sc_orbit.h

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/*
 * orbit.h 
 *
 * Programmers: Joe Mueller, Mike Paluszek, Stephanie Thomas, Wil Turner, Lavanya Swetharanyan
 *
 * Copyright 1999-2006, Princeton Satellite Systems. All rights reserved.
 *
 * Orbit functions. Primarily orbit mechanics.
 */
 
#ifndef __SC_ORBIT__
#define __SC_ORBIT__
 
#ifdef AS_OS_WINDOWS
#include "matrixlib.h"
#else
#include <MatrixLib/MatrixLib.h>
#endif
 
#include "sc_constants.h"
 
extern "C++"
{
 
typedef struct orb_data_s {
    double sma;                 
    double inc;                 
    double raan;                
    double perigee;             
    double ecc;                 
    double mean_anom;           
        double true_anom;           
    double orb_rate;            
    double epoch;               
} orb_data_t;
 
typedef struct gps_data_s {
    double tc;                  
    double a0;                  
    double a1;                  
    double a2;                  
    double te;                  
    double t0;                  
    double ecc;                 
    double sqrt_ax;             
    double m0;                  
    double w0;                  
    double i0;                  
    double l0;                  
    double delta_n;             
    double i_dot;               
    double omega_dot;           
    double cuc;                 
    double cus;                 
    double crc;                 
    double crs;                 
    double cic;                 
    double cis;                 
    double ta;                  
    double w;                   
    double delta_inc;           
    double dm_plane;            
    int satellite;              
    bool broadcast_ephem;       
} gps_data_t;   
                
typedef struct gps_orb_out_s {
        ml_matrix r;               
        ml_matrix v;               
        ml_matrix delta;           
} gps_orb_out_t;
    
    
typedef struct orbit_closest_point_out {
    ml_matrix r;            
    ml_matrix d;            
    ml_matrix julian_date;  
    ml_int_array id;        
} orbit_closest_point_out;
 
        
void el_to_rv(const orb_data_t &data, ml_matrix &pos, ml_matrix &vel);
void rv_to_nearest( const ml_matrix &pos, const ml_matrix &vel, const ml_matrix &pos_target, double jD, ml_matrix &distance, ml_matrix &time );
orb_data_t rv_to_el(const ml_matrix &pos,       const ml_matrix &vel, double mu=MU_EARTH);
double r_to_true(double a, double e, double r);
double rv_to_sma(double r_mag, double v_mag, double mu=MU_EARTH);
double mean_to_true(double ecc, double mean);
double mean_to_ecc(double ecc, double mean);
double ecc_to_true(double ecc, double e );
double ecc_to_mean(double ecc, double e );
double true_to_mean(double ecc, double nu);
double mean_to_true_abs(double ecc, double mean_anom);
double true_to_ecc(double ecc, double nu);
double rarp_to_ecc(double ap, double per);
double rarp_to_sma(double ap, double per);
double slr(double ecc, double sma);
ml_matrix cp_to_i(double inc, double raan, double w);
double orb_rate(double r, double a, double mu=MU_EARTH);
double orb_rate(double r);
double period(double a, double mu=MU_EARTH);
 
void lin_orb(double n, ml_matrix &a, ml_matrix &b, double dt);
void rv_orb_gen(const ml_matrix &el, const ml_matrix &t, ml_matrix &r, ml_matrix &v, double mu=MU_EARTH);
void rv_orb_gen(const orb_data_t &el, const ml_matrix &t, ml_matrix &r, ml_matrix &v, double mu=MU_EARTH);
ml_matrix cart_orb_rhs(const ml_matrix &x);
ml_matrix cart_orb_rhs(const ml_matrix &x, const ml_matrix &a);
 
ml_matrix satellite_visibility(const ml_matrix &from_pos, const ml_matrix &targets, double horizon_angle, double radius);
 
ml_matrix planetary_accelerations(const ml_matrix &pos, double jd, int center);
    
ml_matrix acc_planet(const ml_matrix &pos, double mu, const ml_matrix &rho);
 
ml_matrix orbit_acquisition_dv(ml_matrix &t, const orb_data_t &elI, const orb_data_t &elF, double smaTol = 0.5, double incTol = 1e-3, double raTol=1e-3);
        
double phase_change_dv(double a0, double deltaA, double kTarget, double mu );
    
ml_matrix circular_maneuver( double p, double r, double m );
        
ml_matrix gps_satellite( double jD );
    
orbit_closest_point_out orbit_closest_point( const ml_matrix &r_ef_target, const ml_int_array &t_target, const orb_data_s &el, int n_points = 1000, int n_orbits = 1 );
 
ml_matrix   r_ef_from_el( const orb_data_t &el, int n_points = 1000, int n_orbits = 1 );
    
ml_matrix gps_eci_state_from_data( double longitude, double latitude, double heading, double velocity, double altitude, double jd );
 
void print_orbit_data(orb_data_s orbData);
}
 
#endif