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162 AFDD Weight Models Table 19-18. Parameters for anti-icing group weight. parameter definition units Ablade total blade area of rotor, from geometric solidity ft 2 or m 2 ℓwing wing length (wing span less fuselage width) ft or m kelect electrical system weight factor krotor rotor deice system weight factor kwing wing deice system weight factor engine air intake deice system weight factor kair 19–11 Other Systems and Equipment The following weights are fixed (input) in this model: auxiliary power group; instruments group; pneumatic group; electrical group; avionic group (mission equipment); armament group (armament provisions and armor); furnishing and equipment group; environmental control group; and load and handling group. Typical fixed weights are given in table 19-19, based on medium to heavy helicopters and tiltrotors. Table 19-19. Other systems and equipment weight. group SYSTEMS AND EQUIPMENT flight controls group typical weight (lb) cockpit controls 100–125 automatic flight control system 35–200 flight control electronics, mechanical 35–100 flight control electronics, fly-by-wire 250 auxiliary power group 130–300 instruments group hydraulic group 150-250 equipment 50–300 electrical group 400–1000 avionics group (mission equipment) 400–1500 furnishings & equipment group 600–1000 crew only 100–200 environmental control group 50–250 anti-icing group load & handling group 50–300 internal 200–400 external FIXED USEFUL LOAD 150–300 crew 500–800 fluids (oil, unusable fuel) 50–150
AFDD Weight Models 163 19–12 Folding Weight Folding weights are calculated in a number of groups: wing Wfold (including extensions), rotor Wfold, fuselage Wtfold and Wwfold. These 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 wing, rotor, or fuselage group weight. 19–13 Parametric Weight Correlation Figure 19-24 shows the error of the calculated weight for the sum of all parametric weight, accounting on average for 42% of the empty weight. This sum is composed of the structural group (based on the AFDD00 equation for rotor blade and hub weights, and the AFDD84 equation for body weight), the propulsion group (based on the AFDD00 equation for drive system weight), and the flight controls group. Based on 42 aircraft, the average error of the sum of all parametric weight is 5.3%. The corresponding average error is 6.1% for the structural group (8.6% for the rotor group alone), 10.9% for the propulsion group, and 8.7% for the flight controls group. 19–14 References 1) Chappell, D.; and Peyran, R.: Methodology for Estimating Wing Weights for Conceptual Tilt-Rotor and Tilt-Wing Aircraft. SAWE Paper No. 2107, Category No. 23, May 1992. 2) Chappell, D.P.: Tilt-rotor Aircraft Wing Design. ASRO-PDT-83-1, 1983. 3) Weight Trend Estimation for the Rotor Blade Group, Rotor Hub Group, and Upper Rotor Shaft of the ABC Aircraft. ASRO-PDT-83-2, 1983.
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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
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Tasks 17 engine group is found (inc
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Tasks 19 3-4 Maps 3-4.1 Engine Perf
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Chapter 4 Operation 4-1 Flight Cond
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Operation 23 e) Input payload weigh
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Operation 25 Table 4-1. Mission seg
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Operation 27 horizontal ground dist
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Operation 29 climb for zero power m
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Operation 31 a) Horizontal velocity
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Operation 33 From the pressure p =
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Chapter 5 Solution Procedures The N
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Solution Procedures 37 Sizing Task
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Solution Procedures 39 relaxation i
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Solution Procedures 41 Table 5-4. T
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Solution Procedures 43 successive s
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Solution Procedures 45 initialize e
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Chapter 6 Cost Costs are estimated
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Cost 49 Table 6-1. DoD and CPI infl
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Cost 51 predicted base price (1994$
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Chapter 7 Aircraft The aircraft con
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Aircraft 55 The tilt control variab
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Aircraft 57 forward axes for descri
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Aircraft 59 For steady-state flight
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Aircraft 61 where Δz F = z F − z
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Aircraft 63 disk area); or the drag
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Aircraft 65 7-10 Performance Indice
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Aircraft 67 WEIGHT EMPTY STRUCTURE
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Chapter 8 Systems The systems compo
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Chapter 9 Fuselage There is one fus
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Fuselage 73 αe = αfus − αzl, w
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Chapter 10 Landing Gear There is on
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Chapter 11 Rotor The aircraft can h
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Rotor 79 propulsion group. The driv
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Rotor 81 plane command. The collect
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Rotor 83 or just CSF = WCHF with no
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Rotor 85 If μ is zero, the equatio
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Rotor 87 The velocity ratio is fW =
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Rotor 89 T/T ∞ 1.3 1.2 1.1 1.0 Ha
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Rotor 91 TPP tilt / cyclic magnitud
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Rotor 93 with an average over the r
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Rotor 95 (all equal to 1 for μz =0
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Rotor 97 κ 1.30 1.25 1.20 1.15 1.1
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Rotor 99 (C T /σ) s c d mean 0.20
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Rotor 101 11-5.1.3 Twin Rotors For
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Rotor 103 The wake is a skewed cyli
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Rotor 105 weight per lifting rotor;
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Chapter 12 Force The force componen
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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 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: AFDD Weight Models 161 The conversi
Page 177 and 178: AFDD Weight Models 165 error (%) er
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