Struct Drag

pub struct Drag {
    pub density: AtmDensity,
    pub drag_frame: Frame,
    pub estimate: bool,
}

Drag implements all three drag models.

Fields

density: AtmDensity

Density computation method

drag_frame: Frame

Frame to compute the drag in

estimate: bool

Set to true to estimate the coefficient of drag

Implementations

impl Drag

pub fn earth_exp(almanac: Arc<Almanac>) -> Result<Arc<Self>, DynamicsError>

Common exponential drag model for the Earth

pub fn std_atm1976(almanac: Arc<Almanac>) -> Result<Arc<Self>, DynamicsError>

Drag model which uses the standard atmosphere 1976 model for atmospheric density

Trait Implementations

impl Clone for Drag

fn clone(&self) -> Drag

Returns a copy of the value.

fn clone_from(&mut self, source: &Self)

Performs copy-assignment from source.

impl Display for Drag

fn fmt(&self, f: &mut Formatter<'_>) -> Result

Formats the value using the given formatter.

impl ForceModel for Drag

fn estimation_index(&self) -> Option<usize>

If a parameter of this force model is stored in the spacecraft state, then this function should return the index where this parameter is being affected

fn eom( &self, ctx: &Spacecraft, almanac: Arc<Almanac>, ) -> Result<Vector3<f64>, DynamicsError>

Defines the equations of motion for this force model from the provided osculating state.

fn dual_eom( &self, _osc_ctx: &Spacecraft, _almanac: Arc<Almanac>, ) -> Result<(Vector3<f64>, Matrix4x3<f64>), DynamicsError>

Force models must implement their partials, although those will only be called if the propagation requires the computation of the STM. The osc_ctx is the osculating context, i.e. it changes for each sub-step of the integrator. The last row corresponds to the partials of the parameter of this force model wrt the position, i.e. this only applies to conservative forces.