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

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s % P Q R S S STA T W W H vi Wf WL Z a % 6" Y 6 6a 4. &C 6P E n torque, N-m (ft-lb) rotor radius, m (ft) Laplace variable area of stabilizing surface, m2 (ft2) longitudinal location in the fuselage axes system, m (ft) thrust, N (lb) longitudinal, lateral, and vertical velocities in the body-c.g. system of axes, m/sec (ft/sec) longitudinal, lateral, and vertical velocities relative to the air mass in the body-c.g. system of axes, m/sec (ft/sec) longitudinal, lateral, and vertical velocities relative to the air mass in the air mass in the hub-body system of axes, m/sec (ft/sec) main rotor induced velocity at rotor disk, m/sec (ft/sec) fuel flow rate, N/hr (lb/hr) vertical location in the fuselage axes system, m (ft) longitudinal, lateral, and vertical forces in the body-c.g. axes system, N (Ib) stabilizing surface angle of attack, rad angle of attack for stall, rad rotor sideslip angle, rad blade Lock number, pacR4/Ig equivalent rotor blade profile drag coefficient lateral cyclic stick movement, positive to right, cm (in.) collective control input, positive up, cm (in.) longitudinal cyclic stick movement, positive aft, cm (in.) pedal movement, positive right, cm (in.) hinge offset ratio, e/R stabilizing surface lift efficiency factor 11
0 Euler pitch angle, rad 00 et A blade root collective pitch, rad total blade twist (root minus tip incidence), rad WH CT inflow ratio A - - = 2(v2 + A2)1/2 A sweepback angle of fin, rad rotor advance ratio, /uH2 + VH2 aR P air desntiy, kg/m3 (slugs/ft3> (5 T time constant 9 Euler roll angle, rad R rotor angular velocity, rad/sec Sub scripts: B c.g. E f F H HS i MR P t TR W rotor solidity ratio, blade area/disk area body-c.g. axes system relative to air mass center of gravity engine fuselage vertical fin hub-body axes system, hub location horizon tal stabilizer induced main rotor pi lot input throttle tail rotor hub-wind system of axes 12
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: damping matrix in flapping differen
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 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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