-TPP Voo 7 ais is x W HM LH N -0 D QT Voo QM X - Ty sin (istis) y HM cos (istais) D TM cos (istais) bs &QM LH COSO y T Dsin 10% N W CoS O Longitudinal Equation: Fz: Wcos Doos -TM cos(-is-hus) cos bis - HM sin (-is-aus) cos + Dcos sin (-9)-LH COS(-9)=0 Fx: Tm sin (-is-is) + W sin(-O) - Hm cos (-is-dis) cos- Dcos/cos (-0) - LH sin (-8)=0 My: [TM cos (-is-aus) cos bis + Husin (-is-alis) cos] Im + [-Tmsin (-is-ais) + HM cost-is-aus) cos] hm - LH cos(-0)&H -QT -Qm sinbis = 0 M Lateral - Directional Equations: Fy: T+ + Tm sin bis cos(-is-Qus) + W costsin &- Hm sin -Dsin=0 Mz: - TT&T + QM cos (-is-ais) cosbus +TM sinbis cos (-is-is) Im - HM SMB lm =0 20 Mx = (Tm simbas - Hy sim) hm +T+h+ - Qusin (-is-as) = unknowns: TM, HM, LH, B, O, I, ais, bis, QM, QT, TT 1. You are to trim a hovering helicopter. (a) Write the six trim equations for the helicopter in hover. = = (b) You may assume that both main rotor and tail rotor require only ideal power (neglect profile power). Use the following helicopter parameters: W = 32,000 N, is = -5, A = 95 m, AT m, 40.2 1/s, T 228 1/s, br = 6.5 m, ht lT .72 m, and h .96 m. Also note that p = 1.225 kg/m at sea level. Find values for TM, TT, as, bs, O, and . What is the attitude M 0? For M 0.25 m (center of mass behind the rotor hub)? = 3 = = = = of the helicopter in hover for For M = -0.25 m (center of mass ahead of the rotor hub)? See if you can explain why the solution varies as it does with the change in cm location. (c) What control actions does the pilot have to take in order to trim this helicopter for the given center-of-mass locations? That is, what should be the collective and cyclic control angles? Use a = 6, = 0.075, and t = 8. Ot