Improved Satellite Launcher Navigation Performance by Using the Reference Trajectory Data

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Authors
  1. Beaudoin, Y.
  2. André Desbiens, A.
  3. Gagnon, E.
  4. Landry, R.J.
Corporate Authors
Defence Research and Development Canada, Valcartier Research Centre, Quebec QC (CAN);Laval Univ, Quebec QUE (CAN);Ecole de Technologie Superieure, Montreal QUE (CAN)
Abstract
The navigation is a critical element of a satellite launcher. The objective of this research is to evaluate the additional precision and robustness provided to the navigation solution by using the reference trajectory data. To include this information, the error state model of a GPS/INS configuration is augmented to estimate the difference between the launcher and the reference trajectory attitude data. The assessment of the precision gain is made using the standard deviation of the attitude, velocity and position estimation errors. The robustness is evaluated considering the loss of precision caused by a GPS outage. The velocity estimation is slightly improved, but the attitude estimation greatly benefits from the additional information. Also, the robustness to a GPS outage is greatly improved for all estimated values. The augmented model can withstand errors in the variances of the external perturbations. However, this one could be sensitive to modelling errors.
Keywords
Navigation;Satellite Launcher;Reference Trajectory;GPS;INS
Report Number
DRDC-RDDC-2015-N002 — External Literature
Date of publication
16 Apr 2015
Number of Pages
18
DSTKIM No
CA040188
CANDIS No
801276
Format(s):
Electronic Document(PDF)

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