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

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7 I* where and KB P2 = 1 +- IBn2 g-% +-+- 8 For a two-bladed teetering rotor, the tip-path plane representation loses its physical meaning. However, if the approximation for blade flapping is employed, that is, $(t) = ao(t) - al(t)cos + - bl(t)sin + then a. is treated as a preset constant. The coefficients al(t) and b,(t) can then be solved for by setting E = do = So = 0 in equation (1). The force and moment expressions, with the harmonic terms dropped that correspond to the number of rotor blades are given below. A derivation of these equations is given in reference 2. + 2 *MR = nb 2 pacR(QR)2 (1 - E~)X + 8, [+ + 5 (1 - u2 E)] + 0, [+ + - 4 (1 - E2)] - K b ) - a. [$ + 2 1 1 - 1 (1 - E ~ ) ( B ~ ~ + - [k (1 - yK1 (1 - E)]K~ + a, [; e(l - + 1 (1 - (? cos Bw + sin B)] - - aO n 4 4 W g 61 qH "bMB .. 17 a - (i - ;)
18 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: 1w II 8 2 + - + w 0 N Nlm I n "w (N
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 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.;

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

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