Abstract
Gyroscopes (hereafter abbreviated to gyros) and accelerometers are known as inertial sensors. This is because they exploit the property of inertia, namely the resistance to a change in momentum, to sense angular motion in the case of the gyro and changes in linear motion in the case of the accelerometer. They are fundamental to the control and guidance of an aircraft. For example, in a FBW aircraft the rate gyros and accelerometers provide the aircraftmotion feedback which enables amanoeuvre command control to be achieved and an aerodynamically unstable aircraft to be stabilised by the flight control system (as explained in Chapter 4).
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Further Reading
AGARD Lecture Series No. 95, Strap-Down Inertial Systems.
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Collinson, R.P.G. (2011). Inertial Sensors and Attitude Derivation. In: Introduction to Avionics Systems. Springer, Dordrecht. https://doi.org/10.1007/978-94-007-0708-5_5
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DOI: https://doi.org/10.1007/978-94-007-0708-5_5
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