Research on Radar Aided SINS Autonomous Navigation Scheme for Lunar Soft Landing

Author

Chen, Shuai ; Xue, Xiaozhong ; Guan, Xueyuan ; Bai, Hongyang ; Wu, Panlong

Author_Institution

Coll. of Autom., Nanjing Univ. of Sci. & Technol., Nanjing, China

fYear

2010

fDate

25-27 June 2010

Firstpage

5526

Lastpage

5529

Abstract

In order to meet the requirements of high precision orbit determination and prediction for the safe and pinpoint lunar soft landing, the paper presents an autonomous navigation based on SINS (strapdown inertial navigation system) /DOPPLER Radar/Radar Altimeter integrated navigation system. According to the error characteristics of each sensor, an effective information fusion algorithm is designed. The excellent result of vehicle experiment indicates that the integrated navigation has high precision, the system design method is successful, and it has better value of engineering application.

Keywords

Doppler radar; inertial navigation; radar altimetry; radar astronomy; radionavigation; Doppler radar; error characteristics; high precision orbit determination; high precision orbit prediction; information fusion algorithm; lunar soft landing; radar aided SINS autonomous navigation scheme; radar altimeter integrated navigation system; strapdown inertial navigation system; Doppler radar; Global Positioning System; Inertial navigation; Moon; Silicon compounds; Data fusion; Doppler navigation; Kalman filter; inertial navigation; integrated navigation;

fLanguage

English

Publisher

ieee

Conference_Titel

Electrical and Control Engineering (ICECE), 2010 International Conference on

Conference_Location

Wuhan

Print_ISBN

978-1-4244-6880-5

Type

conf

DOI

10.1109/iCECE.2010.1343

Filename

5631748