Simulation Based on MEMS INS Performance Analyses in Flying Mission

Author

Wenling, Liu ; Pei, Chen ; Chao, Han

Author_Institution

Sch. of Astronaut., Beihang Univ., Beijing, China

fYear

2010

fDate

17-19 Sept. 2010

Firstpage

1205

Lastpage

1208

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.

Keywords

accelerometers; gyroscopes; inertial navigation; micromechanical devices; INS model; MEMS INS performance analyses; MEMS performance; MIMU; accelerometer error models; flying mission; gyroscope; inertial navigation system; micro electro mechanical system; micro inertial measurement unit; navigation precision; sounding rocket; Acceleration; Accelerometers; Gyroscopes; Micromechanical devices; Navigation; Rockets; Trajectory; Error Model; INS; MEMS; Navigation Precision;

fLanguage

English

Publisher

ieee

Conference_Titel

Pervasive Computing Signal Processing and Applications (PCSPA), 2010 First International Conference on

Conference_Location

Harbin

Print_ISBN

978-1-4244-8043-2

Electronic_ISBN

978-0-7695-4180-8

Type

conf

DOI

10.1109/PCSPA.2010.296

Filename

5636013