Mechanization.hpp

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// This file is part of INSTINCT, the INS Toolkit for Integrated
// Navigation Concepts and Training by the Institute of Navigation of
// the University of Stuttgart, Germany.
//
// This Source Code Form is subject to the terms of the Mozilla Public
// License, v. 2.0. If a copy of the MPL was not distributed with this
// file, You can obtain one at https://mozilla.org/MPL/2.0/.

 
#pragma once
 
#include "Navigation/Gravity/Gravity.hpp"
 
#include <Eigen/Core>
#include <Eigen/Dense>
 
#include "Navigation/Constants.hpp"
#include "Navigation/Ellipsoid/Ellipsoid.hpp"
#include "Navigation/INS/Functions.hpp"
#include "Navigation/INS/Mechanization.hpp"
#include "Navigation/Math/Math.hpp"
#include "Navigation/Transformations/CoordinateFrames.hpp"
#include "util/Logger.hpp"
 
#include <cmath>
 
namespace NAV
{
template<typename DerivedA, typename DerivedB>
Eigen::Vector4<typename DerivedA::Scalar> calcTimeDerivativeFor_e_Quat_b(const Eigen::MatrixBase<DerivedA>& b_omega_eb,
                                                                         const Eigen::MatrixBase<DerivedB>& e_Quat_b_coeffs)
{
    using T = typename DerivedA::Scalar;
 
    // Angular rates in matrix form (Titterton (2005), eq. (11.35))
    Eigen::Matrix4<T> A;
 
    // clang-format off
    A <<     T(0.0)    ,  b_omega_eb(2), -b_omega_eb(1), b_omega_eb(0),
         -b_omega_eb(2),     T(0.0)    ,  b_omega_eb(0), b_omega_eb(1),
          b_omega_eb(1), -b_omega_eb(0),     T(0.0)    , b_omega_eb(2),
         -b_omega_eb(0), -b_omega_eb(1), -b_omega_eb(2),    T(0.0)    ;
    // clang-format on
 
    // Propagation of an attitude Quaternion with time (Titterton, ch. 11.2.5, eq. 11.33-11.35, p. 319)
    return 0.5 * A * e_Quat_b_coeffs; // (x, y, z, w)
}

template<typename DerivedA, typename DerivedB, typename DerivedC, typename DerivedD>
Eigen::Vector3<typename DerivedA::Scalar> e_calcTimeDerivativeForVelocity(const Eigen::MatrixBase<DerivedA>& e_measuredForce,
                                                                          const Eigen::MatrixBase<DerivedB>& e_coriolisAcceleration,
                                                                          const Eigen::MatrixBase<DerivedC>& e_gravitation,
                                                                          const Eigen::MatrixBase<DerivedD>& e_centrifugalAcceleration)
{
    return e_measuredForce
           - e_coriolisAcceleration
           + e_gravitation
           - e_centrifugalAcceleration;
}

template<typename Derived>
Eigen::Vector3<typename Derived::Scalar> e_calcTimeDerivativeForPosition(const Eigen::MatrixBase<Derived>& e_velocity)
{
    return e_velocity;
}

template<typename T>
Eigen::Vector<T, 10> e_calcPosVelAttDerivative(const Eigen::Vector<T, 10>& y, const Eigen::Vector<T, 6>& z, const PosVelAttDerivativeConstants& c, double /* t */ = 0.0)
{
    //        0  1  2   3    4    5     6       7       8       9
    // ∂/∂t [ x, y, z, v_x, v_y, v_z, e_q_bx, e_q_by, e_q_bz, e_q_bw]^T
    Eigen::Vector<T, 10> y_dot = Eigen::Vector<T, 10>::Zero();
 
    Eigen::Vector3<T> lla_position = trafo::ecef2lla_WGS84(y.template segment<3>(0));
 
    Eigen::Quaternion<T> e_Quat_b{ y.template segment<4>(6) };
    e_Quat_b.normalize();
    Eigen::Quaternion<T> n_Quat_e = trafo::n_Quat_e(lla_position(0), lla_position(1));
 
    Eigen::Quaternion<T> b_Quat_e = e_Quat_b.conjugate();
    Eigen::Quaternion<T> e_Quat_n = n_Quat_e.conjugate();
 
    LOG_DATA("e_velocity   = {} [m/s]", y.template segment<3>(3).transpose());
    LOG_DATA("e_position = {} [m]", y.template segment<3>(0).transpose());
 
    // ω_eb_b = ω_ib_b - C_be * ω_ie_e
    Eigen::Vector3<T> b_omega_eb = z.template segment<3>(3)
                                   - b_Quat_e * (c.angularRateEarthRotationCompensationEnabled ? InsConst::e_omega_ie : Eigen::Vector3d::Zero()).template cast<T>();
    LOG_DATA("b_omega_eb = {} [rad/s]", b_omega_eb.transpose());
 
    // Coriolis acceleration in [m/s^2] (acceleration due to motion in rotating reference frame)
    Eigen::Vector3<T> e_coriolisAcceleration = c.coriolisAccelerationCompensationEnabled
                                                   ? e_calcCoriolisAcceleration(InsConst::e_omega_ie, y.template segment<3>(3))
                                                   : Eigen::Vector3<T>::Zero();
    LOG_DATA("e_coriolisAcceleration = {} [m/s^2]", e_coriolisAcceleration.transpose());
    // Centrifugal acceleration in [m/s^2] (acceleration that makes a body follow a curved path)
    Eigen::Vector3<T> e_centrifugalAcceleration = c.centrifgalAccelerationCompensationEnabled
                                                      ? e_calcCentrifugalAcceleration(y.template segment<3>(0), InsConst::e_omega_ie)
                                                      : Eigen::Vector3<T>::Zero();
    LOG_DATA("e_centrifugalAcceleration = {} [m/s^2]", e_centrifugalAcceleration.transpose());
 
    Eigen::Vector3<T> e_gravitation = e_Quat_n * n_calcGravitation(lla_position, c.gravitationModel);
    LOG_DATA("e_gravitation = {} [m/s^2] ({})", e_gravitation.transpose(), to_string(c.gravitationModel));
 
    y_dot.template segment<3>(0) = e_calcTimeDerivativeForPosition(y.template segment<3>(3)); // Velocity with respect to the Earth in ECEF frame coordinates [m/s]
 
    y_dot.template segment<3>(3) = e_calcTimeDerivativeForVelocity(e_Quat_b * z.template segment<3>(0), // f_n Specific force vector as measured by a triad of accelerometers and resolved into ECEF frame coordinates
                                                                   e_coriolisAcceleration,              // Coriolis acceleration in ECEF coordinates in [m/s^2]
                                                                   e_gravitation,                       // Local gravitation vector (caused by effects of mass attraction) in ECEF frame coordinates [m/s^2]
                                                                   e_centrifugalAcceleration);          // Centrifugal acceleration in ECEF coordinates in [m/s^2]
 
    y_dot.template segment<4>(6) = calcTimeDerivativeFor_e_Quat_b(b_omega_eb,                // ω_eb_b Body rate with respect to the ECEF frame, expressed in the body frame
                                                                  y.template segment<4>(6)); // e_Quat_b_coeffs Coefficients of the quaternion e_Quat_b
 
    LOG_DATA("e_position_dot = {} [m/s]", y_dot.template segment<3>(0).transpose());
    LOG_DATA("e_velocity_dot = {} [m/s^2]", y_dot.template segment<3>(3).transpose());
    LOG_DATA("e_Quat_b_dot = {} ", y_dot.template segment<4>(6).transpose());
 
    return y_dot;
}
 
} // namespace NAV