Adaptive Output Tracking Control for Nonlinear Systems with Failed Actuators and Aircraft Flight System Applications

<div>The adaptive parameter <svg height="8.64656pt" id="M321" style="vertical-align:-0.04981995pt" version="1.1" viewbox="-0.0498162 -8.59674 7.41997 8.64656" width="7.41997pt" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink"><g transform="matrix(.013,0,0,-0.013,0,0)"><path d="M567 167L534 181C505 122 482 94 454 70C428 46 385 42 330 42C288 42 248 44 235 55C216 70 213 91 220 130L295 528C310 609 314 611 401 618L409 650H140L131 618C222 611 224 609 209 528L133 126C118 47 108 41 25 33L18 0H497C514 33 554 126 567 167Z" id="g50-77"></path><glyph.data ascent="3443" descent="-2856" horiz-adv-x="579" vert-adv-y="579"></glyph.data></g></svg> and the unmeasured state <svg height="9.05107pt" id="M322" style="vertical-align:-3.05102pt" version="1.1" viewbox="-0.0498162 -6.00005 12.4056 9.05107" width="12.4056pt" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink"><g transform="matrix(.013,0,0,-0.013,0,0)"><path d="M545 403C545 425 527 451 498 451C448 451 400 404 312 286L290 341C262 412 246 451 219 451C182 451 138 404 92 345L112 323C152 368 169 378 181 378C192 378 201 359 216 321L257 214C184 115 142 69 113 69C102 69 93 73 88 79S78 89 68 89C47 89 24 61 24 40C24 8 49 -12 75 -12C125 -12 175 31 271 175L312 64C330 15 357 -12 382 -12C421 -12 475 35 515 98L496 121C466 88 439 62 420 62C402 62 384 92 363 147L325 247C349 280 374 309 397 333C422 361 446 381 462 381C471 381 481 374 488 366C493 360 499 357 505 357C521 357 545 380 545 403Z" id="g50-121"></path><glyph.data ascent="3443" descent="-2856" horiz-adv-x="569" vert-adv-y="569"></glyph.data></g><g transform="matrix(.0091,0,0,-0.0091,7.332,3.001)"><path d="M462 177V227H365V632H320C216 495 117 351 21 208V177H284V109C284 42 281 39 190 31V0H451V31C369 39 365 42 365 108V177H462ZM284 227H88C156 336 218 430 282 519H284V227Z" id="g58-50"></path><glyph.data ascent="1007" descent="-369" horiz-adv-x="487" vert-adv-y="487"></glyph.data></g></svg>.</div>

Mathematical Problems in Engineering

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Figure 11

Figure 11: Adaptive Output Tracking Control for Nonlinear Systems with Failed Actuators and Aircraft Flight System Applications 