Container for processed TLE data from TLE strings. More...

#include <predict.h>

Data Fields
int	satellite_number
	Satellite number (line 1, field 2) More...

long	element_number
	Element number (line 1, field 13) More...

char	designator [10]
	International designator (line 1, fields 4, 5, 6) More...

int	epoch_year
	Epoch year (last two digits) (line 1, field 7) More...

double	epoch_day
	Epoch day (day of year and fractional portion of day, line 1, field 8) More...

double	inclination
	Inclination (line 2, field 3) More...

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

double	eccentricity
	Eccentricity (line 2, field 5) More...

double	argument_of_perigee
	Argument of Perigee [Degrees] (line 2, field 6) More...

double	mean_anomaly
	Mean Anomaly [Degrees] (line 2, field 7) More...

double	mean_motion
	Mean Motion [Revs per day] (line 2, field 8) More...

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

double	second_derivative_mean_motion
	Second Time Derivative of Mean Motion divided by six (line 1, field 10) More...

double	bstar_drag_term
	BSTAR drag term (decimal point assumed, line 1, field 11) More...

int	revolutions_at_epoch
	Number of revolutions around Earth at epoch (line 2, field 9) More...

enum predict_ephemeris	ephemeris
	Which perturbation model to use. More...

void *	ephemeris_data
	Ephemeris data structure pointer. More...

Detailed Description

Container for processed TLE data from TLE strings.

Field Documentation

double predict_orbital_elements_t::argument_of_perigee

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

double predict_orbital_elements_t::bstar_drag_term

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

double predict_orbital_elements_t::derivative_mean_motion

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

char predict_orbital_elements_t::designator[10]

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

double predict_orbital_elements_t::eccentricity

Eccentricity (line 2, field 5)

long predict_orbital_elements_t::element_number

Element number (line 1, field 13)

enum predict_ephemeris predict_orbital_elements_t::ephemeris

Which perturbation model to use.

void* predict_orbital_elements_t::ephemeris_data

Ephemeris data structure pointer.

double predict_orbital_elements_t::epoch_day

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

int predict_orbital_elements_t::epoch_year

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

double predict_orbital_elements_t::inclination

Inclination (line 2, field 3)

double predict_orbital_elements_t::mean_anomaly

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

double predict_orbital_elements_t::mean_motion

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

int predict_orbital_elements_t::revolutions_at_epoch

Number of revolutions around Earth at epoch (line 2, field 9)

double predict_orbital_elements_t::right_ascension

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

int predict_orbital_elements_t::satellite_number

Satellite number (line 1, field 2)

double predict_orbital_elements_t::second_derivative_mean_motion

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

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