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Abstract

This chapter discusses some of the most important gyroscopic rotation sensors that have been in use throughout this century. The central issues are their mathematical model and characteristic error sources, which allow the prediction of their performance in various applications and environments. The knowledge of the angular attitude of a flight vehicle with respect to an external reference axis system is of paramount importance in the realization of flight control, attitude estimation and control, and automatic navigation systems. The typical quantities to be measured are the vehicle attitude Euler angles Φ, Θ, and Ψ, defined with respect to the local level and local north and the inertial vehicular angular rates P, Q, R. These quantities are depicted in Figure 4.1. The transformation of any vector from Earth axes X e , Y e , Z e to body axes x b , y b , z b is performed by the Euler transformation [E]=[Φ][Θ][Ψ], formulated in detail in Appendix A4.

Keywords

Drift Rate Angular Rate Spin Axis Horizontal Acceleration Mean Time Between Failure 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag New York, Inc. 1996

Authors and Affiliations

  • Shmuel Merhav
    • 1
  1. 1.Department of Aerospace Engineering TechnionIsrael Institute of TechnologyHaifaIsrael

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