three-bladed hingeless rotor system, 309–11 Machinery rafts, for vibration control, 111–12 Magnetic compasses, 264–71 aircraft compass construction, 264–6 compass dip, 266 compass errors, 267–9 banked turn problems, 267–9 deviation, 267 flux gate compass, 269–71 gyromagnetic compass, 281–2 liquid damping, 266 lubber lines, 266 maps for, 264 and runway numbering, 264 Magnetos, 201–3 Manoeuvres: banking, 87–8 basic manoeuvres, 87–9 hover to transitional flight, 87–8 translational flight, 88–91 Mass centroid, 23 Mass controlled systems, and SHM, 42–3 Mass and density, 22 McDonnell Little Henry helicopter (ramjet), 248 McDonnell XV-1 convertiplane, 355 MD-500, tailplane, 180 Mean sea level (MSL), 325–6 Mil: Mi-24 Crocodile, 171, 175 Mi-26, 171, 176 V-12 multi-rotor helicopter, 361–2 Military applications, 1–2, 321 Models: feedback in servos, 59–60 for research, 8–9 MOGAS (aviation fuel), 238 Moments and couples, 28–9 MSL (mean sea level), 325–6 Multi-rotor helicopters: about multi-rotor helicopters, 12–15, 358 Cierva Air Horse, 358, 360 coaxial helicopters, 15, 361–4 yaw control, 362–4 Mil V-12 helicopter, 361–2 side-by-side configuration, 13, 358–61 Fa 223 helicopter, 359–61 synchropter, 13–15, 364–8 Kaman H-43 (Husky), 366–8 Kolibri (hummingbird) helicopter, 364–6 yaw control, 366–8 see also Tandem rotor helicopters Multiple engine machines: power management, 337–9 transmission, 243–4 Never exceed speed, 97 Newton (N), 23 Newton’s laws, 30 Nodal beam vibration control system (Bell), 112 NOTAR (NO TAil Rotor) system, 167, 187–9 Nyquist frequency, and sidebands, 45–6 Octal systems, 298 OEI (one engine inoperative) safety, 324 OGE (out of ground effect), 329–30 Oil systems, gasoline engines, 205–7 cold starting, 207 heat soak after landing, 207 oil cooler/temperature control, 206–7 oil coolers, 205 oil filter, 206 oil grades, 206 oil pressure relief valve, 205–7 oil pump, 205 oil SAE numbers, 206 oil strainer, 205–6 Oil systems, turbine engines, 232–3 Oleos (oleo-pneumatic struts), 18 One engine inoperative (OEI) safety, 324 Oscillation, mechanics of, 36–40 and centripetal force, 38 and phase shift, 36–7 radius of gyration, 38 and rotation, 37–8 and translation, 38 Osprey helicopter, blade folding, 165 Out of ground effect (OGE), 329–30 Overpitching, 198 PCM (pulse code modulation), 292–3 Pendular vibration absorbers, 110 Performance, 323–46 about performance, 323–4 climbing and descending, 335–7 economic performance, 323 hover in ground effect (HIGE), 323 hover out of ground effect (HOGE), 323, 330 one engine inoperative safety, 324 operational performance, 323 safety implications, 324 speed limits, 97–8 tactical performance, 323–4 see also Power management; Range Index 385
386 Index Piasecki: Dogship tandem rotor helicopter, 368–9 Pathfinder gyrodyne, 354 Piezo-electric gyroscopes, 54–5 Pilot stress, and vibration, 107 Piston engines/installations: basic elements, 17 fuel for, 18 typical installation, 193–4 see also Diesel piston engines/installations; Gasoline engines/installations Pitch control, 136–41 cyclic trim, 141–2 multi-bladed heads, 139–41 servo tabs, 138–9 sliding swashplates, 136–7 Pitch stability, 342 Plunging, 98 Power assisted controls, 302–3 duplex actuator, 303–4 EHV (electro-hydraulic valve), 304–5 fully powered systems, 303–5 Power management, 326–31 airspeed effects, 330–1 and all-up weight (AUW), 329–30, 334 climbing, 335–7 descending, 335–7 and hover out of ground effect (HOGE), 329–30 multiple engine machines, 337–9 power margin, 327–9 Power to weight ratio, high needed, 1 Power turbine inlet temperature (PTIT), 237 Powerblades, 249 Pressure, and gases, 32–3 Pressure and density altitude, 325–7 Pressure instruments: altimeters, 271–5 altitude sensing, 276–7 AMSL (height above mean sea level), 273 ASI (airspeed indicator), 275–6 chaser motors, 277 chasers, 277 GS (groundspeed), 276 IAS (indicated air speed), 276 ISA (International Standard Atmosphere), 273–4, 325–6 QFE (airfield barometric pressure), 273–4 QNH (pressure reduced to mean sea level), 273–4 rotor turning problems, 274 TAS (true air speed), 276 VSI (vertical speed indicator), 275 Profile drag, 63–4 PTIT (power turbine inlet temperature), 237 Pulse code modulation (PCM), 292–3 Pulse jet, 248–9 Pulse width modulation (PWM), 378 Puma, tail design, 173 Pumping loss, gasoline engines, 334 PWM (pulse width modulation), 378 QFE (airfield barometric pressure), 273–4 QNH (pressure reduced to mean sea level), 273–4 Quantizing, 293 RADAR altimeter, 288–90 RADAR sensors, 288–90 Radio control principles, 377–8 Radio-controlled helicopters, 263, 376–7 Radius of gyration, 38 RAF (relative airflow): about RAF, 61 and ground effect, 84 Ramjet (athodyd), 247–8 Range: and all-up weight (AUW), 334 gasoline engines, 333–4 and speed, 331–2 turbine engines, 333–4 wind effects, 332 Recirculation, and ground effect, 86 Relative airflow (RAF): about RAF, 61 and ground effect, 84 Remotely piloted helicopters, 263, 376–7 Resonance, 43 Reynolds numbers, 63 Rigidity and strength, 25–6 Robinson helicopters, 131 R-22, 158 carburettor icing avoidance, 215–16 overpitch control, 198 Rollover, 153–5 Rotation, mechanics of, 40–4 damping, 43 mass controlled systems, 42–3 resistance controlled systems, 43 rotation masses and precession, 51–2 stiffness controlled systems, 42 Rotodyne, 11, 12 Rotor blades: abrasion problems, 163 actuator concept, 73–5 advancing blade compressibility stall, 96, 97 aeroelasticity effect, 115 blade construction, 162–3 blade design, 114–16 blade element theory, 75 blade folding, 163–5 blade forces, 70–1 blade stall and compressibility, 93–7 blade tracking, 163
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The Art of the Helicopter
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The Art of the Helicopter John Watk
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Contents Preface xi Acknowledgement
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4.12 Feathering 134 4.13 Pitch cont
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8.5 Power management 326 8.6 Flying
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xii Preface reader to make sense of
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1 Introduction to rotorcraft 1.1 Ap
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Introduction to rotorcraft 3 Fig. 1
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Introduction to rotorcraft 9 for th
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Introduction to rotorcraft 11 Fig.
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(a) (b) (c) (d) Introduction to rot
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Fig. 1.18 The contra-rotating coaxi
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Fig. 1.20 The structure of a light
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Introduction to rotorcraft 19 wings
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Introduction to rotorcraft 21 a rot
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Technical background 23 Fig. 2.1 At
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Fig. 2.3 Effect of force on velocit
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C Force A E Resultant (a) Force B (
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(a) (b) Technical background 29 Fig
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Technical background 31 Fig. 2.11 A
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Technical background 33 Fig. 2.12 (
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Technical background 35 If the volu
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Fig. 2.16 The definition of a radia
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Technical background 39 force would
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Technical background 41 Figure 2.20
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Technical background 43 force where
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Technical background 45 the cosine
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Technical background 47 Fig. 2.28 F
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Technical background 49 Fig. 2.30 T
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Technical background 51 centripetal
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2.17 The gyroscope Technical backgr
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Technical background 55 of oscillat
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Technical background 57 the inertia
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Technical background 59 shut down a
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3 Introduction to helicopter dynami
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Introduction to helicopter dynamics
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(a) (c) (b) Introduction to helicop
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(a) (b) (c) (d) Introduction to hel
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Fig. 3.23 Conditions for hover and
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(a) (b) Introduction to helicopter
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(a) (b) Introduction to helicopter
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4.1 Introduction 4 Rotors in practi
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(a) (b) Rotors in practice 119 Fig.
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Rotors in practice 121 Designers of
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Rotors in practice 123 opposite occ
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Rotors in practice 125 Fig. 4.6 (a)
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Rotors in practice 127 assembly tha
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Rotors in practice 129 Pitch change
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× T=c× D Rotors in practice 131 F
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Rotors in practice 133 In a real he
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Rotors in practice 135 Fig. 4.15 Va
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(a) (b) Rotors in practice 137 Fig.
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Rotors in practice 139 Fig. 4.18 Th
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Rotors in practice 141 swashplate a
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Fig. 4.23 A fixed-pitch tilting hea
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Rotors in practice 145 Fig. 4.25 Bl
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Rotors in practice 147 Fig. 4.27 Ef
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Rotors in practice 149 Fig. 4.29 (a
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Rotors in practice 151 concerned ar
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Rotors in practice 153 and lag damp
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Rotors in practice 155 disappears a
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(d) (e) (f) Rotors in practice 157
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Rotors in practice 159 hull and a v
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Rotors in practice 161 Fig. 4.35 (C
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Rotors in practice 163 Abrasion is
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Rotors in practice 165 There are so
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eing more visible to ground personn
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otates the rod in the screw thread.
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In the case of a rotor having offse
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The tail rotor designer is faced wi
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Fig. 5.5 A right-side wrong-directi
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centre of mass. The solution was to
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safe to start the rotors. However,
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Fig. 5.10 Tail plane locations: (a)
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Fig. 5.12 (a) A top-mounted fin is
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Fig. 5.14 (a) Main rotor lateral ro
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long. The cross-section of the duct
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drag. However, the slots are emitti
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6 Engines and transmissions The pow
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Engines and transmissions 193 the D
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(a) (b) Engines and transmissions 1
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(a) (b) (c) Engines and transmissio
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Fig. 6.5 A typical horizontally opp
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Engines and transmissions 201 the v
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Engines and transmissions 203 The c
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6.9 The oil system Engines and tran
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Engines and transmissions 207 (non-
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(a) (b) Engines and transmissions 2
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Engines and transmissions 211 a hot
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Engines and transmissions 213 Fig.
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Engines and transmissions 215 In wa
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Engines and transmissions 217 is a
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Engines and transmissions 221 own t
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Fig. 6.16 The complex fuel system o
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Engines and transmissions 233 and c
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Engines and transmissions 237 Sensi
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Engines and transmissions 243 the A
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Fig. 6.37 Displays which may be see
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Engines and transmissions 251 slipr
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Engines and transmissions 253 a fau
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Engines and transmissions 255 resul
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Engines and transmissions 257 The p
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Fig. 7.1 (a) A minimal control loop
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Fig. 7.2 (a) When attitude conditio
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fixed point in the hover despite ex
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(a) (b) Fig. 7.4 (a) The earth beha
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7.4 Compass errors A magnetic compa
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In most cases the machine will have
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Fig. 7.7 The remote indicator for a
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is set by the use of a control knob
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Fig. 7.11 The VSI (vertical speed i
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Fig. 7.13 A chaser system which all
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e modified if the gyro is in a movi
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must be in steady flight when the D
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arranged on opposite sides of the p
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Fig. 7.19 The turn indicator is spr
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7.17 Airflow-sensing devices The he
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Fig. 7.24 Using RADAR signals. At (
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Fig. 7.27 Transducers used in signa
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Fig. 7.28 In PCM or digital signall
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(a) Fig. 7.30 Using slicing and rec
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Fig. 7.33 The false codes created i
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Fig. 7.35 In a pure binary system,
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Fig. 7.38 Producing two’s complem
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Fig. 7.40 A power-assisted hydrauli
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Fig. 7.42 An electro-hydraulic valv
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path axis and the flybar axis diver
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and autostabilization, it also prov
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Fig. 7.47 The Lockheed gyrobar syst
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Fig. 7.49 In the Lockheed AMCS, the
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Fig. 7.50 With the autopilot diseng
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or without the AFCS. Systems of thi
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Thus if a VOR receiver detected a 9
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7.29 Fault tolerance In feedback sy
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8 Helicopter performance 8.1 Introd
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Helicopter performance 325 column i
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Helicopter performance 327 Fig. 8.1
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Helicopter performance 329 to skid
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(a) (b) Helicopter performance 331
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Helicopter performance 333 Fig. 8.7
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Page 354 and 355: Helicopter performance 339 of its c
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Page 360 and 361: Helicopter performance 345 moment f
Page 362 and 363: 9 Other types of rotorcraft Althoug
Page 364 and 365: Other types of rotorcraft 349 De la
Page 366 and 367: Other types of rotorcraft 351 Fig.
Page 368 and 369: Other types of rotorcraft 353 incre
Page 370 and 371: Other types of rotorcraft 355 and c
Page 372 and 373: Fig. 9.7 The Bell-Boeing Osprey til
Page 374 and 375: (a) (b) Other types of rotorcraft 3
Page 380 and 381: Other types of rotorcraft 365 a low
Page 382 and 383: Other types of rotorcraft 367 the y
Page 386 and 387: Other types of rotorcraft 371 the r
Page 388 and 389: Other types of rotorcraft 373 For e
Page 394 and 395: Acceleration: and force, 22-5 and v
Page 396 and 397: Convertiplane, 11-12, 355-8 Bell-Bo
Page 398 and 399: tanks, 219-20 turbine engines, 237-
Page 402 and 403: centrifugal stiffening, 71, 100 and
Page 404 and 405: tail/main rotor interaction, 173 te
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