In this chapter, the measurement equations of gyroscope and accelerometer and the differential equations of strapdown inertial navigation system (SINS) are presented at first. For high accurate application, in order to reduce the influence of output noise on the calculation accuracy of the system and make full use of the output information, the outputs of gyroscope and accelerometer are all increments, namely the angle increment output by gyroscope and the velocity increment output by accelerometer.
Inertial Autonomous Navigation Technology
sp.
Spacecraft Autonomous Navigation Technologies Based on Multi-source Information Fusion ; Kapitel : 7 ; 149-161
01.08.2020
13 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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