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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 "

Introductory Circuit Analysis (13th Edition)
Introductory Circuit Analysis (13th Edition)
13th Edition
ISBN:9780133923605
Author:Robert L. Boylestad
Publisher:Robert L. Boylestad
Chapter1: Introduction
Section: Chapter Questions
Problem 1P: Visit your local library (at school or home) and describe the extent to which it provides literature...
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Is the system controllable? Is the system stabilizable?

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 "
Transcribed Image Text: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 "
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