Abstract
This paper describes the principle and implementation of a simulator based on Inertial Navigation System (INS) using Micro Electro Mechanical System (MEMS) The MEMS is composed of Micro Inertial Measurement Unit (MIMU). The gyroscope and accelerometer error models are established according to the characteristics of the MEMS. The principle of INS is described and an INS model is established to simulate and analyze the influence of the MEMS performance on navigation precision. An example of a sounding rocket is presented in the paper to analyze the INS performance using MEMS in flying mission.
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