An integrated navigation algorithm for Aerospace Vehicle based on extended H∞ filter

Author

Hui Zhao ; Zhi Xiong ; Feng Yu ; Jialiang Pan ; Yongrong Sun

Author_Institution

Coll. of Autom. Eng., Nanjing Univ. of Aeronaut. & Astronaut., Nanjing, China

fYear

2014

fDate

28-30 July 2014

Firstpage

822

Lastpage

826

Abstract

To reduce the effect of changes in gravity field and radius on Aerospace Vehicles navigation system, an inertial navigation algorithm in launch inertial coordinate for ASV is studied in this paper firstly. To overcome the poor performance of Kalman filter in uncertain environment, an extended H_∞ filtering algorithm is designed secondly. Combining the advantages of launch inertial coordinate and H_∞ filter, an integrated navigation algorithm for Aerospace Vehicle is proposed in this paper. The simulation results show that the proposed algorithm can improve the accuracy of the navigation system for ASVs.

Keywords

H_∞ filters; aerospace control; navigation; ASV; aerospace vehicle navigation system; change effect reduction; extended H_∞ filtering algorithm; gravity field; integrated navigation algorithm; launch inertial coordinate; radius; uncertain environment; Filtering algorithms; Gravity; Mathematical model; Navigation; Noise; Robustness; Vehicles; Aerospace Vehicles; extended H∞ filter; integrated navigation system;

fLanguage

English

Publisher

ieee

Conference_Titel

Control Conference (CCC), 2014 33rd Chinese

Conference_Location

Nanjing

Type

conf

DOI

10.1109/ChiCC.2014.6896733

Filename

6896733