A Simple and Precise Approach to Position and Velocity Estimation of Low Earth Orbit Satellites

PDF

Authors
  1. Beaulne, P.D.
  2. Sikaneta, I.C.
Corporate Authors
Defence R&D Canada - Ottawa, Ottawa ONT (CAN)
Abstract
This technical memorandum presents a procedure for calculating a satellite’s state vector (position and velocity), at arbitrary times on its orbit and with a precision of up to 10cm, from a more sparse set of state vectors (measured or predicted) provided by the satellite itself or by its ground station. No orbit propagation is necessary. While very precise, the procedure’s accuracy is limited to the accuracy of the input state vectors. The first part of the memo deals with time systems important in astrodynamic applications, different coordinate systems used to describe satellite state vectors, and the various coordinate transformations necessary for the task. The second part describes the use of Hermite polynomials to interpolate (upsample) new state vectors in the appropriately transformed coordinate system. In the final part, the precision of the procedure is verified by decimating an ERS-2 state vector set and using the sparse set to upsample new state vectors at the original ERS-2 rate. This interpolated set is then compared to the original measured set, and precisions of up to 10cm are observed. Finally, as an example, a set of RADARSAT-1 state vectors are upsampled to 10 Hz from their natural rate of 1/480 Hz.

Il y a un résumé en français ici.

Keywords
SYNTHETIC APERTURE RADAR;GEOLOCATION;TIME SYSTEMS;COORDINATE TRANSFORMATIONS;ORBIT INTERPOLATION;Low Earth Orbits
Report Number
DRDC-OTTAWA-TM-2005-250 — Technical Memorandum
Date of publication
01 Dec 2005
Number of Pages
58
DSTKIM No
CA026985
CANDIS No
524997
Format(s):
CD ROM

Permanent link

Document 1 of 1

Date modified: