Module astro 

Numerical astrodynamics engine for orbit propagation, force models, and future flight-dynamics primitives.

Current scope:

• inertial Cartesian state representation
• two-body gravity and J2 perturbation
• fixed-step RK4
• adaptive Dormand-Prince 5(4) (DP54)
• propagation results with step statistics

Planned future work includes dense output, event handling, richer propagation contexts, additional force models, covariance propagation, estimation, and maneuver support.

Re-exports

pub use spk::DafByteOrder;

pub use spk::DafFileRecord;

pub use spk::DafSpk;

pub use spk::Spk;

pub use spk::SpkError;

pub use spk::SpkSegmentDescriptor;

pub use spk::SpkState;

pub use spk::SpkStateVector;

pub use elements::coe2rv;

pub use elements::rv2coe;

pub use elements::ClassicalElements;

pub use elements::ElementsError;

pub use elements::OrbitType;

pub use error::PropagationError;

pub use state::CartesianState;

pub use time::Time;

Modules

angles

Satellite angular geometry against celestial bodies.

atmosphere

NRLMSISE-00 empirical neutral-atmosphere model (Picone et al., 2002).

bodies

Low-precision analytic Sun and Moon ephemerides.

cdm

CCSDS Conjunction Data Message (CDM) KVN and XML format reader and writer.

conjunction

Conjunction geometry and collision-probability (Pc) computation.

constants

Canonical physical and unit constants shared by the core crates.

covariance

Position-covariance modeling for conjunction and orbit analysis.

coverage

One-epoch satellite/station coverage grid.

data

Embedded reference-data tables, relocated from orbis_nif so the core crate is usable from Rust without Rustler or the BEAM.

doppler

Doppler and range-rate computations for satellite-ground links.

elements

State-vector to classical orbital element conversions.

error

events

forces

frames

High-accuracy frame transforms (Skyfield-compatible, 0-ULP).

integrators

iod

Initial orbit determination (IOD) from position or angle observations.

lambert

Lambert two-point boundary-value orbit solver (Battin’s method).

math

ndm

Shared CCSDS Navigation Data Message primitives.

observation

Observational-astronomy geometry primitives.

oem

CCSDS Orbit Ephemeris Message (OEM) KVN and XML reader/writer.

omm

CCSDS Orbit Mean-Elements Message (OMM) parser, encoder, and SGP4 bridge.

opm

CCSDS Orbit Parameter Message (OPM) KVN and XML reader/writer.

passes

TLE pass prediction over a ground station.

propagator

rf

RF link-budget primitives.

sgp4

SGP4 satellite propagation with 0 ULP parity to the Vallado C++ reference implementation (v2020-07-13).

spk

JPL SPK/DAF binary-kernel parsing.

state

tca

Time of closest approach search between two TLE-backed satellites.

time

Time scales and the public time model.

tle

Two-Line Element (TLE) format parser and encoder.

tolerances

Shared named numerical tolerances for deterministic scalar kernels.

xml

Minimal XML text helpers shared by the CCSDS message encoders (CDM, OMM).