HiNAV Inertial / GNSS Hybrid Navigation System for launchers and re-entry vehicles

Author

Broquet, R. ; Perrimon, N. ; Polle, B. ; Hyounet, P. ; Krauss, P.A. ; Drai, R. ; Voirin, T. ; Fernandez, V.

Author_Institution

Astrium Satellites Toulouse, Toulouse, France

fYear

2010

fDate

8-10 Dec. 2010

Firstpage

1

Lastpage

6

Abstract

Through the HybrId NAVigation system (HiNAV) project, Astrium Satellites studies the hybridisation of GNSS and Inertial Measurement Unit (IMU) measurements in a tight aiding / tight hybridisation architecture dedicated to the navigation function of launchers and re-entry spacecrafts. It is also a valuable solution for the safeguard function of launchers. In the frame of this project, the HiNAV product has been specified, a preliminary design has been defined accordingly, and performances have been assessed using a high fidelity simulator. In parallel a realtime test bench including a breadboard which implements the HiNAV software is currently finalized, leading HiNAV to TRL 4 at beginning of 2011, and a flight demonstration on a sounding rocket is under definition.

Keywords

aircraft navigation; inertial navigation; satellite navigation; space vehicles; Astrium satellites; GNSS; HiNAV software; hybrid navigation system; inertial measurement unit; inertial navigation; navigation function; re-entry spacecrafts; realtime test bench; safeguard function; sounding rocket; tight hybridisation architecture; Global Navigation Satellite Systems; Radio frequency; Receivers; Satellites; Software;

fLanguage

English

Publisher

ieee

Conference_Titel

Satellite Navigation Technologies and European Workshop on GNSS Signals and Signal Processing (NAVITEC), 2010 5th ESA Workshop on

Conference_Location

Noordwijk

Print_ISBN

978-1-4244-8740-0

Type

conf

DOI

10.1109/NAVITEC.2010.5707998

Filename

5707998