A Mathematical Model of a Single Main Rotor Helicopter for ... - Read

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Name Aircraft mass and inertia Aircraft weight Aircraft roll inertia Aircraft pitch inertia Aircraft yaw inertia Aircraft cross product of inertia Center of gravity stationline Center of gravity waterline Center of gravity buttline Fuselage (Fus) Fus aerodynamic reference point stat ion line Fus aerodynamic reference point wa t er 1 ine Fus drag, c1 = B = 0 Fus drag, variation with ci Fus drag, variation with a2 Fus drag, variation with B2 Fus drag, cx = 90" Fus drag, 6 = 90" Fus lift, a = B = 0 TABLE J-1. - Continued . A1 g eb ra ic C ompu t e r Examp le Units symbol mnemonic value - LO q WAITIC XIXXIC XIYYIC XIZZIC XIXZIC STACG WLCG BLCG STAACF WLACF D1 D2 D3 D4 D5 D6 lb slug-f t slug-f t slug-f t slug-f t in. in. in. in. in. f t2 f t2/rad f t /rad2 f t2/rad2 f t2 f t2 XLO ft2 8000 2700 12800 10800 950 196 73 0 200 54 5.5 -4.01 41.56 141.16 84.7 156.1 -4.11 Fus lift, variation with a a (L/q) aa XL1 f t2/rad 15.64 Fus side force, variation with B a (Y/q) a6 Y1 f t2/rad 93.85 Fus rolling moment, variation with B a(R/q) at3 YL1 ft3/rad 246.31 Fus rolling moment, B = 90" YL2 ft3 0 43
Fus pitch moment, a = B = 0 TABLE J-1.- Continued. Algebraic Computer Example Name symbol mnemonic Units value Fus pitch moment, variation with a Fus pitch moment, a = 90” Fus yaw moment, variation with f3 Fus yaw moment, B = 90” Horizontal stabilizer (HS) HS station HS waterline HS incidence angle HS area HS aspect ratio HS maximum lift curve slope HS dynamic pressure ratio Main rotor induced velocity effect at HS Vertical fin (VF) VF s ta tionline Vertical fin waterline VF Incidence angle VF area VF aspect ratio VF sweep angle VF maximum lift curve slope VF dynamic pressure ratio Tail rotor induced velocity effect at VF M 9 a (M/q) aa MI 4 a=90 a (N/q) STAHS WLHS iHS sHS ARH S C ImaxHS “HS K~~~ STAVF WLVF iVF SVF ARVF AF C ImaxVF qVF k~~~ 44 XM1 xM2 xM3 xN1 xN2 STAHS WLHS AIHS SHS ARHS CLMHS X” XKVMR STAVF WLVF AIFF SF AFtF ALMF CLMF VNF XKVTR ftj -6.901 f t3 /rad 280.405 ft3 300 f t3 /rad -913.35 ft3 -600 in. in. rad ft2 N-D N-D N-D N-D in. in. rad ft2 N-D rad N-D N-D N-D 398.5 56.0 0 14.7 3.0 1.2 0.8 1.0 50 1 84 0 18.6 1.56 0.7853 1.2 0.9 0.9 m -? s c
Page 1 and 2: 1 \ 1 i I ! t ... NASA Technical Me
Page 3 and 4: I . I CONTENTS SuMMAEtY ...........
Page 5 and 6: 1 2 3 4 B- 1 B-2 D- 1 FIGURES Block
Page 7 and 8: 0 Q p 0 16 9 2 w a, U & 3 4 t4 0 U
Page 9 and 10: summing the contributions, to each
Page 11 and 12: sideslip that will be encountered a
Page 13 and 14: gust levels. For this representatio
Page 15 and 16: damping matrix in flapping differen
Page 17 and 18: 0 Euler pitch angle, rad 00 et A bl
Page 19 and 20: HU B-BODY AIRCRAFT REFERENCE SYSTEM
Page 21 and 22: 1w II 8 2 + - + w 0 N Nlm I n "w (N
Page 23 and 24: 18 c
Page 25 and 26: (-& Q = nb pacR2 (RR) [l + (1 - - (
Page 27 and 28: (B, is defined as zero if VH = UH =
Page 29 and 30: 1 + jJ KlTRblTR - a blm +-- 4 'TR T
Page 31 and 32: This implicit relationship is solve
Page 33 and 34: APPENDIX E EMPENNAGE FORCES AND MOM
Page 35 and 36: The angle iHs is the incidence of t
Page 37 and 38: APPENDIX F CALCULATION OF FUSELAGE
Page 39 and 40: The forces and moments in the body-
Page 41 and 42: It is important to note that the cu
Page 43 and 44: c, = ‘C, (s) The terms CK1 and CK
Page 45 and 46: a 8 a m a ma a 0 a m 0. a 3" a m a
Page 47: TABLE J-1.- CONFIGURATION DESCRIPTI
Page 51 and 52: REFERENCES l . 1 . Sinacori, J. B.;

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