A Precise State Transition Model for Aircraft Navigation

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Authors
  1. Sinha, A.
  2. Stolpner, S.
  3. Mukherjee, A.
  4. Monckton, S.
Corporate Authors
Defence Research and Development Canada, Suffield Research Centre, Ralston AB (CAN);A.U.G. Signals Ltd, Toronto ONT (CAN)
Abstract
This article considers the problem of accurately modeling the kinematic state transition of an Unmanned Aerial Vehicle (UAV). The full 3D range of motion is accurately captured using compact equations for position update derived in this work. This derivation makes use of the independence of the rotation and translation components of a 3D rigid motion. The proposed motion model is transparent to the sensors used in the system; it is particularly useful in GPS-denied environments and can contribute to different aspects of robust navigation, such as accurate state estimation, sensor fault tolerance and sensor bias estimation. Experimental results comparing the performance of the proposed kinematic model with those typically used demonstrate its superiority.

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Keywords
fault tolerance;kalman filter
Report Number
DRDC-RDDC-2016-P066 — External Literature
Date of publication
21 Jul 2016
Number of Pages
15
Reprinted from
Geomatica, vol 68, no 4, 2014, p 237-242
DSTKIM No
CA042938
CANDIS No
804210
Format(s):
Electronic Document(PDF)

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