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Inertial Sensors and Attitude Derivation

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Introduction to Avionics Systems

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 aircraft motion feedback which enables a manoeuvre 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.

    Google Scholar 

  • Bergh, R.A., Dual-ramp closed-loop fiber-optic gyroscope: Proc. SPIE 1169, pp. 429–439 (1989)

    Article  Google Scholar 

  • Ebberg, A. and Schiffner, G., Closed-loop fiber-optic gyroscope with a sawtooth phase modulated feedback: Opt. Lett. 10, pp. 300–302, (1985)

    Article  Google Scholar 

  • Lefevre, H., The fiber optic gyroscope: Artech House, Boston — London

    Google Scholar 

  • Lefevre, H., Martin, P., Morisse, J., Simonpietri, P., Vvivenot, P., Arditty, H.J., High dynamic range fiber gyro with all-digital processing: SPIE vol. 1367, 70–80 (1990)

    Google Scholar 

  • Matthews, A., Fiber Optic Based Inertial Measuring Unit: SPIE Vol. 1173 Fiber Optic Systems for Mobile Platforms III, 1989

    Google Scholar 

  • Page, J.L., Multiplexed Approach to the Fiber Optic Gyro Inertial Measuring Unit: OE/FIBERS 1990 SPIE Conference, San Jose, California September 1990

    Google Scholar 

  • Ribes, M., Spahlinger, G., Kemmler, M.W., 0.1 °/hr DSP-controlled fiber optic gyroscope: SPIE vol. 2837, 199–207 (1996)

    Article  Google Scholar 

  • Sanders, G.A., Szafraniec, B., Strandjord, L., Bergh, R., Kalisjek, A., Dankwort, R., Lange, C., and Kimmel, D., Progress in high performance fiber optic gyroscopes: 116/OWB1–1: Selected topics in advanced solid state an fiber optic sensors: Year 2000

    Google Scholar 

  • Siouris, G.M., Aerospace Avionic Systems: Academic Press 1993

    Google Scholar 

  • Wrigley, W., Hollister, W.M., and Denhard, W.G., Gyroscopic Theory, Design and Instrumentation: MIT Press 1969

    Google Scholar 

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© 2003 Springer Science+Business Media New York

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Collinson, R.P.G. (2003). Inertial Sensors and Attitude Derivation. In: Introduction to Avionics Systems. Springer, Boston, MA. https://doi.org/10.1007/978-1-4419-7466-2_5

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  • DOI: https://doi.org/10.1007/978-1-4419-7466-2_5

  • Publisher Name: Springer, Boston, MA

  • Print ISBN: 978-1-4757-5584-8

  • Online ISBN: 978-1-4419-7466-2

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