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vector-toc-level-1"> <a class="vector-toc-link" href="#Actuators"> <div class="vector-toc-text"> <span class="vector-toc-numb">2</span> <span>Actuators</span> </div> </a> <button aria-controls="toc-Actuators-sublist" class="cdx-button cdx-button--weight-quiet cdx-button--icon-only vector-toc-toggle"> <span class="vector-icon mw-ui-icon-wikimedia-expand"></span> <span>Toggle Actuators subsection</span> </button> <ul id="toc-Actuators-sublist" class="vector-toc-list"> <li id="toc-Thrusters" class="vector-toc-list-item vector-toc-level-2"> <a class="vector-toc-link" href="#Thrusters"> <div class="vector-toc-text"> <span class="vector-toc-numb">2.1</span> <span>Thrusters</span> </div> </a> <ul id="toc-Thrusters-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Reaction/momentum_wheels" class="vector-toc-list-item vector-toc-level-2"> <a class="vector-toc-link" href="#Reaction/momentum_wheels"> <div class="vector-toc-text"> <span class="vector-toc-numb">2.2</span> <span>Reaction/momentum wheels</span> </div> </a> <ul id="toc-Reaction/momentum_wheels-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Control_moment_gyros" class="vector-toc-list-item vector-toc-level-2"> <a class="vector-toc-link" href="#Control_moment_gyros"> <div class="vector-toc-text"> <span class="vector-toc-numb">2.3</span> <span>Control moment gyros</span> </div> </a> <ul id="toc-Control_moment_gyros-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Solar_sails" class="vector-toc-list-item vector-toc-level-2"> <a class="vector-toc-link" href="#Solar_sails"> <div class="vector-toc-text"> <span class="vector-toc-numb">2.4</span> <span>Solar sails</span> </div> </a> <ul id="toc-Solar_sails-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Gravity-gradient_stabilization" class="vector-toc-list-item vector-toc-level-2"> <a class="vector-toc-link" href="#Gravity-gradient_stabilization"> <div class="vector-toc-text"> <span class="vector-toc-numb">2.5</span> <span>Gravity-gradient stabilization</span> </div> </a> <ul id="toc-Gravity-gradient_stabilization-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Magnetic_torquers" class="vector-toc-list-item vector-toc-level-2"> <a class="vector-toc-link" href="#Magnetic_torquers"> <div class="vector-toc-text"> <span class="vector-toc-numb">2.6</span> <span>Magnetic torquers</span> </div> </a> <ul id="toc-Magnetic_torquers-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Passive_attitude_control" class="vector-toc-list-item vector-toc-level-2"> <a class="vector-toc-link" href="#Passive_attitude_control"> <div class="vector-toc-text"> <span class="vector-toc-numb">2.7</span> <span>Passive attitude control</span> </div> </a> <ul id="toc-Passive_attitude_control-sublist" class="vector-toc-list"> </ul> </li> </ul> </li> <li id="toc-Algorithms" class="vector-toc-list-item vector-toc-level-1"> <a class="vector-toc-link" href="#Algorithms"> <div class="vector-toc-text"> <span class="vector-toc-numb">3</span> <span>Algorithms</span> </div> </a> <ul id="toc-Algorithms-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Attitude_determination" class="vector-toc-list-item vector-toc-level-1"> <a class="vector-toc-link" href="#Attitude_determination"> <div class="vector-toc-text"> <span class="vector-toc-numb">4</span> <span>Attitude determination</span> </div> </a> <button aria-controls="toc-Attitude_determination-sublist" class="cdx-button cdx-button--weight-quiet cdx-button--icon-only vector-toc-toggle"> <span class="vector-icon mw-ui-icon-wikimedia-expand"></span> <span>Toggle Attitude determination subsection</span> </button> <ul id="toc-Attitude_determination-sublist" class="vector-toc-list"> <li id="toc-Sensors" class="vector-toc-list-item vector-toc-level-2"> <a class="vector-toc-link" href="#Sensors"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.1</span> <span>Sensors</span> </div> </a> <ul id="toc-Sensors-sublist" class="vector-toc-list"> <li id="toc-Relative_attitude_sensors" class="vector-toc-list-item vector-toc-level-3"> <a class="vector-toc-link" href="#Relative_attitude_sensors"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.1.1</span> <span>Relative attitude sensors</span> </div> </a> <ul id="toc-Relative_attitude_sensors-sublist" class="vector-toc-list"> <li id="toc-Gyroscopes" class="vector-toc-list-item vector-toc-level-4"> <a class="vector-toc-link" href="#Gyroscopes"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.1.1.1</span> <span>Gyroscopes</span> </div> </a> <ul id="toc-Gyroscopes-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Motion_reference_units" class="vector-toc-list-item vector-toc-level-4"> <a class="vector-toc-link" href="#Motion_reference_units"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.1.1.2</span> <span>Motion reference units</span> </div> </a> <ul id="toc-Motion_reference_units-sublist" class="vector-toc-list"> </ul> </li> </ul> </li> <li id="toc-Absolute_attitude_sensors" class="vector-toc-list-item vector-toc-level-3"> <a class="vector-toc-link" href="#Absolute_attitude_sensors"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.1.2</span> <span>Absolute attitude sensors</span> </div> </a> <ul id="toc-Absolute_attitude_sensors-sublist" class="vector-toc-list"> <li id="toc-Horizon_sensor" class="vector-toc-list-item vector-toc-level-4"> <a class="vector-toc-link" href="#Horizon_sensor"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.1.2.1</span> <span>Horizon sensor</span> </div> </a> <ul id="toc-Horizon_sensor-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Orbital_gyrocompass" class="vector-toc-list-item vector-toc-level-4"> <a class="vector-toc-link" href="#Orbital_gyrocompass"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.1.2.2</span> <span>Orbital gyrocompass</span> </div> </a> <ul id="toc-Orbital_gyrocompass-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Sun_sensor" class="vector-toc-list-item vector-toc-level-4"> <a class="vector-toc-link" href="#Sun_sensor"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.1.2.3</span> <span>Sun sensor</span> </div> </a> <ul id="toc-Sun_sensor-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Earth_sensor" class="vector-toc-list-item vector-toc-level-4"> <a class="vector-toc-link" href="#Earth_sensor"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.1.2.4</span> <span>Earth sensor</span> </div> </a> <ul id="toc-Earth_sensor-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Star_tracker" class="vector-toc-list-item vector-toc-level-4"> <a class="vector-toc-link" href="#Star_tracker"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.1.2.5</span> <span>Star tracker</span> </div> </a> <ul id="toc-Star_tracker-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Magnetometer" class="vector-toc-list-item vector-toc-level-4"> <a class="vector-toc-link" href="#Magnetometer"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.1.2.6</span> <span>Magnetometer</span> </div> </a> <ul id="toc-Magnetometer-sublist" class="vector-toc-list"> </ul> </li> </ul> </li> </ul> </li> <li id="toc-Estimation_methods" class="vector-toc-list-item vector-toc-level-2"> <a class="vector-toc-link" href="#Estimation_methods"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.2</span> <span>Estimation methods</span> </div> </a> <ul id="toc-Estimation_methods-sublist" class="vector-toc-list"> <li id="toc-Static_attitude_estimation_methods" class="vector-toc-list-item vector-toc-level-3"> <a class="vector-toc-link" href="#Static_attitude_estimation_methods"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.2.1</span> <span>Static attitude estimation methods</span> </div> </a> <ul id="toc-Static_attitude_estimation_methods-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-Sequential_estimation_methods" class="vector-toc-list-item vector-toc-level-3"> <a class="vector-toc-link" href="#Sequential_estimation_methods"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.2.2</span> <span>Sequential estimation methods</span> </div> </a> <ul id="toc-Sequential_estimation_methods-sublist" class="vector-toc-list"> </ul> </li> </ul> </li> <li id="toc-Position/location_determination" class="vector-toc-list-item vector-toc-level-2"> <a class="vector-toc-link" href="#Position/location_determination"> <div class="vector-toc-text"> <span class="vector-toc-numb">4.3</span> <span>Position/location determination</span> </div> </a> <ul id="toc-Position/location_determination-sublist" class="vector-toc-list"> </ul> </li> </ul> </li> <li id="toc-See_also" class="vector-toc-list-item vector-toc-level-1"> <a class="vector-toc-link" href="#See_also"> <div class="vector-toc-text"> <span class="vector-toc-numb">5</span> <span>See also</span> </div> </a> <ul id="toc-See_also-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-References" class="vector-toc-list-item vector-toc-level-1"> <a class="vector-toc-link" href="#References"> <div class="vector-toc-text"> <span class="vector-toc-numb">6</span> <span>References</span> </div> </a> <ul id="toc-References-sublist" class="vector-toc-list"> </ul> </li> <li id="toc-External_links" class="vector-toc-list-item vector-toc-level-1"> <a class="vector-toc-link" href="#External_links"> <div class="vector-toc-text"> <span class="vector-toc-numb">7</span> <span>External links</span> </div> </a> <ul id="toc-External_links-sublist" class="vector-toc-list"> </ul> </li> </ul> </div> </div> </nav> </div> </div> <div class="mw-content-container"> <main id="content" class="mw-body"> <header class="mw-body-header vector-page-titlebar"> <nav aria-label="Contents" class="vector-toc-landmark"> <div id="vector-page-titlebar-toc" class="vector-dropdown vector-page-titlebar-toc vector-button-flush-left" > <input type="checkbox" id="vector-page-titlebar-toc-checkbox" role="button" aria-haspopup="true" data-event-name="ui.dropdown-vector-page-titlebar-toc" class="vector-dropdown-checkbox " aria-label="Toggle the table of contents" > <label id="vector-page-titlebar-toc-label" for="vector-page-titlebar-toc-checkbox" class="vector-dropdown-label cdx-button cdx-button--fake-button cdx-button--fake-button--enabled cdx-button--weight-quiet cdx-button--icon-only " aria-hidden="true" ><span class="vector-icon mw-ui-icon-listBullet mw-ui-icon-wikimedia-listBullet"></span> <span class="vector-dropdown-label-text">Toggle the table of contents</span> </label> <div class="vector-dropdown-content"> <div id="vector-page-titlebar-toc-unpinned-container" class="vector-unpinned-container"> </div> </div> </div> </nav> <h1 id="firstHeading" class="firstHeading mw-first-heading"><span class="mw-page-title-main">Spacecraft attitude control</span></h1> <div id="p-lang-btn" class="vector-dropdown mw-portlet mw-portlet-lang" > <input type="checkbox" id="p-lang-btn-checkbox" role="button" aria-haspopup="true" data-event-name="ui.dropdown-p-lang-btn" class="vector-dropdown-checkbox mw-interlanguage-selector" aria-label="Go to an article in another language. Available in 16 languages" > <label id="p-lang-btn-label" for="p-lang-btn-checkbox" class="vector-dropdown-label cdx-button cdx-button--fake-button cdx-button--fake-button--enabled cdx-button--weight-quiet cdx-button--action-progressive mw-portlet-lang-heading-16" aria-hidden="true" ><span class="vector-icon mw-ui-icon-language-progressive mw-ui-icon-wikimedia-language-progressive"></span> <span class="vector-dropdown-label-text">16 languages</span> </label> <div class="vector-dropdown-content"> <div class="vector-menu-content"> <ul class="vector-menu-content-list"> <li class="interlanguage-link interwiki-ar mw-list-item"><a href="https://ar.wikipedia.org/wiki/%D8%A7%D9%84%D8%AA%D8%AD%D9%83%D9%85_%D8%A8%D8%A7%D9%84%D9%88%D8%B6%D8%B9%D9%8A%D8%A9" title="التحكم بالوضعية – Arabic" lang="ar" hreflang="ar" data-title="التحكم بالوضعية" data-language-autonym="العربية" data-language-local-name="Arabic" class="interlanguage-link-target"><span>العربية</span></a></li><li class="interlanguage-link interwiki-ca mw-list-item"><a href="https://ca.wikipedia.org/wiki/Control_d%27orientaci%C3%B3" title="Control d'orientació – Catalan" lang="ca" hreflang="ca" data-title="Control d'orientació" data-language-autonym="Català" data-language-local-name="Catalan" class="interlanguage-link-target"><span>Català</span></a></li><li class="interlanguage-link interwiki-et mw-list-item"><a href="https://et.wikipedia.org/wiki/Kosmoseaparaadi_orienteerimine" title="Kosmoseaparaadi orienteerimine – Estonian" lang="et" hreflang="et" data-title="Kosmoseaparaadi orienteerimine" data-language-autonym="Eesti" data-language-local-name="Estonian" class="interlanguage-link-target"><span>Eesti</span></a></li><li class="interlanguage-link interwiki-es mw-list-item"><a href="https://es.wikipedia.org/wiki/Control_de_actitud" title="Control de actitud – Spanish" lang="es" hreflang="es" data-title="Control de actitud" data-language-autonym="Español" data-language-local-name="Spanish" class="interlanguage-link-target"><span>Español</span></a></li><li class="interlanguage-link interwiki-fa mw-list-item"><a href="https://fa.wikipedia.org/wiki/%DA%A9%D9%86%D8%AA%D8%B1%D9%84_%D9%88%D8%B6%D8%B9%DB%8C%D8%AA_%D9%81%D8%B6%D8%A7%D9%BE%DB%8C%D9%85%D8%A7" title="کنترل وضعیت فضاپیما – Persian" lang="fa" hreflang="fa" data-title="کنترل وضعیت فضاپیما" data-language-autonym="فارسی" data-language-local-name="Persian" class="interlanguage-link-target"><span>فارسی</span></a></li><li class="interlanguage-link interwiki-fr mw-list-item"><a href="https://fr.wikipedia.org/wiki/Contr%C3%B4le_d%27attitude" title="Contrôle d'attitude – French" lang="fr" hreflang="fr" data-title="Contrôle d'attitude" data-language-autonym="Français" data-language-local-name="French" class="interlanguage-link-target"><span>Français</span></a></li><li class="interlanguage-link interwiki-ko mw-list-item"><a href="https://ko.wikipedia.org/wiki/%EC%9E%90%EC%84%B8_%EC%A0%9C%EC%96%B4" title="자세 제어 – Korean" lang="ko" hreflang="ko" data-title="자세 제어" data-language-autonym="한국어" data-language-local-name="Korean" class="interlanguage-link-target"><span>한국어</span></a></li><li class="interlanguage-link interwiki-ig mw-list-item"><a href="https://ig.wikipedia.org/wiki/Nch%E1%BB%8Bkwa_%E1%BB%8Dn%E1%BB%8Dd%E1%BB%A5_%E1%BB%A5gb%E1%BB%8D_mbara_igwe" title="Nchịkwa ọnọdụ ụgbọ mbara igwe – Igbo" lang="ig" hreflang="ig" data-title="Nchịkwa ọnọdụ ụgbọ mbara igwe" data-language-autonym="Igbo" data-language-local-name="Igbo" class="interlanguage-link-target"><span>Igbo</span></a></li><li class="interlanguage-link interwiki-id mw-list-item"><a href="https://id.wikipedia.org/wiki/Kontrol_posisi_wahana_antariksa" title="Kontrol posisi wahana antariksa – Indonesian" lang="id" hreflang="id" data-title="Kontrol posisi wahana antariksa" data-language-autonym="Bahasa Indonesia" data-language-local-name="Indonesian" class="interlanguage-link-target"><span>Bahasa Indonesia</span></a></li><li class="interlanguage-link interwiki-it mw-list-item"><a href="https://it.wikipedia.org/wiki/Controllo_di_assetto" title="Controllo di assetto – Italian" lang="it" hreflang="it" data-title="Controllo di assetto" data-language-autonym="Italiano" data-language-local-name="Italian" class="interlanguage-link-target"><span>Italiano</span></a></li><li class="interlanguage-link interwiki-lv mw-list-item"><a href="https://lv.wikipedia.org/wiki/Orient%C4%81cijas_noteik%C5%A1ana_un_vad%C4%ABba" title="Orientācijas noteikšana un vadība – Latvian" lang="lv" hreflang="lv" data-title="Orientācijas noteikšana un vadība" data-language-autonym="Latviešu" data-language-local-name="Latvian" class="interlanguage-link-target"><span>Latviešu</span></a></li><li class="interlanguage-link interwiki-ja mw-list-item"><a href="https://ja.wikipedia.org/wiki/%E5%A7%BF%E5%8B%A2%E5%88%B6%E5%BE%A1" title="姿勢制御 – Japanese" lang="ja" hreflang="ja" data-title="姿勢制御" data-language-autonym="日本語" data-language-local-name="Japanese" class="interlanguage-link-target"><span>日本語</span></a></li><li class="interlanguage-link interwiki-pt mw-list-item"><a href="https://pt.wikipedia.org/wiki/Controle_de_atitude" title="Controle de atitude – Portuguese" lang="pt" hreflang="pt" data-title="Controle de atitude" data-language-autonym="Português" data-language-local-name="Portuguese" class="interlanguage-link-target"><span>Português</span></a></li><li class="interlanguage-link interwiki-ru mw-list-item"><a href="https://ru.wikipedia.org/wiki/%D0%A1%D0%B8%D1%81%D1%82%D0%B5%D0%BC%D0%B0_%D0%BE%D1%80%D0%B8%D0%B5%D0%BD%D1%82%D0%B0%D1%86%D0%B8%D0%B8_%D0%BA%D0%BE%D1%81%D0%BC%D0%B8%D1%87%D0%B5%D1%81%D0%BA%D0%BE%D0%B3%D0%BE_%D0%B0%D0%BF%D0%BF%D0%B0%D1%80%D0%B0%D1%82%D0%B0" title="Система ориентации космического аппарата – Russian" lang="ru" hreflang="ru" data-title="Система ориентации космического аппарата" data-language-autonym="Русский" data-language-local-name="Russian" class="interlanguage-link-target"><span>Русский</span></a></li><li class="interlanguage-link interwiki-ta mw-list-item"><a href="https://ta.wikipedia.org/wiki/%E0%AE%B5%E0%AE%BF%E0%AE%A3%E0%AF%8D%E0%AE%95%E0%AE%B2%E0%AE%A4%E0%AF%8D_%E0%AE%A4%E0%AE%BF%E0%AE%9A%E0%AF%88%E0%AE%B5%E0%AF%88%E0%AE%AA%E0%AF%8D%E0%AE%AA%E0%AF%81%E0%AE%95%E0%AF%8D_%E0%AE%95%E0%AE%9F%E0%AF%8D%E0%AE%9F%E0%AF%81%E0%AE%AA%E0%AF%8D%E0%AE%AA%E0%AE%BE%E0%AE%9F%E0%AF%81" title="விண்கலத் திசைவைப்புக் கட்டுப்பாடு – Tamil" lang="ta" hreflang="ta" data-title="விண்கலத் திசைவைப்புக் கட்டுப்பாடு" data-language-autonym="தமிழ்" data-language-local-name="Tamil" class="interlanguage-link-target"><span>தமிழ்</span></a></li><li class="interlanguage-link interwiki-uk mw-list-item"><a href="https://uk.wikipedia.org/wiki/%D0%A1%D0%B8%D1%81%D1%82%D0%B5%D0%BC%D0%B0_%D0%BE%D1%80%D1%96%D1%94%D0%BD%D1%82%D0%B0%D1%86%D1%96%D1%97_%D0%BA%D0%BE%D1%81%D0%BC%D1%96%D1%87%D0%BD%D0%BE%D0%B3%D0%BE_%D0%BF%D1%80%D0%B8%D0%BB%D0%B0%D0%B4%D1%83" title="Система орієнтації космічного приладу – Ukrainian" lang="uk" hreflang="uk" data-title="Система орієнтації космічного приладу" data-language-autonym="Українська" data-language-local-name="Ukrainian" class="interlanguage-link-target"><span>Українська</span></a></li> </ul> <div class="after-portlet after-portlet-lang"><span class="wb-langlinks-edit wb-langlinks-link"><a href="https://www.wikidata.org/wiki/Special:EntityPage/Q83001#sitelinks-wikipedia" title="Edit interlanguage links" class="wbc-editpage">Edit links</a></span></div> </div> </div> </div> </header> <div class="vector-page-toolbar"> <div class="vector-page-toolbar-container"> <div id="left-navigation"> <nav aria-label="Namespaces"> <div id="p-associated-pages" class="vector-menu vector-menu-tabs mw-portlet mw-portlet-associated-pages" > <div class="vector-menu-content"> <ul class="vector-menu-content-list"> <li id="ca-nstab-main" class="selected vector-tab-noicon mw-list-item"><a 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data-mw-deduplicate="TemplateStyles:r1236090951">.mw-parser-output .hatnote{font-style:italic}.mw-parser-output div.hatnote{padding-left:1.6em;margin-bottom:0.5em}.mw-parser-output .hatnote i{font-style:normal}.mw-parser-output .hatnote+link+.hatnote{margin-top:-0.5em}@media print{body.ns-0 .mw-parser-output .hatnote{display:none!important}}</style><div role="note" class="hatnote navigation-not-searchable">"Attitude control" redirects here. For the use in psychology, see <a href="/wiki/Attitude_change" title="Attitude change">Attitude change</a>. For attitude control of aircraft, see <a href="/wiki/Aircraft_flight_dynamics" title="Aircraft flight dynamics">Aircraft flight dynamics</a>.</div> <p class="mw-empty-elt"> </p><p><b>Spacecraft attitude control</b> is the process of controlling the orientation of a <a href="/wiki/Spacecraft" title="Spacecraft">spacecraft</a> (vehicle or satellite) with respect to an <a href="/wiki/Inertial_frame_of_reference" title="Inertial frame of reference">inertial frame of reference</a> or another entity such as the <a href="/wiki/Celestial_sphere" title="Celestial sphere">celestial sphere</a>, certain fields, and nearby objects, etc. </p><p>Controlling vehicle attitude requires <a href="/wiki/Actuators" class="mw-redirect" title="Actuators">actuators</a> to apply the torques needed to orient the vehicle to a desired attitude, and <a href="/wiki/Algorithms" class="mw-redirect" title="Algorithms">algorithms</a> to command the actuators based on the current attitude and specification of a desired attitude. </p><p>Before and during attitude control can be performed, <b>spacecraft attitude determination</b> must be performed, which requires <a href="/wiki/Sensor" title="Sensor">sensors</a> for absolute or relative measurement. </p><p>The broader integrated field that studies the combination of sensors, actuators and algorithms is called <i><a href="/wiki/Guidance,_navigation_and_control" class="mw-redirect" title="Guidance, navigation and control">guidance, navigation and control</a></i>, which also involves non-attitude concepts, such as <a href="/wiki/Position_determination" class="mw-redirect" title="Position determination">position determination</a> and <a href="/wiki/Navigation" title="Navigation">navigation</a>. </p> <meta property="mw:PageProp/toc" /> <div class="mw-heading mw-heading2"><h2 id="Overview">Overview</h2><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=1" title="Edit section: Overview"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>A spacecraft's attitude must typically be stabilized and controlled for a variety of reasons. It is often needed so that the spacecraft <a href="/wiki/High-gain_antenna" class="mw-redirect" title="High-gain antenna">high-gain antenna</a> may be accurately pointed to Earth for communications, so that onboard experiments may accomplish precise pointing for accurate collection and subsequent interpretation of data, so that the heating and cooling effects of sunlight and shadow may be used intelligently for thermal control, and also for guidance: short propulsive maneuvers must be executed in the right direction. </p> <div class="mw-heading mw-heading3"><h3 id="Types_of_stabilization">Types of stabilization</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=2" title="Edit section: Types of stabilization"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>Attitude control of spacecraft is maintained using one of two principal approaches: </p> <ul><li><b><style data-mw-deduplicate="TemplateStyles:r1238216509">.mw-parser-output .vanchor>:target~.vanchor-text{background-color:#b1d2ff}@media screen{html.skin-theme-clientpref-night .mw-parser-output .vanchor>:target~.vanchor-text{background-color:#0f4dc9}}@media screen and (prefers-color-scheme:dark){html.skin-theme-clientpref-os .mw-parser-output .vanchor>:target~.vanchor-text{background-color:#0f4dc9}}</style><span class="vanchor"><span id="Spin_stabilization"></span><span class="vanchor-text">Spin stabilization</span></span></b> <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1236090951"><div role="note" class="hatnote navigation-not-searchable">Main article: <a href="/wiki/Spin_stabilization" title="Spin stabilization">Spin stabilization</a></div> Spin stabilization is accomplished by setting the spacecraft spinning, using the gyroscopic action of the rotating spacecraft mass as the stabilizing mechanism. Propulsion system thrusters are fired only occasionally to make desired changes in spin rate, or in the spin-stabilized attitude. If desired, the spinning may be stopped through the use of thrusters or by <a href="/wiki/Yo-yo_de-spin" title="Yo-yo de-spin">yo-yo de-spin</a>. The <i><a href="/wiki/Pioneer_10" title="Pioneer 10">Pioneer 10</a></i> and <i><a href="/wiki/Pioneer_11" title="Pioneer 11">Pioneer 11</a></i> probes in the outer Solar System are examples of spin-stabilized spacecraft.<sup id="cite_ref-1" class="reference"><a href="#cite_note-1"><span class="cite-bracket">[</span>1<span class="cite-bracket">]</span></a></sup></li> <li><b><link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1238216509"><span class="vanchor"><span id="Three-axis_stabilization"></span><span class="vanchor-text">Three-axis stabilization</span></span></b> is an alternative method of spacecraft attitude control in which the spacecraft is held fixed in the desired orientation without any rotation. <ul><li>One method is to use small thrusters to continually nudge the spacecraft back and forth within a <a href="/wiki/Deadband" title="Deadband">deadband</a> of allowed attitude error. Thrusters may also be referred to as mass-expulsion control (MEC)<sup id="cite_ref-2" class="reference"><a href="#cite_note-2"><span class="cite-bracket">[</span>2<span class="cite-bracket">]</span></a></sup> systems, or <a href="/wiki/Reaction_control_system" title="Reaction control system">reaction control systems</a> (RCS). The space probes <i><a href="/wiki/Voyager_1" title="Voyager 1">Voyager 1</a></i> and <i><a href="/wiki/Voyager_2" title="Voyager 2">Voyager 2</a></i> employ this method, and have used up about three quarters<sup id="cite_ref-3" class="reference"><a href="#cite_note-3"><span class="cite-bracket">[</span>3<span class="cite-bracket">]</span></a></sup> of their 100 kg of propellant as of July 2015.</li> <li>Another method for achieving three-axis stabilization is to use electrically powered <a href="/wiki/Reaction_wheel" title="Reaction wheel">reaction wheels</a>, also called momentum wheels, which are mounted on three orthogonal axes aboard the spacecraft. They provide a means to trade <a href="/wiki/Angular_momentum" title="Angular momentum">angular momentum</a> back and forth between spacecraft and wheels. To rotate the vehicle on a given axis, the reaction wheel on that axis is accelerated in the opposite direction. To rotate the vehicle back, the wheel is slowed. Excess momentum that builds up in the system due to external torques from, for example, solar photon pressure or <a href="/wiki/Gravity_gradient" class="mw-redirect" title="Gravity gradient">gravity gradients</a>, must be occasionally removed from the system by applying controlled torque to the spacecraft to allowing the wheels to return to a desired speed under computer control. This is done during maneuvers called momentum desaturation or momentum unload maneuvers. Most spacecraft use a system of thrusters to apply the torque for desaturation maneuvers. A different approach was used by the <a href="/wiki/Hubble_Space_Telescope" title="Hubble Space Telescope">Hubble Space Telescope</a>, which had sensitive optics that could be contaminated by thruster exhaust, and instead used <a href="/wiki/Magnetic_torquers" class="mw-redirect" title="Magnetic torquers">magnetic torquers</a> for desaturation maneuvers.</li></ul></li></ul> <p>There are advantages and disadvantages to both spin stabilization and three-axis stabilization. Spin-stabilized craft provide a continuous sweeping motion that is desirable for fields and particles instruments, as well as some optical scanning instruments, but they may require complicated systems to de-spin antennas or optical instruments that must be pointed at targets for science observations or communications with Earth. Three-axis controlled craft can point optical instruments and antennas without having to de-spin them, but they may have to carry out special rotating maneuvers to best utilize their fields and particle instruments. If thrusters are used for routine stabilization, optical observations such as imaging must be designed knowing that the spacecraft is always slowly rocking back and forth, and not always exactly predictably. Reaction wheels provide a much steadier spacecraft from which to make observations, but they add mass to the spacecraft, they have a limited mechanical lifetime, and they require frequent momentum desaturation maneuvers, which can perturb navigation solutions because of accelerations imparted by the use of thrusters.<sup class="noprint Inline-Template Template-Fact" style="white-space:nowrap;">[<i><a href="/wiki/Wikipedia:Citation_needed" title="Wikipedia:Citation needed"><span title="This claim needs references to reliable sources. (January 2014)">citation needed</span></a></i>]</sup> </p> <div class="mw-heading mw-heading3"><h3 id="Articulation">Articulation</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=3" title="Edit section: Articulation"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>Many spacecraft have components that require articulation. <a href="/wiki/Voyager_program" title="Voyager program">Voyager</a> and <i><a href="/wiki/Galileo_(spacecraft)" title="Galileo (spacecraft)">Galileo</a></i>, for example, were designed with scan platforms for pointing optical instruments at their targets largely independently of spacecraft orientation. Many spacecraft, such as Mars orbiters, have solar panels that must track the Sun so they can provide electrical power to the spacecraft. <a href="/wiki/Cassini%E2%80%93Huygens" title="Cassini–Huygens"><i>Cassini</i><span class="nowrap" style="padding-left:0.1em;">'</span>s</a> main engine nozzles were steerable. Knowing where to point a solar panel, or scan platform, or a nozzle — that is, how to articulate it — requires knowledge of the spacecraft's attitude. Because a single subsystem keeps track of the spacecraft's attitude, the Sun's location, and Earth's location, it can compute the proper direction to point the appendages. It logically falls to the same subsystem – the Attitude and Articulation Control Subsystem (AACS), then, to manage both attitude and articulation. The name AACS may even be carried over to a spacecraft even if it has no appendages to articulate.<sup id="cite_ref-4" class="reference"><a href="#cite_note-4"><span class="cite-bracket">[</span>4<span class="cite-bracket">]</span></a></sup> </p> <div class="mw-heading mw-heading3"><h3 id="Geometry">Geometry</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=4" title="Edit section: Geometry"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1236090951"><div role="note" class="hatnote navigation-not-searchable">Main article: <a href="/wiki/Attitude_(geometry)" class="mw-redirect" title="Attitude (geometry)">Attitude (geometry)</a></div><p>Attitude is part of the description of how an object is placed in the <a href="/wiki/Euclidean_space" title="Euclidean space">space</a> it occupies. Attitude and position fully describe how an object is placed in space. (For some applications such as in robotics and computer vision, it is customary to combine position and attitude together into a single description known as <a href="/wiki/Pose_(computer_vision)" title="Pose (computer vision)">Pose</a>.) </p><p>Attitude can be described using a variety of methods; however, the most common are <a href="/wiki/Rotation_matrix" title="Rotation matrix">Rotation matrices</a>, <a href="/wiki/Quaternion" title="Quaternion">Quaternions</a>, and <a href="/wiki/Euler_angles" title="Euler angles">Euler angles</a>. While Euler angles are oftentimes the most straightforward representation to visualize, they can cause problems for highly-maneuverable systems because of a phenomenon known as <a href="/wiki/Gimbal_lock" title="Gimbal lock">Gimbal lock</a>. A rotation matrix, on the other hand, provides a full description of the attitude at the expense of requiring nine values instead of three. The use of a rotation matrix can lead to increased computational expense and they can be more difficult to work with. Quaternions offer a decent compromise in that they do not suffer from gimbal lock and only require four values to fully describe the attitude. </p> <figure class="mw-default-size" typeof="mw:File/Thumb"><a href="/wiki/File:Change_of_axes.svg" class="mw-file-description"><img src="//upload.wikimedia.org/wikipedia/commons/thumb/c/c2/Change_of_axes.svg/220px-Change_of_axes.svg.png" decoding="async" width="220" height="220" class="mw-file-element" srcset="//upload.wikimedia.org/wikipedia/commons/thumb/c/c2/Change_of_axes.svg/330px-Change_of_axes.svg.png 1.5x, //upload.wikimedia.org/wikipedia/commons/thumb/c/c2/Change_of_axes.svg/440px-Change_of_axes.svg.png 2x" data-file-width="512" data-file-height="512" /></a><figcaption>Changing orientation of a <a href="/wiki/Rigid_body" title="Rigid body">rigid body</a> is the same as <a href="/wiki/Rotation_(mathematics)" title="Rotation (mathematics)">rotating</a> the axes of a <a href="/wiki/Frame_of_reference" title="Frame of reference">reference frame</a> attached to it.</figcaption></figure> <div class="mw-heading mw-heading2"><h2 id="Actuators">Actuators</h2><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=5" title="Edit section: Actuators"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>Attitude control can be obtained by several mechanisms, including: </p> <div class="mw-heading mw-heading3"><h3 id="Thrusters">Thrusters</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=6" title="Edit section: Thrusters"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1236090951"><div role="note" class="hatnote navigation-not-searchable">Main article: <a href="/wiki/Reaction_control_system" title="Reaction control system">Reaction control system</a></div> <p><a href="/wiki/Vernier_thruster" title="Vernier thruster">Vernier thrusters</a> are the most common actuators, as they may be used for station keeping as well. Thrusters must be organized as a system to provide stabilization about all three axes, and at least two thrusters are generally used in each axis to provide torque as a <a href="/wiki/Couple_(mechanics)" title="Couple (mechanics)">couple</a> in order to prevent imparting a <a href="/wiki/Translation_(geometry)" title="Translation (geometry)">translation</a> to the vehicle. Their limitations are fuel usage, engine wear, and cycles of the control valves. The fuel efficiency of an attitude control system is determined by its <a href="/wiki/Specific_impulse" title="Specific impulse">specific impulse</a> (proportional to exhaust velocity) and the smallest torque impulse it can provide (which determines how often the thrusters must fire to provide precise control). Thrusters must be fired in one direction to start rotation, and again in the opposing direction if a new orientation is to be held. Thruster systems have been used on most crewed space vehicles, including <a href="/wiki/Vostok_(spacecraft)" title="Vostok (spacecraft)">Vostok</a>, <a href="/wiki/Project_Mercury" title="Project Mercury">Mercury</a>, <a href="/wiki/Project_Gemini" title="Project Gemini">Gemini</a>, <a href="/wiki/Apollo_(spacecraft)" title="Apollo (spacecraft)">Apollo</a>, <a href="/wiki/Soyuz_(spacecraft)" title="Soyuz (spacecraft)">Soyuz</a>, and the <a href="/wiki/Space_Shuttle" title="Space Shuttle">Space Shuttle</a>. </p><p>To minimize the fuel limitation on mission duration, auxiliary attitude control systems may be used to reduce vehicle rotation to lower levels, such as small <a href="/wiki/Ion_thruster" title="Ion thruster">ion thrusters</a> that accelerate ionized gases electrically to extreme velocities, using power from solar cells. </p> <div class="mw-heading mw-heading3"><h3 id="Reaction/momentum_wheels"><span id="Reaction.2Fmomentum_wheels"></span>Reaction/momentum wheels</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=7" title="Edit section: Reaction/momentum wheels"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1236090951"><div role="note" class="hatnote navigation-not-searchable">Main article: <a href="/wiki/Momentum_wheel" class="mw-redirect" title="Momentum wheel">Momentum wheel</a></div> <p>Momentum wheels are <a href="/wiki/Electric_motor" title="Electric motor">electric motor</a> driven rotors made to spin in the direction opposite to that required to re-orient the vehicle. Because momentum wheels make up a small fraction of the spacecraft's mass and are computer controlled, they give precise control. Momentum wheels are generally suspended on <a href="/wiki/Magnetic_bearing" title="Magnetic bearing">magnetic bearings</a> to avoid bearing friction and breakdown problems.<sup id="cite_ref-5" class="reference"><a href="#cite_note-5"><span class="cite-bracket">[</span>5<span class="cite-bracket">]</span></a></sup> Spacecraft <a href="/wiki/Reaction_wheel" title="Reaction wheel">Reaction wheels</a> often use mechanical ball bearings. </p><p>To maintain orientation in three dimensional space a minimum of three reaction wheels must be used,<sup id="cite_ref-6" class="reference"><a href="#cite_note-6"><span class="cite-bracket">[</span>6<span class="cite-bracket">]</span></a></sup> with additional units providing single failure protection. See <a href="/wiki/Euler_angles" title="Euler angles">Euler angles</a>. </p> <div class="mw-heading mw-heading3"><h3 id="Control_moment_gyros">Control moment gyros</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=8" title="Edit section: Control moment gyros"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1236090951"><div role="note" class="hatnote navigation-not-searchable">Main article: <a href="/wiki/Control_moment_gyroscope" title="Control moment gyroscope">Control moment gyroscope</a></div> <p>These are rotors spun at constant speed, mounted on <a href="/wiki/Gimbal" title="Gimbal">gimbals</a> to provide attitude control. Although a CMG provides control about the two axes orthogonal to the gyro spin axis, triaxial control still requires two units. A CMG is a bit more expensive in terms of cost and mass, because gimbals and their drive motors must be provided. The maximum torque (but not the maximum angular momentum change) exerted by a CMG is greater than for a momentum wheel, making it better suited to large spacecraft. A major drawback is the additional complexity, which increases the number of failure points. For this reason, the <a href="/wiki/International_Space_Station" title="International Space Station">International Space Station</a> uses a set of four CMGs to provide dual failure tolerance. </p> <div class="mw-heading mw-heading3"><h3 id="Solar_sails">Solar sails</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=9" title="Edit section: Solar sails"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1236090951"><div role="note" class="hatnote navigation-not-searchable">Main article: <a href="/wiki/Solar_sail" title="Solar sail">Solar sail</a></div> <p>Small solar sails (devices that produce thrust as a reaction force induced by reflecting incident light) may be used to make small attitude control and velocity adjustments. This application can save large amounts of fuel on a long-duration mission by producing control moments without fuel expenditure. For example, <i><a href="/wiki/Mariner_10" title="Mariner 10">Mariner 10</a></i> adjusted its attitude using its solar cells and antennas as small solar sails. </p> <div class="mw-heading mw-heading3"><h3 id="Gravity-gradient_stabilization">Gravity-gradient stabilization</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=10" title="Edit section: Gravity-gradient stabilization"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1236090951"><div role="note" class="hatnote navigation-not-searchable">Main article: <a href="/wiki/Gravity-gradient_stabilization" title="Gravity-gradient stabilization">Gravity-gradient stabilization</a></div> <p>In orbit, a spacecraft with one axis much longer than the other two will spontaneously orient so that its long axis points at the planet's center of mass. This system has the virtue of needing no active control system or expenditure of fuel. The effect is caused by a <a href="/wiki/Tidal_force" title="Tidal force">tidal force</a>. The upper end of the vehicle feels less gravitational pull than the lower end. This provides a restoring torque whenever the long axis is not co-linear with the direction of gravity. Unless some means of damping is provided, the spacecraft will oscillate about the local vertical. Sometimes <a href="/wiki/Tether_propulsion" class="mw-redirect" title="Tether propulsion">tethers</a> are used to connect two parts of a satellite, to increase the stabilizing torque. A problem with such tethers is that meteoroids as small as a grain of sand can part them. </p> <div class="mw-heading mw-heading3"><h3 id="Magnetic_torquers">Magnetic torquers</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=11" title="Edit section: Magnetic torquers"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1236090951"><div role="note" class="hatnote navigation-not-searchable">Main article: <a href="/wiki/Magnetic_torquers" class="mw-redirect" title="Magnetic torquers">Magnetic torquers</a></div> <p><a href="/wiki/Electromagnetic_coil" title="Electromagnetic coil">Coils</a> or (on very small satellites) <a href="/wiki/Permanent_magnets" class="mw-redirect" title="Permanent magnets">permanent magnets</a> exert a moment against the local magnetic field. This method works only where there is a magnetic field against which to react. One classic field "coil" is actually in the form of a <a href="/wiki/Electrodynamic_tether" title="Electrodynamic tether">conductive tether</a> in a planetary magnetic field. Such a conductive tether can also generate electrical power, at the expense of <a href="/wiki/Orbital_decay" title="Orbital decay">orbital decay</a>. Conversely, by inducing a counter-current, using solar cell power, the orbit may be raised. Due to massive variability in Earth's magnetic field from an ideal radial field, control laws based on torques coupling to this field will be highly non-linear. Moreover, only two-axis control is available at any given time meaning that a vehicle reorient may be necessary to null all rates. </p> <div class="mw-heading mw-heading3"><h3 id="Passive_attitude_control">Passive attitude control</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=12" title="Edit section: Passive attitude control"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>Three main types of passive attitude control exist for satellites. The first one uses gravity gradient, and it leads to four stable states with the long axis (axis with smallest moment of inertia) pointing towards Earth. As this system has four stable states, if the satellite has a preferred orientation, e.g. a camera pointed at the planet, some way to flip the satellite and its tether end-for-end is needed. </p><p>The second passive system orients the satellite along Earth's magnetic field thanks to a magnet.<sup id="cite_ref-7" class="reference"><a href="#cite_note-7"><span class="cite-bracket">[</span>7<span class="cite-bracket">]</span></a></sup> These purely passive attitude control systems have limited pointing accuracy, because the spacecraft will oscillate around energy minima. This drawback is overcome by adding damper, which can be hysteretic materials or a viscous damper. The viscous damper is a small can or tank of fluid mounted in the spacecraft, possibly with internal baffles to increase internal friction. Friction within the damper will gradually convert oscillation energy into heat dissipated within the viscous damper. </p><p>A third form of passive attitude control is aerodynamic stabilization. This is achieved using a drag gradient, as demonstrated on the <a href="/wiki/GASPACS" title="GASPACS">Get Away Special Passive Attitude Control Satellite (GASPACS)</a> technology demonstration. In low Earth orbit, the force due to drag is many orders of magnitude more dominant than the force imparted due to gravity gradients.<sup id="cite_ref-8" class="reference"><a href="#cite_note-8"><span class="cite-bracket">[</span>8<span class="cite-bracket">]</span></a></sup> When a satellite is utilizing aerodynamic passive attitude control, air molecules from the Earth's upper atmosphere strike the satellite in such a way that the center of pressure remains behind the center of mass, similar to how the feathers on an arrow stabilize the arrow. GASPACS utilized a 1 m inflatable 'AeroBoom', which extended behind the satellite, creating a stabilizing torque along the satellite's velocity vector.<sup id="cite_ref-9" class="reference"><a href="#cite_note-9"><span class="cite-bracket">[</span>9<span class="cite-bracket">]</span></a></sup> </p> <div class="mw-heading mw-heading2"><h2 id="Algorithms">Algorithms</h2><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=13" title="Edit section: Algorithms"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p><a href="/wiki/Algorithms" class="mw-redirect" title="Algorithms">Control algorithms</a> are <a href="/wiki/Computer_program" title="Computer program">computer programs</a> that receive data from vehicle sensors and derive the appropriate commands to the actuators to rotate the vehicle to the desired attitude. The algorithms range from very simple, e.g. <a href="/wiki/Proportional_control" title="Proportional control">proportional control</a>, to complex nonlinear estimators or many in-between types, depending on mission requirements. Typically, the attitude control algorithms are part of the software running on the computer hardware, which receives commands from the ground and formats vehicle data <a href="/wiki/Telemetry" title="Telemetry">telemetry</a> for transmission to a ground station. </p><p>The attitude control algorithms are written and implemented based on requirement for a particular attitude maneuver. Asides the implementation of passive attitude control such as the <a href="/wiki/Gravity-gradient_stabilization" title="Gravity-gradient stabilization">gravity-gradient stabilization</a>, most spacecraft make use of active control which exhibits a typical attitude control loop. The design of the control algorithm depends on the actuator to be used for the specific attitude maneuver although using a simple <a href="/wiki/PID_controller" class="mw-redirect" title="PID controller"><i>proportional–integral–derivative controller</i> (<i>PID controller</i>)</a> satisfies most control needs. </p><p>The appropriate commands to the actuators are obtained based on error signals described as the difference between the measured and desired attitude. The error signals are commonly measured as <a href="/wiki/Euler_angles" title="Euler angles">euler angles</a> (Φ, θ, Ψ), however an alternative to this could be described in terms of <a href="/wiki/Direction_cosine" title="Direction cosine">direction cosine</a> matrix or error <a href="/wiki/Quaternion" title="Quaternion">quaternions</a>. The PID controller which is most common reacts to an error signal (deviation) based on attitude as follows </p> <dl><dd><span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle T_{c}(t)=K_{\text{p}}e(t)+K_{\text{i}}\int _{0}^{t}e(\tau )\,d\tau +K_{\text{d}}{\dot {e}}(t),}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <msub> <mi>T</mi> <mrow class="MJX-TeXAtom-ORD"> <mi>c</mi> </mrow> </msub> <mo stretchy="false">(</mo> <mi>t</mi> <mo stretchy="false">)</mo> <mo>=</mo> <msub> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mtext>p</mtext> </mrow> </msub> <mi>e</mi> <mo stretchy="false">(</mo> <mi>t</mi> <mo stretchy="false">)</mo> <mo>+</mo> <msub> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mtext>i</mtext> </mrow> </msub> <msubsup> <mo>∫</mo> <mrow class="MJX-TeXAtom-ORD"> <mn>0</mn> </mrow> <mrow class="MJX-TeXAtom-ORD"> <mi>t</mi> </mrow> </msubsup> <mi>e</mi> <mo stretchy="false">(</mo> <mi>τ</mi> <mo stretchy="false">)</mo> <mspace width="thinmathspace" /> <mi>d</mi> <mi>τ</mi> <mo>+</mo> <msub> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mtext>d</mtext> </mrow> </msub> <mrow class="MJX-TeXAtom-ORD"> <mrow class="MJX-TeXAtom-ORD"> <mover> <mi>e</mi> <mo>˙</mo> </mover> </mrow> </mrow> <mo stretchy="false">(</mo> <mi>t</mi> <mo stretchy="false">)</mo> <mo>,</mo> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle T_{c}(t)=K_{\text{p}}e(t)+K_{\text{i}}\int _{0}^{t}e(\tau )\,d\tau +K_{\text{d}}{\dot {e}}(t),}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/92e28b4eda485aed65041f4b0d6df8a709c401d9" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -2.338ex; width:41.915ex; height:6.176ex;" alt="{\displaystyle T_{c}(t)=K_{\text{p}}e(t)+K_{\text{i}}\int _{0}^{t}e(\tau )\,d\tau +K_{\text{d}}{\dot {e}}(t),}"></span></dd></dl> <p>where <span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle T_{c}}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <msub> <mi>T</mi> <mrow class="MJX-TeXAtom-ORD"> <mi>c</mi> </mrow> </msub> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle T_{c}}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/66261e3cbed8035b2bf7a9ccb878c786cf7556c6" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.671ex; width:2.302ex; height:2.509ex;" alt="{\displaystyle T_{c}}"></span> is the control torque, <span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle e}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mi>e</mi> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle e}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/cd253103f0876afc68ebead27a5aa9867d927467" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.338ex; width:1.083ex; height:1.676ex;" alt="{\displaystyle e}"></span> is the attitude deviation signal, and <span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle K_{\text{p}},K_{\text{i}},K_{\text{d}}}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <msub> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mtext>p</mtext> </mrow> </msub> <mo>,</mo> <msub> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mtext>i</mtext> </mrow> </msub> <mo>,</mo> <msub> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mtext>d</mtext> </mrow> </msub> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle K_{\text{p}},K_{\text{i}},K_{\text{d}}}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/f87ffd3d613436dfc9a61bdfbdf9a1c9fcc99250" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -1.005ex; width:10.969ex; height:2.843ex;" alt="{\displaystyle K_{\text{p}},K_{\text{i}},K_{\text{d}}}"></span> are the PID controller parameters. </p><p>A simple implementation of this can be the application of the proportional control for <a href="/wiki/Nadir" title="Nadir">nadir pointing</a> making use of either momentum or reaction wheels as actuators. Based on the change in momentum of the wheels, the control law can be defined in 3-axes x, y, z as </p> <dl><dd><span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle T_{c}x=-K_{\text{q1}}q_{1}+K_{\text{w1}}{w_{x}},}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <msub> <mi>T</mi> <mrow class="MJX-TeXAtom-ORD"> <mi>c</mi> </mrow> </msub> <mi>x</mi> <mo>=</mo> <mo>−</mo> <msub> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mtext>q1</mtext> </mrow> </msub> <msub> <mi>q</mi> <mrow class="MJX-TeXAtom-ORD"> <mn>1</mn> </mrow> </msub> <mo>+</mo> <msub> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mtext>w1</mtext> </mrow> </msub> <mrow class="MJX-TeXAtom-ORD"> <msub> <mi>w</mi> <mrow class="MJX-TeXAtom-ORD"> <mi>x</mi> </mrow> </msub> </mrow> <mo>,</mo> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle T_{c}x=-K_{\text{q1}}q_{1}+K_{\text{w1}}{w_{x}},}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/8912770be9f3ab32b3a97948871bef1d1eaa64b8" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -1.005ex; width:25.062ex; height:2.843ex;" alt="{\displaystyle T_{c}x=-K_{\text{q1}}q_{1}+K_{\text{w1}}{w_{x}},}"></span></dd></dl> <dl><dd><span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle T_{c}y=-K_{\text{q2}}q_{2}+K_{\text{w2}}{w_{y}},}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <msub> <mi>T</mi> <mrow class="MJX-TeXAtom-ORD"> <mi>c</mi> </mrow> </msub> <mi>y</mi> <mo>=</mo> <mo>−</mo> <msub> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mtext>q2</mtext> </mrow> </msub> <msub> <mi>q</mi> <mrow class="MJX-TeXAtom-ORD"> <mn>2</mn> </mrow> </msub> <mo>+</mo> <msub> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mtext>w2</mtext> </mrow> </msub> <mrow class="MJX-TeXAtom-ORD"> <msub> <mi>w</mi> <mrow class="MJX-TeXAtom-ORD"> <mi>y</mi> </mrow> </msub> </mrow> <mo>,</mo> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle T_{c}y=-K_{\text{q2}}q_{2}+K_{\text{w2}}{w_{y}},}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/757ee7a7bfea60f87aa7c5656b5c752c674f3f13" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -1.005ex; width:24.765ex; height:2.843ex;" alt="{\displaystyle T_{c}y=-K_{\text{q2}}q_{2}+K_{\text{w2}}{w_{y}},}"></span></dd></dl> <dl><dd><span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle T_{c}z=-K_{\text{q3}}q_{3}+K_{\text{w3}}{w_{z}},}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <msub> <mi>T</mi> <mrow class="MJX-TeXAtom-ORD"> <mi>c</mi> </mrow> </msub> <mi>z</mi> <mo>=</mo> <mo>−</mo> <msub> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mtext>q3</mtext> </mrow> </msub> <msub> <mi>q</mi> <mrow class="MJX-TeXAtom-ORD"> <mn>3</mn> </mrow> </msub> <mo>+</mo> <msub> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mtext>w3</mtext> </mrow> </msub> <mrow class="MJX-TeXAtom-ORD"> <msub> <mi>w</mi> <mrow class="MJX-TeXAtom-ORD"> <mi>z</mi> </mrow> </msub> </mrow> <mo>,</mo> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle T_{c}z=-K_{\text{q3}}q_{3}+K_{\text{w3}}{w_{z}},}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/19c2c2d4353ad5fb4e680ab2b42bf491131e81e0" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -1.005ex; width:24.65ex; height:2.843ex;" alt="{\displaystyle T_{c}z=-K_{\text{q3}}q_{3}+K_{\text{w3}}{w_{z}},}"></span></dd></dl> <p>This control algorithm also affects momentum dumping. </p><p>Another important and common control algorithm involves the concept of detumbling, which is attenuating the angular momentum of the spacecraft. The need to detumble the spacecraft arises from the uncontrollable state after release from the launch vehicle. Most spacecraft in <a href="/wiki/Low_Earth_orbit" title="Low Earth orbit">low Earth orbit</a> (LEO) makes use of magnetic detumbling concept which utilizes the effect of the <a href="/wiki/Earth%27s_magnetic_field" title="Earth's magnetic field">Earth's magnetic field</a>. The control algorithm is called the B-Dot controller and relies on <a href="/wiki/Magnetic_torquer" class="mw-redirect" title="Magnetic torquer">magnetic coils</a> or torque rods as control actuators. The control law is based on the measurement of the rate of change of body-fixed <a href="/wiki/Magnetometer" title="Magnetometer">magnetometer</a> signals. </p> <dl><dd><span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle m=-K{\dot {B}}}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mi>m</mi> <mo>=</mo> <mo>−</mo> <mi>K</mi> <mrow class="MJX-TeXAtom-ORD"> <mrow class="MJX-TeXAtom-ORD"> <mover> <mi>B</mi> <mo>˙</mo> </mover> </mrow> </mrow> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle m=-K{\dot {B}}}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/51f5e1d5b86a48e96f43f14ab21fe410bcf5efda" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.505ex; width:10.777ex; height:2.843ex;" alt="{\displaystyle m=-K{\dot {B}}}"></span></dd></dl> <p>where <span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle m}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mi>m</mi> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle m}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/0a07d98bb302f3856cbabc47b2b9016692e3f7bc" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.338ex; width:2.04ex; height:1.676ex;" alt="{\displaystyle m}"></span> is the commanded magnetic dipole moment of the magnetic torquer and <span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle K}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mi>K</mi> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle K}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/2b76fce82a62ed5461908f0dc8f037de4e3686b0" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.338ex; width:2.066ex; height:2.176ex;" alt="{\displaystyle K}"></span> is the proportional gain and <span class="mwe-math-element"><span class="mwe-math-mathml-inline mwe-math-mathml-a11y" style="display: none;"><math xmlns="http://www.w3.org/1998/Math/MathML" alttext="{\displaystyle {\dot {B}}}"> <semantics> <mrow class="MJX-TeXAtom-ORD"> <mstyle displaystyle="true" scriptlevel="0"> <mrow class="MJX-TeXAtom-ORD"> <mrow class="MJX-TeXAtom-ORD"> <mover> <mi>B</mi> <mo>˙</mo> </mover> </mrow> </mrow> </mstyle> </mrow> <annotation encoding="application/x-tex">{\displaystyle {\dot {B}}}</annotation> </semantics> </math></span><img src="https://wikimedia.org/api/rest_v1/media/math/render/svg/1a94a9216e179facec1a5e8c318383edceb8b520" class="mwe-math-fallback-image-inline mw-invert skin-invert" aria-hidden="true" style="vertical-align: -0.338ex; width:1.764ex; height:2.676ex;" alt="{\displaystyle {\dot {B}}}"></span> is the rate of change of the Earth's magnetic field. </p> <div class="mw-heading mw-heading2"><h2 id="Attitude_determination">Attitude determination</h2><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=14" title="Edit section: Attitude determination"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <style data-mw-deduplicate="TemplateStyles:r1251242444">.mw-parser-output .ambox{border:1px solid #a2a9b1;border-left:10px solid #36c;background-color:#fbfbfb;box-sizing:border-box}.mw-parser-output .ambox+link+.ambox,.mw-parser-output .ambox+link+style+.ambox,.mw-parser-output .ambox+link+link+.ambox,.mw-parser-output .ambox+.mw-empty-elt+link+.ambox,.mw-parser-output .ambox+.mw-empty-elt+link+style+.ambox,.mw-parser-output .ambox+.mw-empty-elt+link+link+.ambox{margin-top:-1px}html body.mediawiki .mw-parser-output .ambox.mbox-small-left{margin:4px 1em 4px 0;overflow:hidden;width:238px;border-collapse:collapse;font-size:88%;line-height:1.25em}.mw-parser-output .ambox-speedy{border-left:10px solid #b32424;background-color:#fee7e6}.mw-parser-output .ambox-delete{border-left:10px solid #b32424}.mw-parser-output .ambox-content{border-left:10px solid #f28500}.mw-parser-output .ambox-style{border-left:10px solid #fc3}.mw-parser-output .ambox-move{border-left:10px solid #9932cc}.mw-parser-output .ambox-protection{border-left:10px solid #a2a9b1}.mw-parser-output .ambox .mbox-text{border:none;padding:0.25em 0.5em;width:100%}.mw-parser-output .ambox .mbox-image{border:none;padding:2px 0 2px 0.5em;text-align:center}.mw-parser-output .ambox .mbox-imageright{border:none;padding:2px 0.5em 2px 0;text-align:center}.mw-parser-output .ambox .mbox-empty-cell{border:none;padding:0;width:1px}.mw-parser-output .ambox .mbox-image-div{width:52px}@media(min-width:720px){.mw-parser-output .ambox{margin:0 10%}}@media print{body.ns-0 .mw-parser-output .ambox{display:none!important}}</style><table class="plainlinks metadata ambox ambox-move" role="presentation"><tbody><tr><td class="mbox-image"><div class="mbox-image-div"><span typeof="mw:File"><span><img alt="" src="//upload.wikimedia.org/wikipedia/commons/thumb/a/a7/Split-arrows.svg/50px-Split-arrows.svg.png" decoding="async" width="50" height="17" class="mw-file-element" srcset="//upload.wikimedia.org/wikipedia/commons/thumb/a/a7/Split-arrows.svg/75px-Split-arrows.svg.png 1.5x, //upload.wikimedia.org/wikipedia/commons/thumb/a/a7/Split-arrows.svg/100px-Split-arrows.svg.png 2x" data-file-width="60" data-file-height="20" /></span></span></div></td><td class="mbox-text"><div class="mbox-text-span">It has been suggested that this section be <a href="/wiki/Wikipedia:Splitting" title="Wikipedia:Splitting">split</a> out into another article titled <i><a class="mw-selflink selflink">Spacecraft attitude control</a></i>. (<a href="/wiki/Talk:Spacecraft_attitude_control#Split_Attitude_determination" title="Talk:Spacecraft attitude control">Discuss</a>) <small><i>(November 2024)</i></small></div></td></tr></tbody></table> <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1236090951"><div role="note" class="hatnote navigation-not-searchable">"Attitude determination" redirects here. Not to be confused with <a href="/wiki/Direction_determination" title="Direction determination">Direction determination</a>.</div> <p><i>Spacecraft attitude determination</i> is the process of determining the <a href="/wiki/Attitude_(geometry)" class="mw-redirect" title="Attitude (geometry)">orientation</a> of a <a href="/wiki/Spacecraft" title="Spacecraft">spacecraft</a> (vehicle or satellite). It is a pre-requisite for spacecraft attitude control. A variety of sensors are utilized for relative and absolute attitude determination. </p> <div class="mw-heading mw-heading3"><h3 id="Sensors">Sensors</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=15" title="Edit section: Sensors"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <div class="mw-heading mw-heading4"><h4 id="Relative_attitude_sensors">Relative attitude sensors</h4><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=16" title="Edit section: Relative attitude sensors"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>Many sensors generate outputs that reflect the rate of change in attitude. These require a known initial attitude, or external information to use them to determine attitude. Many of this class of sensor have some noise, leading to inaccuracies if not corrected by absolute attitude sensors. </p> <div class="mw-heading mw-heading5"><h5 id="Gyroscopes">Gyroscopes</h5><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=17" title="Edit section: Gyroscopes"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p><a href="/wiki/Gyroscope" title="Gyroscope">Gyroscopes</a> are devices that sense rotation in <a href="/wiki/Three-dimensional_space" title="Three-dimensional space">three-dimensional space</a> without reliance on the observation of external objects. Classically, a gyroscope consists of a spinning mass, but there are also "<a href="/wiki/Laser_ring_gyroscope" class="mw-redirect" title="Laser ring gyroscope">ring laser gyros</a>" utilizing coherent light reflected around a closed path. Another type of "gyro" is a <a href="/wiki/Hemispherical_resonator_gyroscope" title="Hemispherical resonator gyroscope">hemispherical resonator gyro</a> where a crystal cup shaped like a wine glass can be driven into oscillation just as a wine glass "sings" as a finger is rubbed around its rim. The orientation of the oscillation is fixed in inertial space, so measuring the orientation of the oscillation relative to the spacecraft can be used to sense the motion of the spacecraft with respect to inertial space.<sup id="cite_ref-10" class="reference"><a href="#cite_note-10"><span class="cite-bracket">[</span>10<span class="cite-bracket">]</span></a></sup> </p> <div class="mw-heading mw-heading5"><h5 id="Motion_reference_units">Motion reference units</h5><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=18" title="Edit section: Motion reference units"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>Motion reference units are a kind of <a href="/wiki/Inertial_measurement_unit" title="Inertial measurement unit">inertial measurement unit</a> with single- or multi-axis motion sensors. They utilize <a href="/wiki/Vibrating_structure_gyroscope#MEMS_Gyroscopes" title="Vibrating structure gyroscope">MEMS gyroscopes</a>. Some multi-axis MRUs are capable of measuring <a href="/wiki/Six_degrees_of_freedom" title="Six degrees of freedom">roll, pitch, yaw and heave</a>. They have applications outside the aeronautical field, such as:<sup id="cite_ref-11" class="reference"><a href="#cite_note-11"><span class="cite-bracket">[</span>11<span class="cite-bracket">]</span></a></sup> </p> <ul><li><a href="/wiki/Antenna_(radio)" title="Antenna (radio)">Antenna</a> motion compensation and stabilization</li> <li><a href="/wiki/Dynamic_positioning" title="Dynamic positioning">Dynamic positioning</a></li> <li><a href="/wiki/Active_heave_compensation" title="Active heave compensation">Heave compensation</a> of offshore cranes</li> <li>High speed craft motion control and damping systems</li> <li>Hydro acoustic positioning</li> <li>Motion compensation of single and <a href="/wiki/Multibeam_echosounder" title="Multibeam echosounder">multibeam echosounders</a></li> <li>Ocean wave measurements</li> <li>Offshore structure motion monitoring</li> <li>Orientation and attitude measurements on <a href="/wiki/Autonomous_underwater_vehicle" title="Autonomous underwater vehicle">Autonomous underwater vehicles</a> and <a href="/wiki/Remotely_operated_underwater_vehicle" title="Remotely operated underwater vehicle">Remotely operated underwater vehicles</a></li> <li>Ship motion monitoring</li></ul> <div class="mw-heading mw-heading4"><h4 id="Absolute_attitude_sensors">Absolute attitude sensors</h4><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=19" title="Edit section: Absolute attitude sensors"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>This class of sensors sense the position or orientation of fields, objects or other phenomena outside the spacecraft. </p> <div class="mw-heading mw-heading5"><h5 id="Horizon_sensor">Horizon sensor</h5><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=20" title="Edit section: Horizon sensor"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>A <i>horizon sensor</i> is an optical instrument that detects light from the 'limb' of Earth's atmosphere, i.e., at the horizon. <a href="/wiki/Infrared#Heat" title="Infrared">Thermal infrared</a> sensing is often used, which senses the comparative warmth of the atmosphere, compared to the much colder <a href="/wiki/Cosmic_microwave_background_radiation" class="mw-redirect" title="Cosmic microwave background radiation">cosmic background</a>. This sensor provides orientation with respect to Earth about two orthogonal axes. It tends to be less precise than sensors based on stellar observation. Sometimes referred to as an Earth sensor.<sup id="cite_ref-horizonsensor_12-0" class="reference"><a href="#cite_note-horizonsensor-12"><span class="cite-bracket">[</span>12<span class="cite-bracket">]</span></a></sup> </p> <div class="mw-heading mw-heading5"><h5 id="Orbital_gyrocompass">Orbital gyrocompass</h5><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=21" title="Edit section: Orbital gyrocompass"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>Similar to the way that a terrestrial <a href="/wiki/Gyrocompass" title="Gyrocompass">gyrocompass</a> uses a <a href="/wiki/Pendulum" title="Pendulum">pendulum</a> to sense local gravity and force its gyro into alignment with Earth's spin vector, and therefore point north, an <i>orbital gyrocompass</i> uses a horizon sensor to sense the direction to Earth's center, and a gyro to sense rotation about an axis normal to the orbit plane. Thus, the horizon sensor provides pitch and roll measurements, and the gyro provides yaw.<sup id="cite_ref-13" class="reference"><a href="#cite_note-13"><span class="cite-bracket">[</span>13<span class="cite-bracket">]</span></a></sup> See <a href="/wiki/Tait-Bryan_angles" class="mw-redirect" title="Tait-Bryan angles">Tait-Bryan angles</a>. </p> <div class="mw-heading mw-heading5"><h5 id="Sun_sensor">Sun sensor</h5><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=22" title="Edit section: Sun sensor"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>A <i><a href="/wiki/Sun_sensor" title="Sun sensor">Sun sensor</a></i> is a device that senses the direction to the <a href="/wiki/Sun" title="Sun">Sun</a>. This can be as simple as some <a href="/wiki/Solar_cell" title="Solar cell">solar cells</a> and shades, or as complex as a steerable <a href="/wiki/Telescope" title="Telescope">telescope</a>, depending on mission requirements. </p> <div class="mw-heading mw-heading5"><h5 id="Earth_sensor">Earth sensor</h5><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=23" title="Edit section: Earth sensor"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>An <i>Earth sensor</i> is a device that senses the direction to <a href="/wiki/Earth" title="Earth">Earth</a>. It is usually an <a href="/wiki/Infrared_camera" class="mw-redirect" title="Infrared camera">infrared camera</a>; nowadays the main method to detect attitude is the <a href="/wiki/Star_tracker" title="Star tracker">star tracker</a>, but Earth sensors are still integrated in satellites for their low cost and reliability.<sup id="cite_ref-horizonsensor_12-1" class="reference"><a href="#cite_note-horizonsensor-12"><span class="cite-bracket">[</span>12<span class="cite-bracket">]</span></a></sup> </p> <div class="mw-heading mw-heading5"><h5 id="Star_tracker">Star tracker</h5><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=24" title="Edit section: Star tracker"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <figure class="mw-default-size" typeof="mw:File/Thumb"><a href="/wiki/File:STARS_on_EBEX_ld2012_image.png" class="mw-file-description"><img src="//upload.wikimedia.org/wikipedia/commons/thumb/0/01/STARS_on_EBEX_ld2012_image.png/220px-STARS_on_EBEX_ld2012_image.png" decoding="async" width="220" height="174" class="mw-file-element" srcset="//upload.wikimedia.org/wikipedia/commons/thumb/0/01/STARS_on_EBEX_ld2012_image.png/330px-STARS_on_EBEX_ld2012_image.png 1.5x, //upload.wikimedia.org/wikipedia/commons/thumb/0/01/STARS_on_EBEX_ld2012_image.png/440px-STARS_on_EBEX_ld2012_image.png 2x" data-file-width="802" data-file-height="633" /></a><figcaption>The STARS real-time star tracking software operates on an image from <a href="/wiki/The_E_and_B_Experiment" title="The E and B Experiment">EBEX</a> 2012, a high-altitude balloon-borne cosmology experiment launched from Antarctica on 2012-12-29</figcaption></figure> <p>A <i><a href="/wiki/Star_tracker" title="Star tracker">star tracker</a></i> is an optical device that measures the position(s) of <a href="/wiki/Star" title="Star">star</a>(s) using <a href="/wiki/Photocell" class="mw-redirect" title="Photocell">photocell</a>(s) or a camera.<sup id="cite_ref-14" class="reference"><a href="#cite_note-14"><span class="cite-bracket">[</span>14<span class="cite-bracket">]</span></a></sup> It uses magnitude of brightness and spectral type to identify and then calculate the relative position of stars around it. </p> <div class="mw-heading mw-heading5"><h5 id="Magnetometer">Magnetometer</h5><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=25" title="Edit section: Magnetometer"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>A <i><a href="/wiki/Magnetometer" title="Magnetometer">magnetometer</a></i> is a device that senses <a href="/wiki/Magnetic_field" title="Magnetic field">magnetic field</a> strength and, when used in a three-axis triad, magnetic field direction. As a spacecraft navigational aid, sensed field strength and direction is compared to a map of <a href="/wiki/Earth%27s_magnetic_field" title="Earth's magnetic field">Earth's magnetic field</a> stored in the memory of an on-board or ground-based guidance computer. If spacecraft position is known then attitude can be inferred.<sup id="cite_ref-15" class="reference"><a href="#cite_note-15"><span class="cite-bracket">[</span>15<span class="cite-bracket">]</span></a></sup> </p> <div class="mw-heading mw-heading3"><h3 id="Estimation_methods">Estimation methods</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=26" title="Edit section: Estimation methods"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>Attitude cannot be measured directly by any single measurement, and so must be calculated (or <a href="/wiki/Estimation_theory" title="Estimation theory">estimated</a>) from a set of measurements (often using different sensors). This can be done either statically (calculating the attitude using only the measurements currently available), or through the use of a statistical filter (most commonly, the <a href="/wiki/Kalman_filter" title="Kalman filter">Kalman filter</a>) that statistically combine previous attitude estimates with current sensor measurements to obtain an optimal estimate of the current attitude. </p> <div class="mw-heading mw-heading4"><h4 id="Static_attitude_estimation_methods">Static attitude estimation methods</h4><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=27" title="Edit section: Static attitude estimation methods"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>Static attitude estimation methods are solutions to <a href="/wiki/Wahba%27s_problem" title="Wahba's problem">Wahba's problem</a>. Many solutions have been proposed, notably Davenport's q-method, QUEST, TRIAD, and <a href="/wiki/Singular_value_decomposition" title="Singular value decomposition">singular value decomposition</a>.<sup id="cite_ref-16" class="reference"><a href="#cite_note-16"><span class="cite-bracket">[</span>16<span class="cite-bracket">]</span></a></sup> </p><p>Crassidis, John L., and John L. Junkins.. Chapman and Hall/CRC, 2004. </p> <div class="mw-heading mw-heading4"><h4 id="Sequential_estimation_methods">Sequential estimation methods</h4><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=28" title="Edit section: Sequential estimation methods"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <p>Kalman filtering can be used to sequentially estimate the attitude, as well as the angular rate. Because attitude dynamics (combination of <a href="/wiki/Euler%27s_equations_(rigid_body_dynamics)" title="Euler's equations (rigid body dynamics)">rigid body dynamics</a> and attitude kinematics) are non-linear, a linear Kalman filter is not sufficient. Because attitude dynamics is not very non-linear, the <a href="/wiki/Extended_Kalman_filter" title="Extended Kalman filter">Extended Kalman filter</a> is usually sufficient (however Crassidis and Markely demonstrated that the <a href="/wiki/Unscented_Kalman_filter" class="mw-redirect" title="Unscented Kalman filter">Unscented Kalman filter</a> could be used, and can provide benefits in cases where the initial estimate is poor).<sup id="cite_ref-17" class="reference"><a href="#cite_note-17"><span class="cite-bracket">[</span>17<span class="cite-bracket">]</span></a></sup> Multiple methods have been proposed, however the Multiplicative Extended Kalman Filter (MEKF) is by far the most common approach.<sup class="noprint Inline-Template Template-Fact" style="white-space:nowrap;">[<i><a href="/wiki/Wikipedia:Citation_needed" title="Wikipedia:Citation needed"><span title="This claim needs references to reliable sources. (May 2020)">citation needed</span></a></i>]</sup> This approach utilizes the multiplicative formulation of the error quaternion, which allows for the unity constraint on the quaternion to be better handled. It is also common to use a technique known as dynamic model replacement, where the angular rate is not estimated directly, but rather the measured angular rate from the gyro is used directly to propagate the rotational dynamics forward in time. This is valid for most applications as gyros are typically far more precise than one's knowledge of disturbance torques acting on the system (which is required for precise estimation of the angular rate). </p> <div class="mw-heading mw-heading3"><h3 id="Position/location_determination"><span id="Position.2Flocation_determination"></span>Position/location determination</h3><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=29" title="Edit section: Position/location determination"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <link rel="mw-deduplicated-inline-style" href="mw-data:TemplateStyles:r1236090951"><div role="note" class="hatnote navigation-not-searchable">Further information: <a href="/wiki/Position_determination" class="mw-redirect" title="Position determination">Position determination</a></div> <p>For some sensors and applications (such as spacecraft using magnetometers) the precise location must also be known. While pose<sup class="noprint Inline-Template" style="margin-left:0.1em; white-space:nowrap;">[<i><a href="/wiki/Wikipedia:Please_clarify" title="Wikipedia:Please clarify"><span title="The text near this tag may need clarification or removal of jargon. (December 2022)">clarification needed</span></a></i>]</sup> estimation can be employed, for spacecraft it is usually sufficient to estimate the position (via <a href="/wiki/Orbit_determination" title="Orbit determination">Orbit determination</a>) separate from the attitude estimation.<sup class="noprint Inline-Template Template-Fact" style="white-space:nowrap;">[<i><a href="/wiki/Wikipedia:Citation_needed" title="Wikipedia:Citation needed"><span title="This claim needs references to reliable sources. (December 2022)">citation needed</span></a></i>]</sup> For terrestrial vehicles and spacecraft operating near the Earth, the advent of <a href="/wiki/Satellite_navigation" title="Satellite navigation">Satellite navigation</a> systems allows for precise position knowledge to be obtained easily. This problem becomes more complicated for deep space vehicles, or terrestrial vehicles operating in Global Navigation Satellite System (GNSS) denied environments (see <a href="/wiki/Navigation" title="Navigation">Navigation</a>). </p> <div class="mw-heading mw-heading2"><h2 id="See_also">See also</h2><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=30" title="Edit section: See also"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <style data-mw-deduplicate="TemplateStyles:r1239009302">.mw-parser-output .portalbox{padding:0;margin:0.5em 0;display:table;box-sizing:border-box;max-width:175px;list-style:none}.mw-parser-output .portalborder{border:1px solid var(--border-color-base,#a2a9b1);padding:0.1em;background:var(--background-color-neutral-subtle,#f8f9fa)}.mw-parser-output .portalbox-entry{display:table-row;font-size:85%;line-height:110%;height:1.9em;font-style:italic;font-weight:bold}.mw-parser-output .portalbox-image{display:table-cell;padding:0.2em;vertical-align:middle;text-align:center}.mw-parser-output .portalbox-link{display:table-cell;padding:0.2em 0.2em 0.2em 0.3em;vertical-align:middle}@media(min-width:720px){.mw-parser-output .portalleft{clear:left;float:left;margin:0.5em 1em 0.5em 0}.mw-parser-output .portalright{clear:right;float:right;margin:0.5em 0 0.5em 1em}}</style><ul role="navigation" aria-label="Portals" class="noprint portalbox portalborder portalright"> <li class="portalbox-entry"><span class="portalbox-image"><span class="noviewer" typeof="mw:File"><span><img alt="" src="//upload.wikimedia.org/wikipedia/commons/thumb/6/68/Aviacionavion.png/28px-Aviacionavion.png" decoding="async" width="28" height="28" class="mw-file-element" srcset="//upload.wikimedia.org/wikipedia/commons/thumb/6/68/Aviacionavion.png/42px-Aviacionavion.png 1.5x, //upload.wikimedia.org/wikipedia/commons/thumb/6/68/Aviacionavion.png/56px-Aviacionavion.png 2x" data-file-width="1600" data-file-height="1600" /></span></span></span><span class="portalbox-link"><a href="/wiki/Portal:Aviation" title="Portal:Aviation">Aviation portal</a></span></li><li class="portalbox-entry"><span class="portalbox-image"><span class="noviewer" typeof="mw:File"><span><img alt="" src="//upload.wikimedia.org/wikipedia/commons/thumb/d/d6/RocketSunIcon.svg/28px-RocketSunIcon.svg.png" decoding="async" width="28" height="28" class="mw-file-element" srcset="//upload.wikimedia.org/wikipedia/commons/thumb/d/d6/RocketSunIcon.svg/42px-RocketSunIcon.svg.png 1.5x, //upload.wikimedia.org/wikipedia/commons/thumb/d/d6/RocketSunIcon.svg/56px-RocketSunIcon.svg.png 2x" data-file-width="128" data-file-height="128" /></span></span></span><span class="portalbox-link"><a href="/wiki/Portal:Spaceflight" title="Portal:Spaceflight">Spaceflight portal</a></span></li></ul> <ul><li><a href="/wiki/Astrionics#Attitude_determination_and_control" title="Astrionics">Astrionics#Attitude determination and control</a></li> <li><a href="/wiki/Longitudinal_static_stability" class="mw-redirect" title="Longitudinal static stability">Longitudinal static stability</a></li> <li><a href="/wiki/Directional_stability" title="Directional stability">Directional stability</a></li> <li><a href="/wiki/Reaction_control_system" title="Reaction control system">Reaction control system</a></li> <li><a href="/wiki/Spacecraft_flight_dynamics#Attitude_control" title="Spacecraft flight dynamics">Spacecraft_flight_dynamics#Attitude_control</a></li> <li><a href="/wiki/Triad_method" title="Triad method">Triad method</a></li> <li><a href="/wiki/Wahba%27s_problem" title="Wahba's problem">Wahba's problem</a></li></ul> <div class="mw-heading mw-heading2"><h2 id="References">References</h2><span class="mw-editsection"><span class="mw-editsection-bracket">[</span><a href="/w/index.php?title=Spacecraft_attitude_control&action=edit&section=31" title="Edit section: References"><span>edit</span></a><span class="mw-editsection-bracket">]</span></span></div> <style data-mw-deduplicate="TemplateStyles:r1239543626">.mw-parser-output .reflist{margin-bottom:0.5em;list-style-type:decimal}@media screen{.mw-parser-output .reflist{font-size:90%}}.mw-parser-output .reflist .references{font-size:100%;margin-bottom:0;list-style-type:inherit}.mw-parser-output .reflist-columns-2{column-width:30em}.mw-parser-output .reflist-columns-3{column-width:25em}.mw-parser-output .reflist-columns{margin-top:0.3em}.mw-parser-output .reflist-columns ol{margin-top:0}.mw-parser-output .reflist-columns li{page-break-inside:avoid;break-inside:avoid-column}.mw-parser-output .reflist-upper-alpha{list-style-type:upper-alpha}.mw-parser-output .reflist-upper-roman{list-style-type:upper-roman}.mw-parser-output .reflist-lower-alpha{list-style-type:lower-alpha}.mw-parser-output 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