Background

Example Ephemeris and units

Defining Equations

Coordinate System

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The “SPOT model” is an analytic (General Perturbation) model of the motion of a satellite, intended for use over short periods of time (day or two) with near circular low-Earth orbits. It was originally developed for use with the SPOT satellite (Satellite Pour l'Observation de la Terre) as a fast approximation for on-board use, etc.

Unlike the ‘classic’ GP models, where the ephemeris consist of the epoch and the Keplarian set (plus drag terms sometimes), the SPOT model has the epoch and 13 fitted parameters (6 essentially classical and 7 perturbation terms) that allow higher short-term accuracy.

It
was adopted for the METOP series of satellites as offering higher
accuracy than some more general analytic models (e.g. SGP4,
Brower-Lyddane) but without the huge CPU load of a numerical
integrator (Special Perturbation) model. The study concluded the
error for a 12 hours period was of the order of 0.172km RMS, and METOP
carries sets of elements for 0-12h, 12-24h and 24-36h periods.

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When
using the data from METOP, the main problem is the unannounced change
of units, for example, the Eumetsat document EPS/GGS/TN/980021 Issue
2, Rev. 0, 03 October 2003 “Metop Administration Message
Technical Note” is wrong, it gives the equations in Annex 3 and
in this case it is clearly stated that times is in
seconds. Also the format of the equations imply radian units (e.g.
use of P_{11} parameter in conjunction with a per-day
periodicity).
Furthermore, the cited document RD-1 EPS/Metop
–
Technical Note on Orbit Prediction, GMV-EPSFDS-TN-002 clearly
states the units to be radians and seconds (Table 4-8, page
40).

We
now know that the units of the message are degrees and days!

The 13 fitted parameters for METOP-A at Tue Feb 06 01:00:00.000 2007
are:

Term |
Example Value |
Units |
Approximate physical interpretation |

1 |
7195.643693 |
km |
Semi-major axis |

2 |
-5.9e-005 |
- |
Eccentricity and cos(argument of perigee) at epoch. |

3 |
0.00117 |
- |
Eccentricity and sin(argument of perigee) at epoch. |

4 |
98.762653 |
degrees |
Inclination |

5 |
98.319158 |
degrees |
Right Ascension of Ascending Node at epoch. |

6 |
246.173671 |
degrees |
Mean argument of latitude at epoch. |

7 |
0.988393 |
degrees/day |
Rate of change of RAAN, should average around 360/365.25 = 0.9856 deg/day for a sun-synchronous orbit. |

8 |
5114.436329 |
degrees/day |
Rate of change of argument of latitude (i.e. mean motion) |

9 |
0.000849 |
- |
Fudge factor based on zonal gravitational potential term (see below). |

10 |
-0.003888 |
degrees |
‘Amplitude’ of J |

11 |
250.510794 |
degrees |
‘Phase’ of J |

12 |
0.022983 |
degrees/day |
Drag term (quadratic in mean motion). |

13 |
-0.048474 |
1/day |
Similar to the rate of change of argument of perigee (in radian/day), but also of eccentricity and really just a solved-for fudge factor. |

NOTES:

1) METOP is intended to
maintain a 'frozen' orbit when operational, with the argument of
perigee staying around the 90° value.

2) The osculating value of argument of perigee
changes significantly due to perturbations on low eccentricity orbits,
this is different to the mean perigee.

3) The P_{9} fudge factor is approximately
given by:

Where a is the semi-major
axis, a_{E} is the Earth radius, and J_{2}
the zonal
gravity constant of 1.08263e-003 (in the above example, this equation
yields 0.0008506078 rather than the solved-for value of 0.000849)

4) Unlike the NOAA satellites,
it is expected that METOP will perform occasional orbit correction
manoeuvres, thus rendering prior ephemeris invalid.

The model itself is defined by the following equations, working with t (time since epoch), first compute the 'mean' mean argument latitude (without the short term gravitational perturbations) from:

Then compute the following osculating parameters:

The resulting osculating terms are a

In general, all of the ‘degrees’ terms (4-8, 10-12) in the elements are converted to radian units before the calculations are preformed, and the resulting osculating elements are then also in radians.

Next the traditional elements are extracted by:

Typically the atan2() function is used to resolve the quadrant of ω

In the Dundee case, we specifically wanted to make a set of osculating elements that resemble the intermediate stage of the SGP4 model, prior to conversion to XYZ format. To do this we solve the equation of Kepler to obtain the eccentric anomaly E, from the implicit relationship:

We do this by Newton-Raphson iteration. Given the typically small values for eccentricity, this will converge rapidly and without problems. Alternatively, it may be sufficient to use some of the approximations to the solution as they are often good enough for small eccentricities.

Then the true anomaly f, true argument of latitude u

Finally leading to the terms for velocity computation (the radial velocity and along-track velocity components):

Where GM is the Earth’s gravitational constant of 398600.4418 km

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The full conversion with Polar Motion to the International Terrestrial Reference Frame may not be necessary, but for maximum accuracy (~0.02km RMS) it should be done. However, remember the SPOT model is only around 0.172km RMS accuracy!

In matrix terms:

ITRF = [PM][ST][NUT][PREC]J2000

Each of these matrices is covered in most text books, for example, see pages 219-228 of “Fundamentals of Astrodynamics and Applications”, 2nd Edition, David A. Vallado, ISBN 1-881883-12-4

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(c) Paul Crawford, 20 Feb 2007. All rights reserved. No warranty, etc.