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//! Errors produced by the `orbitprop` module.
use numeris::ode;
use thiserror::Error;
use crate::Frame;
/// Errors that can occur while configuring or executing orbit propagation.
#[derive(Debug, Error)]
pub enum Error {
// -- propagator-internal errors --------------------------------------
/// Returned when the integrated state matrix has an unexpected
/// number of columns.
#[error("Invalid number of columns: {c}")]
InvalidStateColumns { c: usize },
/// Returned by the dense-output interp helpers when the underlying
/// ODE solution does not carry interpolation data.
#[error("No Dense Output in Solution")]
NoDenseOutputInSolution,
/// Wraps an [`ode::OdeError`] surfaced by the chosen integrator.
/// `OdeError` does not implement `std::error::Error` (numeris keeps
/// it as a plain `Display`-only enum), so this variant is built
/// manually rather than via `#[from]`.
#[error("ODE Error: {0}")]
OdeError(ode::OdeError),
/// RODAS4 does not support state transition matrix propagation
/// (`C == 7`).
#[error("RODAS4 does not support state transition matrix propagation")]
RODAS4NoSTM,
/// Gauss-Jackson 8 does not support state transition matrix
/// propagation (`C == 7`).
#[error("Gauss-Jackson 8 does not support state transition matrix propagation")]
GaussJackson8NoSTM,
// -- precomputed.rs --------------------------------------------------
/// Returned by [`Precomputed::interp`](crate::orbitprop::Precomputed::interp)
/// when the requested time falls outside the precomputed range.
#[error("Precomputed::interp: time {time} is outside of precomputed range : {begin} to {end}")]
PrecomputedOutOfRange {
time: String,
begin: String,
end: String,
},
/// Wraps an error surfaced while building a
/// [`Precomputed`](crate::orbitprop::Precomputed) interp table from
/// JPL ephemeris data.
#[error(transparent)]
Jplephem(#[from] crate::jplephem::Error),
// -- satstate.rs -----------------------------------------------------
/// Returned by [`SatState::set_pos_uncertainty`](crate::orbitprop::SatState::set_pos_uncertainty),
/// [`SatState::set_vel_uncertainty`](crate::orbitprop::SatState::set_vel_uncertainty),
/// and the internal `cov_frame_to_gcrf` helper when the supplied
/// frame is not one of the supported orbital or inertial frames.
#[error("Unsupported frame for uncertainty: {frame}. Must be GCRF, LVLH, RIC, or NTW")]
UnsupportedUncertaintyFrame { frame: Frame },
/// Returned by [`SatState::propagate`](crate::orbitprop::SatState::propagate)
/// when a scheduled maneuver uses a frame in which a delta-v cannot be
/// resolved. Validated up front so it surfaces as an error rather than a
/// panic inside the force evaluation.
#[error("Unsupported frame for maneuver: {frame}. Must be GCRF, RTN (RIC), NTW, or LVLH")]
UnsupportedManeuverFrame { frame: Frame },
/// Returned by [`ContinuousThrust::new`](crate::orbitprop::ContinuousThrust::new)
/// when the thrust frame is not one in which a thrust acceleration can be
/// resolved. Validated at construction so it surfaces as an error rather
/// than a panic inside the force evaluation.
#[error("Unsupported frame for thrust: {frame}. Must be GCRF, RTN (RIC), NTW, or LVLH")]
UnsupportedThrustFrame { frame: Frame },
// -- settings.rs -----------------------------------------------------
/// Returned by [`PropSettings::set_gravity`](crate::orbitprop::PropSettings::set_gravity)
/// when `order > degree`.
#[error("Gravity order ({order}) must be ≤ degree ({degree})")]
InvalidGravityOrder { order: u16, degree: u16 },
/// Returned when a Gauss-Jackson 8 propagation is requested over a span
/// shorter than its 8-step startup requires. Reduce `gj_step_seconds` or
/// use an adaptive integrator (e.g. RKV98) for short arcs.
#[error(
"Propagation span ({span} s) is too short for Gauss-Jackson 8, which \
needs at least 8 steps ({min} s at the configured step). Reduce \
gj_step_seconds or use an adaptive integrator."
)]
GJIntervalTooShort { span: f64, min: f64 },
}
impl From<ode::OdeError> for Error {
fn from(e: ode::OdeError) -> Self {
Self::OdeError(e)
}
}
/// Convenient type alias used throughout the `orbitprop` module.
pub type Result<T> = std::result::Result<T, Error>;