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

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Y APPENDIX H COCKPIT CONTROLS AND CYCLIC CONTROL PHASING Cyclic, collective, and pedal controls may be specified from a zero position either centered or full left or down. The cyclic control position must be consistent between longitudinal and lateral cyclic, that is, centered or full left and forward. The zero position of the collective or pedals may be specified independently. The table below lists the zero position, positive direction, and sign of the moment or force produced in the body system of axes. Alternate control zero position conventions are listed in parentheses. Control Longitudinal cyclic, 6, Lateral cyclic, 6, Collective, tic Pedals, 6p Zero position Positive direction Moment/force Centered Aft (full forward) Centered Right (full left) Full down UP -Z Centered Right pedal +N (full left) forward The control gearing, rigging, and cyclic control phasing are governed by the following equations : e, = C,6, + c, = C b +c, 'OTR 8 P The terms , C,, and C, are the constant or rigging terms for each 2- control. The terms C, through C, can be used to adjust for the phase angle between 4 the cyclic control input and the resulting flapping. These phase angle terms may be specified in two ways. First, a cyclic control phase relationship may be specified c on the basis of main rotor dynamic properties: c, = 1 - (8/3)~ + 2~~ 1 - (4/3)€ 37 (CK2) +M +L
c, = ‘C, (s) The terms CK1 and CK2 are the longitudinal and lateral cyclic control sensitivities, respectively. As an alternative, a control phase angle, Jlo, may be specified, which Y provides the following rela tionships: C, = (CK2)cos q0 . C, = (CK2)sin Jl,, c, = -c, (s) 38 .
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: It is important to note that the cu
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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