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Astro
0.0.0
A C++ library for space dynamics
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Astro
0.0.0
A C++ library for space dynamics
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Astronomical body class container. More...
#include <Body.hxx>
Inherits Astro::Orbit.
Public Member Functions | |
| Body () | |
| Body (Body const &)=default | |
| Body (Body &&)=default | |
| Body & | operator= (const Body &)=default |
| Body & | operator= (Body &&)=default |
| Real | mass () const |
| void | mass (Real t_mass) |
| MatrixA | equinoctial_eom_A () const |
| VectorB | equinoctial_eom_b () const |
| Vector6 | cartesian_eom (Vector3 const &thrust_rtn) const |
| Vector6 | cartesian_eom (Real thrust_rad, Real thrust_tan, Real thrust_nor) const |
| Vector6 | equinoctial_eom (Vector3 const &thrust) const |
| Vector6 | equinoctial_eom (Real thrust_rad, Real thrust_tan, Real thrust_nor) const |
 Public Member Functions inherited from Astro::Orbit | |
| Orbit () | |
| Orbit (Orbit const &)=default | |
| Orbit (Orbit &&)=default | |
| Orbit & | operator= (const Orbit &)=default |
| Orbit & | operator= (Orbit &&)=default |
| Cartesian const & | cartesian () const |
| void | set_cartesian (Real r_x, Real r_y, Real r_z, Real v_x, Real v_y, Real v_z) |
| void | cartesian (Vector3 const &t_r, Vector3 const &t_v) |
| void | cartesian (Cartesian const &t_cart) |
| Keplerian const & | keplerian () const |
| void | keplerian (Real t_a, Real t_e, Real t_i, Real t_Omega, Real t_omega) |
| void | keplerian (Keplerian const &t_kepl) |
| Equinoctial const & | equinoctial () const |
| void | set_equinoctial (Real t_p, Real t_f, Real t_g, Real t_h, Real t_k) |
| void | set_equinoctial (Equinoctial const &t_equi) |
| Quaternionic const & | quaternionic () const |
| void | set_quaternionic (Real t_q_1, Real t_q_2, Real t_q_3, Real t_q_4) |
| void | set_quaternionic (Quaternion const &t_quat) |
| Anomaly const & | anomaly () const |
| void | anomaly (Anomaly const &t_anom) |
| Type | type () const |
| void | type (Real e) |
| Factor | factor () const |
| void | factor (Factor t_factor) |
| Real | mu () const |
| void | mu (Real t_mu) |
| std::string | info () const |
| void | info (std::ostream &os) |
| void | reset () |
| Rotation | keplerian_to_reference () const |
| Rotation | equinoctial_to_reference () const |
| Rotation | cartesian_to_frenet_rtn () const |
| Rotation | equinoctial_to_frenet_rtn () const |
| Vector3 | cartesian_rtn_to_xyz (Vector3 const &vec) const |
| Vector3 | equinoctial_rtn_to_xyz (Vector3 const &vec) const |
| Vector3 | cartesian_xyz_to_rtn (Vector3 const &vec) const |
| Vector3 | equinoctial_xyz_to_rtn (Vector3 const &vec) const |
Private Types | |
| using | MatrixA = Eigen::Matrix<Real, 6, 3> |
| using | VectorB = Eigen::Vector<Real, 6> |
Private Attributes | |
| Real | m_mass {QUIET_NAN} |
Additional Inherited Members | |
| Protected Attributes inherited from Astro::Orbit | |
| Cartesian | m_cart |
| Keplerian | m_kepl |
| Equinoctial | m_equi |
| Quaternionic | m_quat |
| Anomaly | m_anom |
| Type | m_type {Type::UNDEFINED} |
| Factor | m_factor {Factor::UNDEFINED} |
| Real | m_mu {QUIET_NAN} |
The astronomical body class container is used to model the properties of an astronomical body in space. The class provides methods for setting and getting the mass of the body, as well as its orbit parameters.
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Matrix \( \mathbf{A} \in \mathbb{R}^{6 \times 3}\).
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Vector \( \mathbf{b} \in \mathbb{R}^{6 \times 1}\).
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Class constructor for the astronomical body object.
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default |
Enable the default astronomical body copy constructor.
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Enable the default astronomical body move constructor.
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Compute the vector of the first-order cartesian equations of orbital motion given the thrust vector components \( \mathbf{t} = [t_{\text{rad}}, t_{\text{tan}}, t_{\text{nor}}]^\top \).
| [in] | thrust_rad | The radial thrust component. |
| [in] | thrust_tan | The tangential thrust component. |
| [in] | thrust_nor | The normal thrust component. |
Compute the vector of the first-order cartesian equations of orbital motion given the thrust vector components \( \mathbf{t} = [t_{\text{rad}}, t_{\text{tan}}, t_{\text{nor}}]^\top \).
| [in] | thrust_rtn | The thrust components vector. |
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Compute the system of first-order modified equinoctial equations of orbital motion given the thrust vector components \( \mathbf{t} = [t_{\text{rad}}, t_{\text{tan}}, t_{\text{nor}}]^\top \).
| [in] | thrust_rad | The radial component of the thrust. |
| [in] | thrust_tan | The tangential component of the thrust. |
| [in] | thrust_nor | The normal component of the thrust. |
Compute the system of first-order modified equinoctial equations of orbital motion given the thrust vector components \( \mathbf{t} = [t_{\text{rad}}, t_{\text{tan}}, t_{\text{nor}}]^\top \).
| [in] | thrust | The components (radial, tangential, normal) of the thrust. |
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Compute the matrix of the first-order modified equinoctial equations of orbital motion as
\[ A = \begin{bmatrix} 0 & 2\sqrt{\displaystyle\frac{p}{\mu}} & 0 \\ \sqrt{p}\sin(L) & \sqrt{\displaystyle\frac{p}{\mu}}\left[(w+1)\cos(L)+f\right] & -\sqrt{\displaystyle\frac{p}{\mu}}(h\sin(L)-k\cos(L)) \\ -\sqrt{p}\cos(L) & \sqrt{\displaystyle\frac{p}{\mu}}\left[(w+1)\sin(L)+g\right] & \sqrt{\displaystyle\frac{p}{\mu}}(h\cos(L)+k\sin(L)) \\ 0 & 0 & \displaystyle\frac{\sqrt{p}}{2}\displaystyle\frac{s^2\cos(L)}{2} \\ 0 & 0 & \displaystyle\frac{\sqrt{p}}{2}\displaystyle\frac{s^2\sin(L)}{2} \\ 0 & 0 & \displaystyle\frac{\sqrt{p}}{2}(h\sin(L)-k\cos(L)) \end{bmatrix} \text{.} \]
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Compute the vector of the first-order modified equinoctial equations of orbital motion as
\[ \mathbf{b} = \left[0, 0, 0, 0, 0, \sqrt{\mu p} \left(\displaystyle\frac{w}{p}\right)^2 \right]^\top \text{.} \]
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Get the mass of the astronomical body.
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Set the mass of the astronomical body.
| [in] | t_mass | The mass of |
Enable the default astronomical body move assignment operator.
Enable the default astronomical body assignment operator.
1.13.2