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The linearized longitudinal motion of a helicopter near hover can be modeled by the following normalized equations: where ? is the pitch ratio, ? is the hull pitch attitude, ? is the horizontal velocity, and δ is the rotor pitch angle corresponding to the control input. Suppose our sensor measures horizontal velocity ? as output. Automatic Control. 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: where ? is the pitch ratio, ? is the hull pitch attitude, ? is the horizontal velocity, and δ is the rotor pitch angle corresponding to the control input. Suppose our sensor measures horizontal velocity ? as output. Automatic Control. Is the system controllable? Is the system stabilizable?

Introductory Circuit Analysis (13th Edition)
Introductory Circuit Analysis (13th Edition)
13th Edition
ISBN:9780133923605
Author:Robert L. Boylestad
Publisher:Robert L. Boylestad
Chapter1: Introduction
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The linearized longitudinal motion of a helicopter near hover can be modeled by the following normalized equations:

where ? is the pitch ratio, ? is the hull pitch attitude, ? is the horizontal velocity, and δ is the rotor pitch angle corresponding to the control input.
Suppose our sensor measures horizontal velocity ? as output. Automatic Control.

Is the system controllable? Is the system stabilizable?

= -0.011 91 00][ -1.4 9.8 -0.029+ Lu- -0.4 0 1 0 6.31 08 19.8] lage reference axis Vertical 0 Rotor thrust Rotor 21
Transcribed Image Text:= -0.011 91 00][ -1.4 9.8 -0.029+ Lu- -0.4 0 1 0 6.31 08 19.8] lage reference axis Vertical 0 Rotor thrust Rotor 21
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