Struct RecoveryForces 

pub struct RecoveryForces<F> { /* private fields */ }

Apogee recovery: a stateless force-model wrapper that swaps the inner model for recovery drag once the vehicle is descending (vy <= 0) and the simulation time is at or past deploy_after_s. Recovery drag replaces the inner acceleration entirely except for gravity: a = g − (q·CdA/m)·v̂ evaluated against local air. Terminal velocity sqrt(2·m·g/(ρ·CdA)) emerges naturally.

Because deployment is a pure function of the current state, the wrapper is deterministic and side-effect free, as ForceModel requires.

Implementations

impl<F> RecoveryForces<F>

pub fn new( inner: F, recovery_cd_area_m2: f64, deploy_after_s: f64, atmosphere: Atmosphere, wind_mps: Vec3, ) -> Result<Self>

recovery_cd_area_m2 is the parachute’s Cd·A product in m². deploy_after_s is an absolute simulation-time gate: deployment happens on the first descending state at or after it (0 = at apogee). wind_mps should match the inner model’s uniform wind.

Trait Implementations

impl<F: Clone> Clone for RecoveryForces<F>

fn clone(&self) -> Self

Returns a duplicate of the value.

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

Performs copy-assignment from source.

impl<F: Debug> Debug for RecoveryForces<F>

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

Formats the value using the given formatter.

impl<F: ForceModel> ForceModel for RecoveryForces<F>

fn acceleration(&self, state: &FlightState, mass_kg: f64) -> Result<Vec3>

Acceleration in world-frame metres per second squared.

fn acceleration_with_axis( &self, state: &FlightState, mass_kg: f64, body_axis: Vec3, ) -> Result<Vec3>

Acceleration when the commanded body axis is known, for angle-of-attack-aware models (body lift, induced drag). body_axis is the solver-resolved unit thrust axis at this stage. The default ignores the axis, which keeps every orientation-blind model (gravity, plain drag) bit-identical.