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Modify celestial rotation to suit coding rule #501

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Oct 4, 2023
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Modify celestial rotation to suit coding rule #501

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b654127
Fix argument name to suit the coding rule
200km Sep 27, 2023
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Add doxygen comment
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146 changes: 73 additions & 73 deletions src/environment/global/celestial_rotation.cpp
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Expand Up @@ -53,7 +53,7 @@ void CelestialRotation::InitCelestialRotationAsEarth(const RotationMode rotation
c_epsilon_rad_[2] = -5.9000e-4 * libra::arcsec_to_rad; // [rad/century^2]
c_epsilon_rad_[3] = 1.8130e-3 * libra::arcsec_to_rad; // [rad/century^3]

// Coefficients to compute delauney angles
// Coefficients to compute Delaunay angles
// The actual unit of the coefficients are [rad/century^i], where i is the index of the array
c_lm_rad_[0] = 134.96340251 * libra::deg_to_rad; // [rad]
c_lm_rad_[1] = 1717915923.21780000 * libra::arcsec_to_rad; // [rad/century]
Expand Down Expand Up @@ -131,40 +131,40 @@ void CelestialRotation::InitCelestialRotationAsEarth(const RotationMode rotation
}
}

void CelestialRotation::Update(const double JulianDate) {
double gmst_rad = gstime(JulianDate); // It is a bit different with 長沢(Nagasawa)'s algorithm. TODO: Check the correctness
void CelestialRotation::Update(const double julian_date) {
double gmst_rad = gstime(julian_date); // It is a bit different with 長沢(Nagasawa)'s algorithm. TODO: Check the correctness

if (rotation_mode_ == RotationMode::kFull) {
// Compute Julian date for terrestrial time
double jdTT_day = JulianDate + kDtUt1Utc_ * kSec2Day_; // TODO: Check the correctness. Problem is that S2E doesn't have Gregorian calendar.
double terrestrial_time_julian_day = julian_date + kDtUt1Utc_ * kSec2Day_; // TODO: Check the correctness. Problem is that S2E doesn't have Gregorian calendar.

// Compute nth power of julian century for terrestrial time the actual unit of tTT_century is [century^(i+1)], i is the index of the array
double tTT_century[4];
tTT_century[0] = (jdTT_day - kJulianDateJ2000_) / kDayJulianCentury_;
// Compute nth power of julian century for terrestrial time.
// The actual unit of tTT_century is [century^(i+1)], i is the index of the array
double terrestrial_time_julian_century[4];
terrestrial_time_julian_century[0] = (terrestrial_time_julian_day - kJulianDateJ2000_) / kDayJulianCentury_;
for (int i = 0; i < 3; i++) {
tTT_century[i + 1] = tTT_century[i] * tTT_century[0];
terrestrial_time_julian_century[i + 1] = terrestrial_time_julian_century[i] * terrestrial_time_julian_century[0];
}

libra::Matrix<3, 3> P;
libra::Matrix<3, 3> N;
libra::Matrix<3, 3> R;
libra::Matrix<3, 3> W;
libra::Matrix<3, 3> dcm_precession;
libra::Matrix<3, 3> dcm_nutation;
libra::Matrix<3, 3> dcm_rotation;
libra::Matrix<3, 3> dcm_polar_motion;
// Nutation + Precession
P = Precession(tTT_century);
N = Nutation(tTT_century); // epsilon_rad_, d_epsilon_rad_, d_psi_rad_ are
// updated in this procedure
dcm_precession = Precession(terrestrial_time_julian_century);
dcm_nutation = Nutation(terrestrial_time_julian_century); // epsilon_rad_, d_epsilon_rad_, d_psi_rad_ are updated in this procedure

// Axial Rotation
double Eq_rad = d_psi_rad_ * cos(epsilon_rad_ + d_epsilon_rad_); // Equation of equinoxes [rad]
double gast_rad = gmst_rad + Eq_rad; // Greenwitch 'Apparent' Sidereal Time [rad]
R = AxialRotation(gast_rad);
double equinox_rad = d_psi_rad_ * cos(epsilon_rad_ + d_epsilon_rad_); // Equation of equinoxes [rad]
double gast_rad = gmst_rad + equinox_rad; // Greenwich 'Apparent' Sidereal Time [rad]
dcm_rotation = AxialRotation(gast_rad);
// Polar motion (is not considered so far, even without polar motion, the result agrees well with the matlab reference)
double Xp = 0.0;
double Yp = 0.0;
W = PolarMotion(Xp, Yp);
double x_p = 0.0;
double y_p = 0.0;
dcm_polar_motion = PolarMotion(x_p, y_p);

// Total orientation
dcm_j2000_to_xcxf_ = W * R * N * P;
dcm_j2000_to_xcxf_ = dcm_polar_motion * dcm_rotation * dcm_nutation * dcm_precession;
} else if (rotation_mode_ == RotationMode::kSimple) {
// In this case, only Axial Rotation is executed, with its argument replaced from G'A'ST to G'M'ST
// FIXME: Not suitable when the center body is not the earth
Expand All @@ -175,108 +175,108 @@ void CelestialRotation::Update(const double JulianDate) {
}
}

libra::Matrix<3, 3> CelestialRotation::AxialRotation(const double GAST_rad) { return libra::MakeRotationMatrixZ(GAST_rad); }
libra::Matrix<3, 3> CelestialRotation::AxialRotation(const double gast_rad) { return libra::MakeRotationMatrixZ(gast_rad); }

libra::Matrix<3, 3> CelestialRotation::Nutation(const double (&tTT_century)[4]) {
libra::Matrix<3, 3> CelestialRotation::Nutation(const double (&t_tt_century)[4]) {
// Mean obliquity of the ecliptic
epsilon_rad_ = c_epsilon_rad_[0];
for (int i = 0; i < 3; i++) {
epsilon_rad_ += c_epsilon_rad_[i + 1] * tTT_century[i];
epsilon_rad_ += c_epsilon_rad_[i + 1] * t_tt_century[i];
}

// Compute five delauney angles(l=lm,l'=ls,F,D,Ω=O)
// Compute five Delaunay angles(l=lm, l'=ls, F, D, Ω=O)
// Mean anomaly of the moon
double lm_rad = c_lm_rad_[0];
for (int i = 0; i < 4; i++) {
lm_rad += c_lm_rad_[i + 1] * tTT_century[i];
lm_rad += c_lm_rad_[i + 1] * t_tt_century[i];
}
// Mean anomaly of the sun
double ls_rad = c_ls_rad_[0];
for (int i = 0; i < 4; i++) {
ls_rad += c_ls_rad_[i + 1] * tTT_century[i];
ls_rad += c_ls_rad_[i + 1] * t_tt_century[i];
}
// Mean longitude of the moon - mean longitude of ascending node of the moon
double F_rad = c_f_rad_[0];
double f_rad = c_f_rad_[0];
for (int i = 0; i < 4; i++) {
F_rad += c_f_rad_[i + 1] * tTT_century[i];
f_rad += c_f_rad_[i + 1] * t_tt_century[i];
}
// Mean elogation of the moon from the sun
double D_rad = c_d_rad_[0];
// Mean elongation of the moon from the sun
double d_rad = c_d_rad_[0];
for (int i = 0; i < 4; i++) {
D_rad += c_d_rad_[i + 1] * tTT_century[i];
d_rad += c_d_rad_[i + 1] * t_tt_century[i];
}
// Mean longitude of ascending node of the moon
double O_rad = c_o_rad_[0];
double o_rad = c_o_rad_[0];
for (int i = 0; i < 4; i++) {
O_rad += c_o_rad_[i + 1] * tTT_century[i];
o_rad += c_o_rad_[i + 1] * t_tt_century[i];
}

// Additional angles
double L_rad = F_rad + O_rad; // F + Ω [rad]
double Ld_rad = L_rad - D_rad; // F - D + Ω [rad]
double l_rad = f_rad + o_rad; // F + Ω
double ld_rad = l_rad - d_rad; // F + Ω - D

// Compute luni-solar nutation
// Nutation in obliquity
d_psi_rad_ = c_d_psi_rad_[0] * sin(O_rad) + c_d_psi_rad_[1] * sin(2 * Ld_rad) + c_d_psi_rad_[2] * sin(2 * O_rad) +
c_d_psi_rad_[3] * sin(2 * L_rad) + c_d_psi_rad_[4] * sin(ls_rad); // [rad]
d_psi_rad_ = d_psi_rad_ + c_d_psi_rad_[5] * sin(lm_rad) + c_d_psi_rad_[6] * sin(2 * Ld_rad + ls_rad) + c_d_psi_rad_[7] * sin(2 * L_rad + lm_rad) +
c_d_psi_rad_[8] * sin(2 * Ld_rad - ls_rad); // [rad]
d_psi_rad_ = c_d_psi_rad_[0] * sin(o_rad) + c_d_psi_rad_[1] * sin(2 * ld_rad) + c_d_psi_rad_[2] * sin(2 * o_rad) +
c_d_psi_rad_[3] * sin(2 * l_rad) + c_d_psi_rad_[4] * sin(ls_rad);
d_psi_rad_ = d_psi_rad_ + c_d_psi_rad_[5] * sin(lm_rad) + c_d_psi_rad_[6] * sin(2 * ld_rad + ls_rad) + c_d_psi_rad_[7] * sin(2 * l_rad + lm_rad) +
c_d_psi_rad_[8] * sin(2 * ld_rad - ls_rad);

// Nutation in longitude
d_epsilon_rad_ = c_d_epsilon_rad_[0] * cos(O_rad) + c_d_epsilon_rad_[1] * cos(2 * Ld_rad) + c_d_epsilon_rad_[2] * cos(2 * O_rad) +
c_d_epsilon_rad_[3] * cos(2 * L_rad) + c_d_epsilon_rad_[4] * cos(ls_rad); // [rad]
d_epsilon_rad_ = d_epsilon_rad_ + c_d_epsilon_rad_[5] * cos(lm_rad) + c_d_epsilon_rad_[6] * cos(2 * Ld_rad + ls_rad) +
c_d_epsilon_rad_[7] * cos(2 * L_rad + lm_rad) + c_d_epsilon_rad_[8] * cos(2 * Ld_rad - ls_rad); // [rad]
d_epsilon_rad_ = c_d_epsilon_rad_[0] * cos(o_rad) + c_d_epsilon_rad_[1] * cos(2 * ld_rad) + c_d_epsilon_rad_[2] * cos(2 * o_rad) +
c_d_epsilon_rad_[3] * cos(2 * l_rad) + c_d_epsilon_rad_[4] * cos(ls_rad);
d_epsilon_rad_ = d_epsilon_rad_ + c_d_epsilon_rad_[5] * cos(lm_rad) + c_d_epsilon_rad_[6] * cos(2 * ld_rad + ls_rad) +
c_d_epsilon_rad_[7] * cos(2 * l_rad + lm_rad) + c_d_epsilon_rad_[8] * cos(2 * ld_rad - ls_rad);

double epsi_mod_rad = epsilon_rad_ + d_epsilon_rad_;
libra::Matrix<3, 3> X_epsi_1st = libra::MakeRotationMatrixX(epsilon_rad_);
libra::Matrix<3, 3> Z_dpsi = libra::MakeRotationMatrixZ(-d_psi_rad_);
libra::Matrix<3, 3> X_epsi_2nd = libra::MakeRotationMatrixX(-epsi_mod_rad);
libra::Matrix<3, 3> x_epsi_1st = libra::MakeRotationMatrixX(epsilon_rad_);
libra::Matrix<3, 3> z_d_psi = libra::MakeRotationMatrixZ(-d_psi_rad_);
libra::Matrix<3, 3> x_epsi_2nd = libra::MakeRotationMatrixX(-epsi_mod_rad);

libra::Matrix<3, 3> N;
N = X_epsi_2nd * Z_dpsi * X_epsi_1st;
libra::Matrix<3, 3> dcm_nutation;
dcm_nutation = x_epsi_2nd * z_d_psi * x_epsi_1st;

return N;
return dcm_nutation;
}

libra::Matrix<3, 3> CelestialRotation::Precession(const double (&tTT_century)[4]) {
libra::Matrix<3, 3> CelestialRotation::Precession(const double (&t_tt_century)[4]) {
// Compute precession angles(zeta, theta, z)
double zeta_rad = 0.0;
for (int i = 0; i < 3; i++) {
zeta_rad += c_zeta_rad_[i] * tTT_century[i];
zeta_rad += c_zeta_rad_[i] * t_tt_century[i];
}
double theta_rad = 0.0;
for (int i = 0; i < 3; i++) {
theta_rad += c_theta_rad_[i] * tTT_century[i];
theta_rad += c_theta_rad_[i] * t_tt_century[i];
}
double z_rad = 0.0;
for (int i = 0; i < 3; i++) {
z_rad += c_z_rad_[i] * tTT_century[i];
z_rad += c_z_rad_[i] * t_tt_century[i];
}

// Develop transformation matrix
libra::Matrix<3, 3> Z_zeta = libra::MakeRotationMatrixZ(-zeta_rad);
libra::Matrix<3, 3> Y_theta = libra::MakeRotationMatrixY(theta_rad);
libra::Matrix<3, 3> Z_z = libra::MakeRotationMatrixZ(-z_rad);
libra::Matrix<3, 3> z_zeta = libra::MakeRotationMatrixZ(-zeta_rad);
libra::Matrix<3, 3> y_theta = libra::MakeRotationMatrixY(theta_rad);
libra::Matrix<3, 3> z_z = libra::MakeRotationMatrixZ(-z_rad);

libra::Matrix<3, 3> P;
P = Z_z * Y_theta * Z_zeta;
libra::Matrix<3, 3> dcm_precession;
dcm_precession = z_z * y_theta * z_zeta;

return P;
return dcm_precession;
}

libra::Matrix<3, 3> CelestialRotation::PolarMotion(const double Xp, const double Yp) {
libra::Matrix<3, 3> W;
libra::Matrix<3, 3> CelestialRotation::PolarMotion(const double x_p, const double y_p) {
libra::Matrix<3, 3> dcm_polar_motion;

W[0][0] = 1.0;
W[0][1] = 0.0;
W[0][2] = -Xp;
W[1][0] = 0.0;
W[1][1] = 1.0;
W[1][2] = -Yp;
W[2][0] = Xp;
W[2][1] = Yp;
W[2][2] = 1.0;
dcm_polar_motion[0][0] = 1.0;
dcm_polar_motion[0][1] = 0.0;
dcm_polar_motion[0][2] = -x_p;
dcm_polar_motion[1][0] = 0.0;
dcm_polar_motion[1][1] = 1.0;
dcm_polar_motion[1][2] = -y_p;
dcm_polar_motion[2][0] = x_p;
dcm_polar_motion[2][1] = y_p;
dcm_polar_motion[2][2] = 1.0;

return W;
return dcm_polar_motion;
}
48 changes: 36 additions & 12 deletions src/environment/global/celestial_rotation.hpp
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Original file line number Diff line number Diff line change
Expand Up @@ -42,9 +42,9 @@ class CelestialRotation {
/**
* @fn Update
* @brief Update rotation
* @param [in] JulianDate: Julian date
* @param [in] julian_date: Julian date
*/
void Update(const double JulianDate);
void Update(const double julian_date);

/**
* @fn GetDcmJ2000ToXcxf
Expand Down Expand Up @@ -72,11 +72,11 @@ class CelestialRotation {
// TODO: Consider to read setting files for these coefficients
// TODO: Consider other formats for other planets
double c_epsilon_rad_[4]; //!< Coefficients to compute mean obliquity of the ecliptic
double c_lm_rad_[5]; //!< Coefficients to compute delauney angle (l=lm: Mean anomaly of the moon)
double c_ls_rad_[5]; //!< Coefficients to compute delauney angle (l'=ls: Mean anomaly of the sun)
double c_f_rad_[5]; //!< Coefficients to compute delauney angle (F: Mean longitude of the moon - mean longitude of ascending node of the moon)
double c_d_rad_[5]; //!< Coefficients to compute delauney angle (D: Elogation of the moon from the sun)
double c_o_rad_[5]; //!< Coefficients to compute delauney angle (Ω=O: Mean longitude of ascending node of the moon)
double c_lm_rad_[5]; //!< Coefficients to compute Delaunay angle (l=lm: Mean anomaly of the moon)
double c_ls_rad_[5]; //!< Coefficients to compute Delaunay angle (l'=ls: Mean anomaly of the sun)
double c_f_rad_[5]; //!< Coefficients to compute Delaunay angle (F: Mean longitude of the moon - mean longitude of ascending node of the moon)
double c_d_rad_[5]; //!< Coefficients to compute Delaunay angle (D: Elongation of the moon from the sun)
double c_o_rad_[5]; //!< Coefficients to compute Delaunay angle (Ω=O: Mean longitude of ascending node of the moon)
double c_d_epsilon_rad_[9]; //!< Coefficients to compute nutation angle (delta-epsilon)
double c_d_psi_rad_[9]; //!< Coefficients to compute nutation angle (delta-psi)
double c_zeta_rad_[3]; //!< Coefficients to compute precession angle (zeta)
Expand All @@ -98,12 +98,36 @@ class CelestialRotation {
*/
void InitCelestialRotationAsEarth(const RotationMode rotation_mode, const std::string center_body_name);

// TODO: Add doxygen comments for the private functions and fix argument name
/**
* @fn AxialRotation
* @brief Calculate movement of the coordinate axes due to rotation around the rotation axis
* @param [in] gast_rad: Greenwich 'Apparent' Sidereal Time [rad]
* @return Rotation matrix
*/
libra::Matrix<3, 3> AxialRotation(const double gast_rad);

/**
* @fn Nutation
* @brief Calculate movement of the coordinate axes due to Nutation
* @param [in] t_tt_century: nth power of julian century for terrestrial time
* @return Rotation matrix
*/
libra::Matrix<3, 3> Nutation(const double (&t_tt_century)[4]);

libra::Matrix<3, 3> AxialRotation(const double GAST_rad); //!< Movement of the coordinate axes due to rotation around the rotation axis
libra::Matrix<3, 3> Nutation(const double (&tTT_century)[4]); //!< Movement of the coordinate axes due to Nutation
libra::Matrix<3, 3> Precession(const double (&tTT_century)[4]); //!< Movement of the coordinate axes due to Precession
libra::Matrix<3, 3> PolarMotion(const double Xp, const double Yp); //!< Movement of the coordinate axes due to Polar Motion
/**
* @fn Precession
* @brief Calculate movement of the coordinate axes due to Precession
* @param [in] t_tt_century: nth power of julian century for terrestrial time
* @return Rotation matrix
*/
libra::Matrix<3, 3> Precession(const double (&t_tt_century)[4]);

/**
* @fn PolarMotion
* @brief Calculate movement of the coordinate axes due to Polar Motion
* @note Currently, this function is not used.
*/
libra::Matrix<3, 3> PolarMotion(const double x_p, const double y_p);
};

#endif // S2E_ENVIRONMENT_GLOBAL_CELESTIAL_ROTATION_HPP_