Download - NASA

More documents

Recommendations

Info

74 Fuselage
Chapter 10 Landing Gear There is one landing-gear component for the aircraft. The landing gear can be located on the body or on the wing. The landing gear can be fixed or retractable; a gear retraction speed is specified (CAS), or the landing-gear state can be specified in the flight state. 10–1 Geometry The landing gear has a position z F , where the aerodynamic forces act. The component axes are aligned with the aircraft axes, C BF = I. The landing gear has no control variables. The height of the bottom of the landing gear above ground level, hLG, is specified in the flight state. The landing-gear position z F is a distance dLG above the bottom of the gear. 10-1.1 Drag The drag area is specified for landing gear extended, (D/q)LG. The velocity relative to the air at z F gives the drag direction ed = −v F /|v F | and dynamic pressure q = 1/2ρ|v F | 2 (no interference). Then is the total drag force. F F = ed q(D/q)LG 10–2 Weights The alighting gear group consists of basic structure, retraction, and crashworthiness structure.
Page 1 and 2:
NASA/TP-2009-215402 NDARC NASA Desi
Page 3 and 4:
NASA/TP-2009-215402 NDARC NASA Desi
Page 5 and 6:
TABLE OF CONTENTS CHAPTER 1 - INTRO
Page 7:
TABLE OF CONTENTS (cont.) CHAPTER 1
Page 10 and 11:
viii LIST OF FIGURES (cont.) Figure
Page 13 and 14:
Chapter 1 Introduction The NASA Des
Page 15 and 16:
Introduction 3 of rotorcraft config
Page 17 and 18:
Introduction 5 previous case DESIGN
Page 19 and 20:
Introduction 7 4) Scully, M.; and F
Page 21 and 22:
Chapter 2 Nomenclature The nomencla
Page 23 and 24:
Nomenclature 11 Fuel Tanks Power Na
Page 25 and 26:
Nomenclature 13 Motion aF AC aircra
Page 27 and 28:
Chapter 3 Tasks The NDARC code perf
Page 29 and 30:
Tasks 17 engine group is found (inc
Page 31 and 32:
Tasks 19 3-4 Maps 3-4.1 Engine Perf
Page 33 and 34:
Chapter 4 Operation 4-1 Flight Cond
Page 35 and 36: Operation 23 e) Input payload weigh
Page 37 and 38: Operation 25 Table 4-1. Mission seg
Page 39 and 40: Operation 27 horizontal ground dist
Page 41 and 42: Operation 29 climb for zero power m
Page 43 and 44: Operation 31 a) Horizontal velocity
Page 45 and 46: Operation 33 From the pressure p =
Page 47 and 48: Chapter 5 Solution Procedures The N
Page 49 and 50: Solution Procedures 37 Sizing Task
Page 51 and 52: Solution Procedures 39 relaxation i
Page 53 and 54: Solution Procedures 41 Table 5-4. T
Page 55 and 56: Solution Procedures 43 successive s
Page 57 and 58: Solution Procedures 45 initialize e
Page 59 and 60: Chapter 6 Cost Costs are estimated
Page 61 and 62: Cost 49 Table 6-1. DoD and CPI infl
Page 63 and 64: Cost 51 predicted base price (1994$
Page 65 and 66: Chapter 7 Aircraft The aircraft con
Page 67 and 68: Aircraft 55 The tilt control variab
Page 69 and 70: Aircraft 57 forward axes for descri
Page 71 and 72: Aircraft 59 For steady-state flight
Page 73 and 74: Aircraft 61 where Δz F = z F − z
Page 75 and 76: Aircraft 63 disk area); or the drag
Page 77 and 78: Aircraft 65 7-10 Performance Indice
Page 79 and 80: Aircraft 67 WEIGHT EMPTY STRUCTURE
Page 81 and 82: Chapter 8 Systems The systems compo
Page 83 and 84: Chapter 9 Fuselage There is one fus
Page 85: Fuselage 73 αe = αfus − αzl, w
Page 89 and 90: Chapter 11 Rotor The aircraft can h
Page 91 and 92: Rotor 79 propulsion group. The driv
Page 93 and 94: Rotor 81 plane command. The collect
Page 95 and 96: Rotor 83 or just CSF = WCHF with no
Page 97 and 98: Rotor 85 If μ is zero, the equatio
Page 99 and 100: Rotor 87 The velocity ratio is fW =
Page 101 and 102: Rotor 89 T/T ∞ 1.3 1.2 1.1 1.0 Ha
Page 103 and 104: Rotor 91 TPP tilt / cyclic magnitud
Page 105 and 106: Rotor 93 with an average over the r
Page 107 and 108: Rotor 95 (all equal to 1 for μz =0
Page 109 and 110: Rotor 97 κ 1.30 1.25 1.20 1.15 1.1
Page 111 and 112: Rotor 99 (C T /σ) s c d mean 0.20
Page 113 and 114: Rotor 101 11-5.1.3 Twin Rotors For
Page 115 and 116: Rotor 103 The wake is a skewed cyli
Page 117 and 118: Rotor 105 weight per lifting rotor;
Page 119 and 120: Chapter 12 Force The force componen
Page 121 and 122: Chapter 13 Wing The aircraft can ha
Page 123 and 124: Wing 111 denotes outboard edge, sub
Page 125 and 126: Wing 113 13-3.1 Lift The wing lift
Page 127 and 128: Wing 115 The wing interference at t
Page 129 and 130: Chapter 14 Empennage The aircraft c
Page 131 and 132: Empennage 119 14-4 Weights The tail
Page 133 and 134: Chapter 15 Fuel Tank 15-1 Fuel Capa
Page 135 and 136: Fuel Tank 123 if Wfuel >Wfuel−max
Page 137 and 138:
Chapter 16 Propulsion The propulsio
Page 139 and 140:
Propulsion 127 If the sum of the fi
Page 141 and 142:
Chapter 17 Engine Group The engine
Page 143 and 144:
Engine Group 131 The engine group p
Page 145 and 146:
Engine Group 133 specific fuel cons
Page 147 and 148:
Chapter 18 Referred Parameter Turbo
Page 149 and 150:
Referred Parameter Turboshaft Engin
Page 151 and 152:
Page 153 and 154:
Page 155 and 156:
Page 157 and 158:
Page 159 and 160:
Chapter 19 AFDD Weight Models This
Page 161 and 162:
AFDD Weight Models 149 The spar-cap
Page 163 and 164:
AFDD Weight Models 151 19-1.2 Aircr
Page 165 and 166:
AFDD Weight Models 153 where w = nz
Page 167 and 168:
AFDD Weight Models 155 units as use
Page 169 and 170:
AFDD Weight Models 157 Table 19-9.
Page 171 and 172:
AFDD Weight Models 159 where fP = f
Page 173 and 174:
AFDD Weight Models 161 The conversi
Page 175 and 176:
AFDD Weight Models 163 19-12 Foldin
Page 177 and 178:
AFDD Weight Models 165 error (%) er
Page 179 and 180:
Page 181 and 182:
Page 183 and 184:
Page 185 and 186:
Page 187 and 188:
show all

Download - NASA

You also want an ePaper? Increase the reach of your titles

Delete template?

Save as template?