Design of loosely-coupled INS/GPS integration system applied to Boeing-747 aircraft model
by Chingiz Hajiyev; Deniz Burak Kamiloğlu
International Journal of Sustainable Aviation (IJSA), Vol. 4, No. 3/4, 2018

Abstract: Inertial navigation systems (INSs) require some type of aiding and updating in the long term to remain valid. In many applications for purpose of INSs error compensation its integration by GPS is preferred. In this study, the Kalman filter-based loosely-coupled integrated INS/GPS is designed and investigated on the Boeing-747 aircraft model. The INS errors are modelled, estimated and compared with integrated navigation system errors which are position, velocity and attitude for each axis. The proposed integrated navigation system has high accuracy than stand-alone INS and it provides more reliable navigation information.

Online publication date: Wed, 13-Mar-2019

The full text of this article is only available to individual subscribers or to users at subscribing institutions.

 
Existing subscribers:
Go to Inderscience Online Journals to access the Full Text of this article.

Pay per view:
If you are not a subscriber and you just want to read the full contents of this article, buy online access here.

Complimentary Subscribers, Editors or Members of the Editorial Board of the International Journal of Sustainable Aviation (IJSA):
Login with your Inderscience username and password:

    Username:        Password:         

Forgotten your password?


Want to subscribe?
A subscription gives you complete access to all articles in the current issue, as well as to all articles in the previous three years (where applicable). See our Orders page to subscribe.

If you still need assistance, please email subs@inderscience.com