Attitude and heading reference system: Difference between revisions
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An '''attitude and heading reference system''' ( |
An '''attitude and heading reference system''' ('''AHRS''') consists of sensors on three axes that provide [[Aircraft heading|heading]], [[Aircraft attitude|attitude]] and [[Yaw angle|yaw]] information for aircraft. They are designed to replace traditional mechanical [[gyroscopic]] [[flight instruments]] and provide superior reliability and accuracy. |
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AHRS consist of either solid-state or [[microelectromechanical systems]] (MEMS) [[gyroscopes]], [[accelerometers]] and [[magnetometers]] on all three axes. The key difference between an [[inertial measurement unit]] (IMU) and an AHRS is the addition of an on-board processing system in an AHRS which provides solved attitude and heading solutions versus an IMU which just delivers sensor data to an additional device that solves the attitude solution. |
AHRS consist of either solid-state or [[microelectromechanical systems]] (MEMS) [[gyroscopes]], [[accelerometers]] and [[magnetometers]] on all three axes. The key difference between an [[inertial measurement unit]] (IMU) and an AHRS is the addition of an on-board processing system in an AHRS which provides solved attitude and heading solutions versus an IMU which just delivers sensor data to an additional device that solves the attitude solution. |
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Revision as of 02:43, 5 April 2014
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An attitude and heading reference system (AHRS) consists of sensors on three axes that provide heading, attitude and yaw information for aircraft. They are designed to replace traditional mechanical gyroscopic flight instruments and provide superior reliability and accuracy.
AHRS consist of either solid-state or microelectromechanical systems (MEMS) gyroscopes, accelerometers and magnetometers on all three axes. The key difference between an inertial measurement unit (IMU) and an AHRS is the addition of an on-board processing system in an AHRS which provides solved attitude and heading solutions versus an IMU which just delivers sensor data to an additional device that solves the attitude solution. In addition to attitude determination an AHRS may also form part of an inertial navigation system.
A form of non-linear estimation such as an Extended Kalman filter is typically used to compute the solution from these multiple sources.[1]
AHRS have proven themselves to be highly reliable and are in common use in commercial and business aircraft. AHRS are typically integrated with electronic flight instrument systems (EFIS) which are the central part of so-called glass cockpits, to form the primary flight display. AHRS can be combined with air data computers to form an "air data, attitude and heading reference systems" (ADAHRS), which provide additional information such as airspeed, altitude and outside air temperature.
One abbreviation used in technology for sensor arrays used in AHRS is MARG (Magnetic, Angular Rate, and Gravity).[2]