Struct ConstantDrag 

pub struct ConstantDrag {
    pub rho: f64,
    pub drag_frame: Frame,
    pub estimate: bool,
}

ConstantDrag implements a constant drag model as defined in Vallado, 4th ed., page 551, with an important caveat.

WARNING: This basic model assumes that the velocity of the spacecraft is identical to the velocity of the upper atmosphere, This is a bad assumption and should not be used for high fidelity simulations. This will be resolved after https://gitlab.com/chrisrabotin/nyx/issues/93 is implemented.

Fields

rho: f64

atmospheric density in kg/m^3

drag_frame: Frame

Geoid causing the drag

estimate: bool

Set to true to estimate the coefficient of drag

Trait Implementations

impl Clone for ConstantDrag

fn clone(&self) -> ConstantDrag

Returns a duplicate of the value.

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

Performs copy-assignment from source.

impl Display for ConstantDrag

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

Formats the value using the given formatter.

impl ForceModel for ConstantDrag

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.