brouwer - Propagate the orbital elements from epoch to the time of interest

SYNTAX

FUNCTION brouwer(t, model, truea, rsat, thetas, anlng, inclin, zdot, eorbit, porbit, slat, slong)

     double		*t;
     struct MODEL	*model;
     double		*truea;
     double		*rsat;
     double		*thetas;
     double		*anlng;
     double		*inclin;
     long		*zdot;
     long		*eorbit;
     long		*porbit;
     double		*slat;
     double		*slong;

PARAMETERS

t (double *, input)

Total seconds past epoch.

model (struct MODEL *, input)

Model and orbital information.

truea (double *, output)

True anomaly past perigee.

rsat (double *, output)

Distance of satellite from earth center.

thetas (double *, output)

True anomaly past equator.

anlng (double *, output)

Longitude of ascending node.

inclin (double *, output)

Inclination angle.

zdot (long *, output)

Direction of pass:

     =  1:	Ascending
     = -1:	Descending

eorbit (long *, output)

Orbit counter from equator.

porbit (long *, output)

Orbit counter from perigee.

slat (double *, output)

Geocenteric latitude of satellite.

slong (double *, output)

Longitude of satellite.

DESCRIPTION

Calculate new orbital elements at time t. Count the perigee and equator orbits. Make the mean anomaly less than 2 * PI but not less than zero (0). Change the mean elements into oscilating elements. Find the new eccentric anomaly. Calculate the true anomaly. Determine the true anomaly past the ascending node. Find orbital radius of the satellite at thetas. Determine the pass direction to be ascending or descending. Find the satellite latitude and longitude.

RETURN VALUE

brouwer() has no return value.