## NOAA KLM User's Guide## Appendix I.3 |

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There area at least two ways to define the satellite subpoint. The first way is to call it the intersection with the earth ellipsoid surface of a line from the satellite to the earth ellipsoid's center - call this the geocentric subpoint. The second way is to call it the intersection with the earth ellipsoid's surface of a line from the satellite perpendicular to the ellipsoid - call this the geodetic subpoint. (See Figure I.3-1 and imaging that the feature being located is the satellite.) When the satellite is over the North or South Pole or over the Equator, geodetic and geocentric subpoints will be colocated; when it is over 45° North or South, the distance between the geocentric and geodetic subpoints will be about 2.5 kilometers for NOAA satellites. Documents describing the NOAA K, L and M Attitude Detection and Control System (ADACS) define the subpoint to be geodetic.

Case 1 - The satellite subpoint is defined to be the geocentric subpoint.

In this case, the unit vector points in the opposite direction from the Satellite position vector. So, if the satellites's position vector in earth-centered-inertial coordinates is

then

where .

Case 2 - The satellite subpoint is defined to be the geodetic subpoint.

In this case, the earth-centered-inertial coordinates of the satellite will be known. The problem will be to use them to find the direction cosines from the satellite toward the geodetic subpoint. Again, the position vector of the satellite will be

.

The magnitude of the component of this vector that is in the equatorial plane is

.

If DIST_{sateq} = 0 and Z_{sat} > 0.0 or if DIST_{sateq} = 0 and Z_{sat} < 0.0, or if Z_{sat} = 0.0, or if Z_{sat} =0.0 the
satellite is over one of the earth's poles or the earth's equator and the geodetic subpoint is the
same as the geocentric subpoint.

If DIST_{sateq} = 0
0 and Z_{sat}
latitude (See "I.4 CONVERSION BETWEEN GEODETIC AND GEOCENTRIC LATITUDE",equation (I-36)).

where h_{sat}, the height of the satellite above the ellipsoid, has been substituted for h_{f}, the height of the feature of interest, the satellite's
geocentric latitude, φ_{satgc}, has been substituted for φ_{gcf}, the geocentric latitude of the feature, and the satellite's geodetic
latitude, φ_{satgd}, has been substituted for φ_{gdf}, the geodetic latitude of the feature. The tangent of the satellite’s geocentric
latitude is given by

Use it in the above equation, and solve for φ_{satgd } by the procedures given in section, I.4, B "Conversion from Geodetic Latitude", Case 2. The right
ascension of the satellite is Θ_{sat} = arctan(Y_{sat}/X_{sat}). Find the earth-centered-inertial position vector of the geodetic satellite
subpoint, (x_{s},y_{s},z_{s}), by using equations (I-31), (I-32) and (I-33) and replacing φ_{gdf} with φ_{satgd} and θ_{f}
with Θ_{sat}. The vector from the satellite to its geodetic subpoint will be

and its magnitude will be

.

The unit vector pointing from the satellite toward its geodetic subpoint will be, then,

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Last Updated Tuesday, 03-Mar-2009 10:29:33 EST

Please see the NCDC Contact Page if you have questions or comments.