Download e-book for iPad: Advances in Control Theory and Applications by Manuel Béjar, Anibal Ollero, Federico Cuesta (auth.),

By Manuel Béjar, Anibal Ollero, Federico Cuesta (auth.), Claudio Bonivento, Lorenzo Marconi, Carlo Rossi, Alberto Isidori (eds.)

ISBN-10: 354070700X

ISBN-13: 9783540707004

This quantity is the end result of the 1st CASY workshop on "Advances up to the mark idea and purposes" which used to be held at college of Bologna on may possibly 22-26, 2006. It includes chosen contributions by way of the various invited audio system and includes contemporary ends up in control.

The quantity is meant for engineers, researchers, and scholars up to speed engineering.

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N }, a feedback K is said to be compatible with G if GK is a subgraph of G (we will use the notation GK ⊆ G). The average consensus problem is said to be solvable on a graph G if there exists a feedback K compatible with G solving the average consensus problem. The following result completely characterize those graphs for which the average consensus problem is solvable. Proposition 1. Let G be a directed graph and assume that G contains all loops (i, i). The following conditions are equivalent: (A) The average consensus problem is solvable on G.

The first design presented considers the case in which the tethers connecting each helicopter to the load are 26 M. B´ejar, A. Ollero, and F. Cuesta equal in length, and the second considers the case in which the tether lengths are unequal. Both designs are based on a seven degree of freedom model linearized about hover. The primary objective of each controller is to minimize the control action and pitching motion required to stabilize the helicopters as they perform elementary maneuvers. A simulation of a typical TLHS command scenario is used to evaluate stability and robustness of the resulting two feedback systems with respect to structured parametric uncertainty.

22 M. B´ejar, A. Ollero, and F. Cuesta from the origin. Notice that the existence of the stable limit cycle prevents the helicopter from becoming totally unstable. Instead of this, the helicopter will exhibit a permanent stable oscillation. If the error is even larger, the stable limit cycle will attract the helicopter preventing again from instability (see Fig. 12). Fig. 12. Altitude error vs. vertical velocity phase plane Clearly, from the point of view of model validation, testing a controller like this one on the real helicopter has several advantages.

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Advances in Control Theory and Applications by Manuel Béjar, Anibal Ollero, Federico Cuesta (auth.), Claudio Bonivento, Lorenzo Marconi, Carlo Rossi, Alberto Isidori (eds.)


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