Orbit equation of motion using position and velocity.
Calculate the new time rate of change of state (position & velocity) using two-body dynamics with disturbance forces
![\[ \ddot{\vec{r}} = -\frac{\mu}{r^{2}}\frac{\vec{r}}{r}\]](form_62.png)
The returned state vector is:
![\[ \begin{bmatrix} \dot{\vec{r}}\\ \dot{\vec{v}} \end{bmatrix} = \begin{bmatrix} \vec{v}\\ -\frac{\mu}{\left|\vec{r}\right|^{3}}\vec{r} \end{bmatrix} \]](form_63.png)
- Parameters:
-
_time current time (in seconds) _state vector of states, ![$\left[\vec{r},\vec{v}\right]^{T}$](form_64.png)
(kilometers, kilometers/second) _pOrbit pointer to the current Orbit instance _pAttitude pointer to the current Attitude instance _parameters additional parameters for integration ![$\left[\mu\right]$](form_65.png)
_forceFuncPtr pointer to the force calculating function
- Returns:
- 6x1 vector of time derivatives of state
![$\left[\dot{\vec{r}},\dot{\vec{v}}\right]^{T}$](form_66.png)
Definition at line 71 of file TwoBodyDynamics.h.
References _, O_SESSAME::Functor::Call(), O_SESSAME::Attitude::GetStateObject(), O_SESSAME::OrbitState::GetStateRepresentation(), O_SESSAME::Matrix, O_SESSAME::OrbitStateRepresentation::SetPositionVelocity(), O_SESSAME::Vector, and O_SESSAME::VectorIndexBase.
