9.3 Include File: HD_reference.h
/***********************************************************************
*
* FILE NAME: HD_reference.h
*
*
* PURPOSE: Defines all reference data variables.
*
*
* GLOBAL VARIABLES:
*
* Variables Type Description
* ------------- -------- ---------------------------
* e_pos double[3] S/C to Earth unit vector
*
* ephem_file_lu long FORTRAN logical unit number
* for the ephemeris file
*
* ephem_file_name char[30] Name of the ephemeris file
*
* ephem_method char Method for computing
* ephemeris information:
* F = Use ephemeris file
* A = Compute analytically
* using Keplerian
* elements
*
* keplerian double[6] Keplerian orbital elements
* at the epoch time
* (orbital_t_epoch):
* [1] Semimajor axis [km]
* [2] Eccentricity
* [3] Inclination [rad]
* [4] Right ascension of
* the ascending node
* [rad]
* [5] Argument of perigee
* [rad]
* [6] Mean anomaly [rad]
*
* m_order long Order of magnetic field
*
* m_pos double[3] S/C to Moon unit vector
*
* mag_field double[3] Earth magnetic field vector
* [mG]
*
* mag_field_unit double[3] Earth magnetic field unit
* vector
*
* maxit long Maximum number of
* iterations to converge
* the true anomaly
*
* MU_E double Earth gravitational
* constant [km^3/sec^2]
*
* NUMPTS int Number of points used by
* the EPHEMRD interpolator
*
* orbit_normal double[3] Orbit normal unit vector
*
* orbital_t_epoch double Base epoch time of the
* orbital elements [sec]
*
* s_c_pos double[3] S/C position vector [km]
*
* s_c_vel double[3] S/C velocity vector
* [km/sec]
*
* s_pos double[3] S/C to Sun unit vector
*
* t_b_ref double Time of last calculated
* Earth magnetic field
* vector [sec]
*
* t_e_ref double Time of last calculated s/c
* to Earth unit vector
* [sec]
*
* t_m_ref double Time of last calculated s/c
* to Moon unit vector [sec]
*
* t_o_ref double Time of last calculated
* orbit normal unit vector
* [sec]
*
* t_rv_ref double Time of last calculated s/c
* position and velocity
* vectors[sec]
*
* t_s_ref double Time of last calculated s/c
* to Sun unit vector [sec]
*
* THREEB double Gravitational constant of
* perturbations [Km^2]
*
* ttol double Tolerance in the
* calculations of the true
* anomaly [rad]
*
*
* DEVELOPMENT HISTORY:
*
* Date Author Change Release Description of Change
* ID
* -------- ------------- ------ ------- ------------------------
* 09-23-93 J. Programmer 1 Prolog and PDL
* 10-07-93 J. Programmer 1 Controlled
* 12-02-93 J. Programmer 1 Integrated new RSL routines
* 12-17-93 J. Programmer 2 Added maxit and ttol;
* added MU_E and THREEB
* as #defines
* 04-06-94 J. Programmer 27 3 Corrected the THREEB value
* 05-10-94 J. Programmer 3 Added ephemeris read
capability
*
*
***********************************************************************/
#define MU_E 398600.8
#define THREEB 66042.0
#define NUMPTS 4
extern long ephem_file_lu;
extern double e_pos[3];
extern char ephem_file_name[30];
extern char ephem_method;
extern double keplerian[6];
extern long m_order;
extern double m_pos[3];
extern double mag_field[3];
extern double mag_field_unit[3];
extern long maxit;
extern double orbit_normal[3];
extern double orbital_t_epoch;
extern double s_c_pos[3];
extern double s_c_vel[3];
extern double s_pos[3];
extern double t_b_ref;
extern double t_e_ref;
extern double t_m_ref;
extern double t_o_ref;
extern double t_rv_ref;
extern double t_s_ref;
extern double ttol;