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50 Cost Table 6-2. Cost model parameters. parameter definition units WE weight empty lb WMTO maximum takeoff weight lb Nblade number of blades per rotor P rated takeoff power (all engines) hp WMEP fixed useful load weight, mission equipment package lb or kg WFCE fixed useful load weight, flight control electronics lb or kg rMEP cost factor, mission equipment package $/lb or $/kg rFCE cost factor, flight control electronics $/lb or $/kg L additional labor rate for composite construction $/lb or $/kg Wfuel mission fuel burned lb or kg Tmiss mission time hr Rmiss mission range nm G fuel cost $/gallon or $/liter B available block hours hr S spares per aircraft (fraction purchase price) D depreciation period yr V residual value (fraction) L loan period yr i interest rate % TNF non-flight time per trip hr Npass number of passengers ρfuel fuel density (weight per volume) lb/gal or kg/liter 6–2 References 1) National Defense Budget Estimates for FY 1998/2010. Office of the Under Secretary of Defense (Comptroller), March 1997/2008. Department of Defense deflators, for Total Obligational Authority (TOA), Procurement. 2) Consumer Price Index. U.S. Department Of Labor, Bureau of Labor Statistics, 2009. All Urban Consumers (CPI-U), U.S. city average, all items. 3) Harris, F.D.; and Scully, M.P.: Rotorcraft Cost Too Much. Journal of the American Helicopter Society, vol. 43, no. 1, January 1998. 4) Harris, F.D.: An Economic Model of U.S. Airline Operating Expenses. <strong>NASA</strong> CR 2005-213476, December 2005. 5) Coy, J.J.: Cost Analysis for Large Civil Transport Rotorcraft. American Helicopter Society Vertical Lift Aircraft Design Conference, San Francisco, California, January 2006.
Cost 51 predicted base price (1994$/lb) 1000. 900. 800. 700. 600. 500. 400. 300. 200. 100. no error ±10% ±20% aircraft 0. 0. 100. 200. 300. 400. 500. 600. 700. 800. 900. 1000. actual base price (1994$/lb) Figure 6-1. Statistical estimation of rotorcraft flyaway cost ($/lb).
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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
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: Cost 49 Table 6-1. DoD and CPI infl
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 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
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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
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Wing 111 denotes outboard edge, sub
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Wing 113 13-3.1 Lift The wing lift
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Wing 115 The wing interference at t
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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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