Terminal Sliding Mode Control for Attitude Tracking of Spacecraft Based on Rotation Matrix

<div>The curves of <svg height="10.3417pt" id="M217" style="vertical-align:-4.04996pt" version="1.1" viewbox="-0.0498162 -6.29174 12.9374 10.3417" width="12.9374pt" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink"><g transform="matrix(.0135,0,0,-0.0135,0,0)"><path d="M400 123C365 93 327 80 288 80C216 80 157 134 153 241C251 245 374 254 392 257C414 260 420 273 421 293C421 375 351 454 258 454H257C203 454 148 427 104 383C62 341 30 278 30 202C30 87 103 -12 237 -12C279 -12 357 8 417 99L400 123ZM237 414C276 414 299 362 298 311C298 294 292 291 277 291C236 290 199 289 157 288C164 367 198 414 237 414Z" id="g13-99"></path><glyph.data ascent="1024" descent="-360" horiz-adv-x="437" vert-adv-y="437"></glyph.data></g><g transform="matrix(.0095,0,0,-0.0095,6.787,1.834)"><path d="M490 623L468 651C434 618 405 602 360 602C327 602 300 608 259 619C204 636 179 642 146 642C101 642 46 623 0 561L22 533C59 565 94 582 139 582C175 582 196 573 232 564C277 552 312 542 349 542C396 542 452 559 490 623Z" id="g56-25"></path><glyph.data ascent="3443" descent="-2856" horiz-adv-x="490" vert-adv-y="490"></glyph.data></g><g transform="matrix(.0095,0,0,-0.0095,5.921,3.957)"><path d="M669 29C646 36 629 47 608 69C589 89 568 120 532 175C502 221 466 287 451 316C519 343 576 391 576 479C576 542 547 586 507 613C466 640 415 650 326 650H42V608C115 602 124 593 124 514V138C124 57 112 49 38 42V0H343V42C267 49 258 57 258 138V277H279C311 277 329 265 344 237C373 185 400 130 427 88C467 26 504 -2 632 -8C645 -8 656 -9 662 -9L669 29ZM258 323V556C258 577 260 587 266 594C272 600 285 605 312 605C368 605 431 568 431 465C431 416 418 377 382 348C361 330 327 323 286 323H258Z" id="g22-80"></path><glyph.data ascent="1041" descent="-369" horiz-adv-x="672" vert-adv-y="672"></glyph.data></g></svg> under the controller in [<a href="/journals/mpe/2015/187924/#B18">18</a>].</div>

Mathematical Problems in Engineering

fig12

Figure 12

Figure 12: Terminal Sliding Mode Control for Attitude Tracking of Spacecraft Based on Rotation Matrix 