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Applications in the Flight Attitude Control System

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Abstract

Due to the breakthrough provided by the calculation method and software, the output of multi-information from a “non-driven structure silicon micromechanical gyroscope” can be realized.

Copyright information

© National Defense Industry Press and Springer-Verlag GmbH Germany 2018

Authors and Affiliations

  1. 1.Beijing Information Science and Technology UniversityBeijingChina
  2. 2.Academy of Armored Forces EngineeringBeijingChina

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