predict_orbit_t Struct Reference

Satellite orbit definitions, according to defined NORAD TLE. More...

#include <predict.h>

Collaboration diagram for predict_orbit_t:

Data Fields
char	name [128]
	Name of satellite.
predict_julian_date_t	time
	Timestamp for last call to orbit_predict.
double	position [3]
	ECI position in km.
double	velocity [3]
	ECI velocity in km/s.
double	latitude
	Latitude in radians, northing/easting.
double	longitude
	Longitude in radians, northing/easting.
double	altitude
	Altitude in meters.
int	eclipsed
	Whether satellite is eclipsed by the earth.
double	eclipse_depth
	Eclipse depth.
enum predict_ephemeris	ephemeris
	Which perturbation model to use.
char	line1 [70]
	Original TLE line number one:
char	line2 [70]
	Original TLE line number two:
predict_tle_t	tle
	Original tle_t used to hold processed tle parameters used in calculations.
int	catnum
	Satellite number (line 1, field 2)
long	setnum
	Element number (line 1, field 13)
char	designator [10]
	International designator (line 1, fields 4, 5, 6)
int	year
	Epoch year (last two digits) (line 1, field 7)
double	refepoch
	Epoch day (day of year and fractional portion of day, line 1, field 8)
double	incl
	Inclination (line 2, field 3)
double	raan
	Right Ascension of the Ascending Node [Degrees] (line 2, field 4)
double	eccn
	Eccentricity (decimal point assumed) (line 2, field 5)
double	argper
	Argument of Perigee [Degrees] (line 2, field 6)
double	meanan
	Mean Anomaly [Degrees] (line 2, field 7)
double	meanmo
	Mean Motion [Revs per day] (line 2, field 8)
double	drag
	First Time Derivative of the Mean Motion divided by two (line 1, field 9)
double	nddot6
	Second Time Derivative of Mean Motion divided by six (decimal point assumed, line 1, field 10)
double	bstar
	BSTAR drag term (decimal point assumed, line 1, field 11)
int	orbitnum
	Orbital number (line 2, field 9)
void *	ephemeris_data
	Ephemeris data structure pointer.

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Detailed Description

Satellite orbit definitions, according to defined NORAD TLE.

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Field Documentation

double predict_orbit_t::altitude

Altitude in meters.

double predict_orbit_t::argper

Argument of Perigee [Degrees] (line 2, field 6)

double predict_orbit_t::bstar

BSTAR drag term (decimal point assumed, line 1, field 11)

int predict_orbit_t::catnum

Satellite number (line 1, field 2)

char predict_orbit_t::designator[10]

International designator (line 1, fields 4, 5, 6)

double predict_orbit_t::drag

First Time Derivative of the Mean Motion divided by two (line 1, field 9)

double predict_orbit_t::eccn

Eccentricity (decimal point assumed) (line 2, field 5)

double predict_orbit_t::eclipse_depth

Eclipse depth.

int predict_orbit_t::eclipsed

Whether satellite is eclipsed by the earth.

enum predict_ephemeris predict_orbit_t::ephemeris

Which perturbation model to use.

void* predict_orbit_t::ephemeris_data

Ephemeris data structure pointer.

double predict_orbit_t::incl

Inclination (line 2, field 3)

double predict_orbit_t::latitude

Latitude in radians, northing/easting.

char predict_orbit_t::line1[70]

Original TLE line number one:

char predict_orbit_t::line2[70]

Original TLE line number two:

double predict_orbit_t::longitude

Longitude in radians, northing/easting.

double predict_orbit_t::meanan

Mean Anomaly [Degrees] (line 2, field 7)

double predict_orbit_t::meanmo

Mean Motion [Revs per day] (line 2, field 8)

char predict_orbit_t::name[128]

Name of satellite.

double predict_orbit_t::nddot6

Second Time Derivative of Mean Motion divided by six (decimal point assumed, line 1, field 10)

int predict_orbit_t::orbitnum

Orbital number (line 2, field 9)

double predict_orbit_t::position[3]

ECI position in km.

double predict_orbit_t::raan

Right Ascension of the Ascending Node [Degrees] (line 2, field 4)

double predict_orbit_t::refepoch

Epoch day (day of year and fractional portion of day, line 1, field 8)

long predict_orbit_t::setnum

Element number (line 1, field 13)

predict_julian_date_t predict_orbit_t::time

Timestamp for last call to orbit_predict.

predict_tle_t predict_orbit_t::tle

Original tle_t used to hold processed tle parameters used in calculations.

double predict_orbit_t::velocity[3]

ECI velocity in km/s.

int predict_orbit_t::year

Epoch year (last two digits) (line 1, field 7)

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The documentation for this struct was generated from the following file:

• include/predict/predict.h