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68 Aircraft SYSTEMS AND EQUIPMENT flight controls group cockpit controls automatic flight control system system controls fixed wing systems non-boosted (*), boost mechanisms (*) rotary wing systems non-boosted (*), boost mechanisms (*), boosted (*) conversion systems non-boosted (*), boost mechanisms (*) auxiliary power group instruments group hydraulic group fixed wing (*), rotary wing (*), conversion (*) equipment (*) pneumatic group electrical group avionics group (mission equipment) armament group armament provisions (*), armor (*) furnishings & equipment group environmental control group anti-icing group electrical system (*), anti-ice system (*) load & handling group VIBRATION (*) CONTINGENCY FIXED USEFUL LOAD crew fluids (oil, unusable fuel) (*) auxiliary fuel tanks other fixed useful load (*) furnishings increment (*) folding kit (*) wing extension kit (*) other kit (*) PAYLOAD USABLE FUEL standard tanks (*) auxiliary tanks (*) OPERATING WEIGHT = weight empty + fixed useful load USEFUL LOAD = fixed useful load + payload + usable fuel GROSS WEIGHT = weight empty + useful load GROSS WEIGHT = operating weight + payload + usable fuel Figure 7-2b. Weight statement (* indicates extension of RP8A).
Chapter 8 Systems The systems component contains weight information (fixed useful load, vibration, contingency, and systems and equipment). 8–1 Weights The weight empty consists of structure, propulsion group, systems and equipment, vibration, and contingency weights. The vibration control weight can be input, or specified as a fraction of weight empty: Wvib = fvibWE. The contingency weight can be input, or specified as a fraction of weight empty: Wcont = fcontWE. However, if the weight empty is input, then the contingency weight is adjusted so WE equals the required value. The weights of all components are evaluated and summed, producing the aircraft weight empty less vibration and contingency weight, WX. Then: a) Fixed weight empty: Wvib input or Wvib = fvibWE; Wcont = WE − (WX + Wvib). b) Both fractional: WE = WX/(1 − fvib − fcont), Wvib = fvibWE, Wcont = fcontWE. c) Only vibration weight fractional: Wcont input, WE =(WX + Wcont)/(1 − fvib), Wvib = fvibWE. d) Only contingency weight fractional: Wvib input, WE =(WX + Wvib)/(1 − fcont), Wcont = fcontWE. e) Both input: Wvib and Wcont input, WE = WX + Wvib + Wcont. Finally, the operating weight WO = WE + WFUL is recalculated. The fixed useful load WFUL consists of crew (Wcrew), trapped fluids (oil and unusable fuel, Wtrap), auxiliary fuel tanks (Wauxtank), furnishings increment, kits (folding, wing extension, other), and other fixed useful load (WFULother). Wcrew, Wtrap, and WFULother are input. For a each flight state, the fixed useful load may be different than the design configuration because of changes in auxiliary-fuel-tank weight, kit weight, and crew or furnishings weight increments. Folding weights can be calculated in several weight groups, including wing, rotor, and fuselage. These weights are the total weights for folding and the impact of folding on the group. A fraction ffoldkit of these weights can be in a kit, hence optionally removable. Thus of the total folding weight, the fraction ffoldkit is a kit weight in the fixed useful load of the weight statement, while the remainder is kept in the component group weight. Systems and equipment includes the following fixed (input) weights: auxiliary power group, instruments group, pneumatic group, electrical group, avionics group (mission equipment), armament group (armor and armament provisions), furnishings and equipment group, environmental control group, and load and handling group. Systems and equipment includes the following scaled weights: flight controls group, hydraulic group, and anti-icing group.
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NASA/TP-2009-215402 NDARC NASA Desi
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NASA/TP-2009-215402 NDARC NASA Desi
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TABLE OF CONTENTS CHAPTER 1 - INTRO
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TABLE OF CONTENTS (cont.) CHAPTER 1
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viii LIST OF FIGURES (cont.) Figure
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Chapter 1 Introduction The NASA Des
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Introduction 3 of rotorcraft config
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Introduction 5 previous case DESIGN
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Introduction 7 4) Scully, M.; and F
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Chapter 2 Nomenclature The nomencla
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Nomenclature 11 Fuel Tanks Power Na
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Nomenclature 13 Motion aF AC aircra
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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: Aircraft 67 WEIGHT EMPTY STRUCTURE
Page 83 and 84: Chapter 9 Fuselage There is one fus
Page 85 and 86: Fuselage 73 αe = αfus − αzl, w
Page 87 and 88: Chapter 10 Landing Gear There is on
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
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Empennage 119 14-4 Weights The tail
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Chapter 15 Fuel Tank 15-1 Fuel Capa
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Fuel Tank 123 if Wfuel >Wfuel−max
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Chapter 16 Propulsion The propulsio
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Propulsion 127 If the sum of the fi
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Chapter 17 Engine Group The engine
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Engine Group 131 The engine group p
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Engine Group 133 specific fuel cons
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Chapter 18 Referred Parameter Turbo
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Referred Parameter Turboshaft Engin
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Chapter 19 AFDD Weight Models This
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AFDD Weight Models 149 The spar-cap
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AFDD Weight Models 151 19-1.2 Aircr
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AFDD Weight Models 153 where w = nz
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AFDD Weight Models 155 units as use
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AFDD Weight Models 157 Table 19-9.
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AFDD Weight Models 159 where fP = f
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AFDD Weight Models 161 The conversi
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AFDD Weight Models 163 19-12 Foldin
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AFDD Weight Models 165 error (%) er
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