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

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-. . *. APPENDIX D TAIL ROTOR FLAPPING AND FORCE CALCULATION The tail rotor is assumed to be teetering with a constant built-in coning ao. The angular rate of the tail rotor is sufficiently high so that the tip-path dynamics may be ignored. Under these conditions, a, and b, in the flapping equations are assumed to be constant, and a steady-state solution of the equations is obtained to yield these quantities as follows: where 4 2 ATR = 1 - - 4 TR + K:TR(l + F)(l + 5 PgR) The forces on the tail rotor are then calculated as follows: -a OTR (i + *) KITR + 21 23
1 + jJ KlTRblTR - a blm +-- 4 'TR The positive directions for tail rotor torque and rotation are shown on figure D-1. THRUST ALONG SHAFT INTO PAGE Figure D-1.- Tail rotor forces and moments. 24 3 TR G ROTATION
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: (B, is defined as zero if VH = UH =
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 and 48: TABLE J-1.- CONFIGURATION DESCRIPTI
Page 49 and 50: Fus pitch moment, a = B = 0 TABLE J
Page 51 and 52: REFERENCES l . 1 . Sinacori, J. B.;

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