int main(){
V6 v6;
v6 = v6init(SPHERICAL);
v6SetR(v6, 1.0);
v6SetAlpha(v6, M_PI/4.0);
v6SetDelta(v6, M_PI/4.0);
v6 = v6s2c(v6);
v6SetXDot(v6, -0.034);
v6SetYDot(v6, -0.12);
v6SetZDot(v6, -0.9);
v6 = ecl2equ(v6, d2r(23.7));
printf("X %.9f \tY %.9f \tZ %.9f \nXDOT %.9f \tYDOT %.9f \tZDOT %.9f\n",
v6GetX(v6), v6GetY(v6), v6GetZ(v6), v6GetXDot(v6),
v6GetYDot(v6), v6GetZDot(v6));
return 0;
}
/*
* calc_moon_internal:
* @info: WeatherInfo containing time_t of interest. The
* values moonphase, moonlatitude and moonValid are updated
* on success.
*
* Returns: gboolean indicating success or failure.
* moonphase is expressed as degrees where '0' is a new moon,
* '90' is first quarter, etc.
*/
static gboolean
calc_moon_internal (time_t update, gdouble *moonphase, gdouble *moonlatitude)
{
time_t t;
gdouble ra_h;
gdouble decl_r;
gdouble ndays, sunMeanAnom_d;
gdouble moonLong_d;
gdouble moonMeanAnom_d, moonMeanAnom_r;
gdouble sunEclipLong_r;
gdouble ascNodeMeanLong_d;
gdouble corrLong_d, eviction_d;
gdouble sinSunMeanAnom;
gdouble Ae, A3, Ec, A4, lN_r;
gdouble lambda_r, beta_r;
/*
* The comments refer to the enumerated steps to calculate the
* position of the moon (section 65 of above reference)
*/
t = update;
ndays = EPOCH_TO_J2000(t) / 86400.;
sunMeanAnom_d = fmod (MEAN_ECLIPTIC_LONGITUDE (ndays) - PERIGEE_LONGITUDE (ndays),
360.);
sunEclipLong_r = sunEclipLongitude (t);
moonLong_d = fmod (LUNAR_MEAN_LONGITUDE + (ndays * LUNAR_PROGRESSION),
360.);
/* 5: moon's mean anomaly */
moonMeanAnom_d = fmod ((moonLong_d - (0.1114041 * ndays)
- (LUNAR_PERIGEE_MEAN_LONG + LUNAR_NODE_MEAN_LONG)),
360.);
/* 6: ascending node mean longitude */
ascNodeMeanLong_d = fmod (LUNAR_NODE_MEAN_LONG - (0.0529539 * ndays),
360.);
eviction_d = 1.2739 /* 7: eviction */
* sin (DEGREES_TO_RADIANS (2.0 * (moonLong_d - RADIANS_TO_DEGREES (sunEclipLong_r))
- moonMeanAnom_d));
sinSunMeanAnom = sin (DEGREES_TO_RADIANS (sunMeanAnom_d));
Ae = 0.1858 * sinSunMeanAnom;
A3 = 0.37 * sinSunMeanAnom; /* 8: annual equation */
moonMeanAnom_d += eviction_d - Ae - A3; /* 9: "third correction" */
moonMeanAnom_r = DEGREES_TO_RADIANS (moonMeanAnom_d);
Ec = 6.2886 * sin (moonMeanAnom_r); /* 10: equation of center */
A4 = 0.214 * sin (2.0 * moonMeanAnom_r); /* 11: "yet another correction" */
/* Steps 12-14 give the true longitude after correcting for variation */
moonLong_d += eviction_d + Ec - Ae + A4
+ (0.6583 * sin (2.0 * (moonMeanAnom_r - sunEclipLong_r)));
/* 15: corrected longitude of node */
corrLong_d = ascNodeMeanLong_d - 0.16 * sinSunMeanAnom;
/*
* Calculate ecliptic latitude (16-19) and longitude (20) of the moon,
* then convert to right ascension and declination.
*/
lN_r = DEGREES_TO_RADIANS (moonLong_d - corrLong_d); /* l''-N' */
lambda_r = DEGREES_TO_RADIANS(corrLong_d)
+ atan2 (sin (lN_r) * cos (LUNAR_INCLINATION), cos (lN_r));
beta_r = asin (sin (lN_r) * sin (LUNAR_INCLINATION));
ecl2equ (t, lambda_r, beta_r, &ra_h, &decl_r);
/*
* The phase is the angle from the sun's longitude to the moon's
*/
*moonphase =
fmod (15.*ra_h - RADIANS_TO_DEGREES (sunEclipLongitude (update)),
360.);
if (*moonphase < 0)
*moonphase += 360;
*moonlatitude = RADIANS_TO_DEGREES (decl_r);
return TRUE;
}
/// Implementation of the objective function.
void tandem::objfun_impl(fitness_vector &f, const decision_vector &x) const
{
if (tof!=-1) { //constrained problem
//Here we copy the chromosome into a new vector and we transform its time percentages into days
copy_of_x = x;
copy_of_x[4] = x[4]*365.25*tof;
copy_of_x[5] = x[5]*(365.25*tof-copy_of_x[4]);
copy_of_x[6] = x[6]*(365.25*tof-copy_of_x[4]-copy_of_x[5]);
copy_of_x[7] = x[7]*(365.25*tof-copy_of_x[4]-copy_of_x[5]-copy_of_x[6]);
MGA_DSM(copy_of_x, problem, f[0]);
} else { //unconstrained problem
MGA_DSM(x, problem, f[0]);
}
//evaluating the mass from the dvs
double rE[3];
double vE[3];
Planet_Ephemerides_Analytical (x[0],3,rE,vE);
double VINFE = x[1];
double udir = x[2];
double vdir = x[3];
double vtemp[3];
vtemp[0]= rE[1]*vE[2]-rE[2]*vE[1];
vtemp[1]= rE[2]*vE[0]-rE[0]*vE[2];
vtemp[2]= rE[0]*vE[1]-rE[1]*vE[0];
double iP1[3];
double normvE=sqrt(vE[0]*vE[0]+vE[1]*vE[1]+vE[2]*vE[2]);
iP1[0]= vE[0]/normvE;
iP1[1]= vE[1]/normvE;
iP1[2]= vE[2]/normvE;
double zP1[3];
double normvtemp=sqrt(vtemp[0]*vtemp[0]+vtemp[1]*vtemp[1]+vtemp[2]*vtemp[2]);
zP1[0]= vtemp[0]/normvtemp;
zP1[1]= vtemp[1]/normvtemp;
zP1[2]= vtemp[2]/normvtemp;
double jP1[3];
jP1[0]= zP1[1]*iP1[2]-zP1[2]*iP1[1];
jP1[1]= zP1[2]*iP1[0]-zP1[0]*iP1[2];
jP1[2]= zP1[0]*iP1[1]-zP1[1]*iP1[0];
double theta=2*M_PI*udir; //See Picking a Point on a Sphere
double phi=acos(2*vdir-1)-M_PI/2; //In this way: -pi/2<phi<pi/2 so phi can be used as out-of-plane rotation
double vinf[3];
vinf[0]=VINFE*(cos(theta)*cos(phi)*iP1[0]+sin(theta)*cos(phi)*jP1[0]+sin(phi)*zP1[0]);
vinf[1]=VINFE*(cos(theta)*cos(phi)*iP1[1]+sin(theta)*cos(phi)*jP1[1]+sin(phi)*zP1[1]);
vinf[2]=VINFE*(cos(theta)*cos(phi)*iP1[2]+sin(theta)*cos(phi)*jP1[2]+sin(phi)*zP1[2]);
//We rotate it to the equatorial plane
ecl2equ(vinf,vinf);
//And we find the declination in degrees
double normvinf=sqrt(vinf[0]*vinf[0]+vinf[1]*vinf[1]+vinf[2]*vinf[2]);
double sindelta = vinf[2] / normvinf;
double declination = asin(sindelta)/M_PI*180;
//double m_initial = SoyuzFregat(VINFE,declination);
double m_initial = Atlas501(VINFE,declination);
//We evaluate the final mass
double Isp = 312;
double g0 = 9.80665;
double sumDVvec=0;
for(unsigned int i=1;i<=5;i++) {
sumDVvec=sumDVvec+problem.DV[i];
}
double m_final;
sumDVvec=sumDVvec+0.165; //losses for 3 swgbys + insertion
m_final = m_initial * exp(-sumDVvec/Isp/g0*1000);
f[0] = -log(m_final);
}
