The linearized longitudinal motion of a helicopter near hover can be modeled by the following normalized equations: = -0.01] [91 6.3 0 + 8 + -0.02 u 19.81 [-0.4 0 1 0 -1.4 9.8 where q is the pitch rate, is the pitch angle of fuselage, u is the horizontal velocity, and 8 is the rotor tilt angle, which corresponds to the control input. Suppose our sensor measures the horizontal velocity u as the output. Fuselage reference axis Vertical- Rotor thrust Rotor "

The linearized longitudinal motion of a helicopter near hover can be modeled by the following normalized equations: = -0.01] [91 6.3 0 + 8 + -0.02 u 19.81 [-0.4 0 1 0 -1.4 9.8 where q is the pitch rate, is the pitch angle of fuselage, u is the horizontal velocity, and 8 is the rotor tilt angle, which corresponds to the control input. Suppose our sensor measures the horizontal velocity u as the output. Fuselage reference axis Vertical- Rotor thrust Rotor "

Power System Analysis and Design (MindTap Course List)

6th Edition

ISBN:9781305632134

Author:J. Duncan Glover, Thomas Overbye, Mulukutla S. Sarma

Publisher:J. Duncan Glover, Thomas Overbye, Mulukutla S. Sarma

Chapter6: Power Flows

Section: Chapter Questions

Problem 6.22P

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