Crate astrodyn

Expand description

ECS-agnostic orchestration layer for JEOD physics.

This crate is the single dependency for ECS adapters and mission crates. It re-exports the types from the astrodyn_* physics crates that such consumers need, plus orchestration functions that compose them into pipeline stages.

§Per-body functions (primary API for ECS integration)

Composable, borrow-based functions that any ECS adapter can call from its system functions. The ECS world remains the single source of truth.

accumulate_gravity — gravity accumulation across sources
evaluate_atmosphere — atmosphere evaluation pipeline
compute_ballistic_drag — aerodynamic drag with frame transform
compute_gravity_torque — gravity gradient torque with quaternion conversion
collect_and_resolve_forces — force/torque collection with frame transforms
integrate_body — RK4 integration with 6-DOF/3-DOF routing
validate_body — JEOD invariant checking
compute_orbital_elements — orbital elements from translational state
compute_body_euler_angles — Euler angles from body attitude
compute_body_lvlh_frame — LVLH frame from translational state
compute_body_geodetic — geodetic coordinates from inertial position
compute_body_solar_beta — solar beta angle

§Standalone runner

For batch propagation and Tier 3 tests, see the astrodyn_runner crate which provides a standalone Simulation struct that owns all state and drives the pipeline. ECS adapters should not use astrodyn_runner — use the per-body functions from this crate instead. astrodyn_runner is a parallel non-Bevy consumer that, like astrodyn_bevy and mission code, depends on astrodyn and only astrodyn for physics.

§Re-export discipline

Every pub use astrodyn_*::... re-export is justified by an active mission- crate, astrodyn_bevy adapter, or astrodyn_runner consumer — every non-verification consumer of the pipeline routes through this crate. The contract is intentionally tight: a rename in one of the underlying physics crates only ripples to mission code if the affected type is one the mission API genuinely owns. The criteria are spelled out at the head of the re-export block in lib.rs.

§Pipeline ordering

See PipelineStage and PIPELINE_ORDER for the canonical stage execution order that any adapter must respect.

§Quick start

Compose a vehicle through the typestate VehicleBuilder using only gateway re-exports — mission code never reaches into the physics crates directly:

use astrodyn::{
    recipes::{earth, orbital_elements, vehicle},
    F64Ext, GravityControl, GravityGradient, VehicleBuilder,
};

let mu = earth::point_mass().source.mu.m3_per_s2();
let cfg = VehicleBuilder::new()
    .from_orbital_elements(orbital_elements::iss(), mu)
    .three_dof_point_mass(vehicle::iss_mass())
    .rk4()
    .gravity(GravityControl::new_spherical(0_usize, GravityGradient::Skip))
    .build();

cfg (a VehicleConfig) is then handed to either astrodyn_bevy::VehicleConfigBevyExt::spawn_bevy or astrodyn_runner::Simulation::add_vehicle — both consumers share the same configuration shape so a mission can swap between them without reauthoring its setup code.

Re-exports§

pub use atmosphere::evaluate_atmosphere;
pub use atmosphere::evaluate_atmosphere_typed;
pub use atmosphere::evaluate_body_atmosphere_typed;
pub use atmosphere::run_atmosphere_stage;
pub use atmosphere::AtmosphereBodyInputs;
pub use atmosphere::AtmosphereConfig;
pub use atmosphere::AtmosphereModel;
pub use attach::stage_attach_combine;
pub use attach::stage_detach_capture;
pub use attach::CrossIntegFrameStateShift;
pub use attach::StageAttachInputs;
pub use attach::StageAttachOutputs;
pub use body_action::BodyAction;
pub use body_action::OrbitalElementSet;
pub use derived::compute_body_euler_angles;
pub use derived::compute_body_euler_angles_typed;
pub use derived::compute_body_lvlh_frame;
pub use derived::compute_body_lvlh_frame_typed;
pub use derived::compute_lvlh_relative_state;
pub use derived::compute_lvlh_relative_state_typed;
pub use derived::compute_orbital_elements;
pub use derived::compute_orbital_elements_typed;
pub use derived::compute_relative_state;
pub use derived::LvlhRelativeState;
pub use derived::RelativeState;
pub use derived::RelativeTranslation;
pub use frame_orchestration::evaluate_and_apply_frame_switch;
pub use frame_orchestration::FrameSwitchTargetMissing;
pub use integrable::IntegrableObject;
pub use integration::integrate_bodies_contact_coupled;
pub use integration::integrate_bodies_contact_coupled_typed;
pub use integration::integrate_body;
pub use integration::integrate_body_coupled;
pub use integration::integrate_body_coupled_typed;
pub use integration::integrate_body_typed;
pub use integration::reset_integrators;
pub use integration::CoupledBodyInput;
pub use integration::CoupledBodyInputTyped;
pub use integration::CoupledIntegScratch;
pub use integration::CoupledStageEval;
pub use integrator::Abm4State;
pub use integrator::GaussJacksonConfig;
pub use integrator::GaussJacksonState;
pub use integrator::IntegratorType;
pub use interactions::evaluate_contact_pair;
pub use interactions::evaluate_ground_contact_pair;
pub use interactions::ContactPairEval;
pub use interactions::FlatPlateStageInputs;
pub use interactions::FlatPlateState;
pub use interactions::GroundContactPairEval;
pub use interactions::ThermalIntegrationOrder;
pub use kinematic_propagation::propagate_state_via_storage;
pub use kinematic_propagation::KinematicEdge;
pub use kinematic_propagation::KinematicNodeState;
pub use pipeline::PipelineStage;
pub use pipeline::PIPELINE_ORDER;
pub use planet_config::PlanetConfig;
pub use planet_config::EARTH;
pub use planet_config::MARS;
pub use planet_config::MOON;
pub use planet_config::SUN;
pub use rotation_model::RotationModel;
pub use simulation_builder::MassTreeAttachment;
pub use simulation_builder::SimulationBuilder;
pub use source_frames::SourceFrameIds;
pub use source_handle::SourceHandle;
pub use source_state::set_source_position;
pub use source_state::set_source_state;
pub use source_state::source_frame_id;
pub use source_state::source_pfix_rotation;
pub use source_state::source_position;
pub use sources::GravitySourceEntry;
pub use validation::validate_body;
pub use validation::ValidationError;
pub use vehicle_builder::BuildState;
pub use vehicle_builder::HasIntegrator;
pub use vehicle_builder::NeedsMass;
pub use vehicle_builder::NeedsState;
pub use vehicle_builder::Ready;
pub use vehicle_builder::VehicleBuilder;
pub use vehicle_config::DerivedStateConfig;
pub use vehicle_config::EarthLightingConfig;
pub use vehicle_config::FrameSwitchConfig;
pub use vehicle_config::GeodeticConfig;
pub use vehicle_config::ShadowBody;
pub use vehicle_config::SrpModel;
pub use vehicle_config::SwitchSense;
pub use vehicle_config::VehicleConfig;
pub use wrench::aggregate_wrenches_via_storage;
pub use wrench::edge_geometry_from_composites;
pub use wrench::EdgeGeometry;

Modules§

atmosphere: Atmosphere stage: configuration and the per-body evaluate_atmosphere / evaluate_atmosphere_typed orchestration that converts inertial position to geodetic coordinates and queries the configured density / temperature / wind model.
attach: Orchestration: stage and apply a JEOD-faithful mass-tree attach / detach in an ECS-agnostic context.
body_action: ECS-agnostic body actions: queueable mutations to a vehicle’s translational state, rotational state, and mass properties.
derived: Per-body derived state functions.
ephemeris_assets: Path resolvers for the in-workspace kernel fixtures.
forces: Force-collection re-exports.
frame_orchestration: Frame-tree orchestration helpers shared by every consumer of astrodyn.
gravity: Gravity stage re-exports.
gravity_fixtures: Committed planetary gravity-coefficient fixtures.
integrable: IntegrableObject trait — port of JEOD’s multi-ODE RK4 scheduling.
integration: Integration stage: stepping per-body translational + rotational state by one timestep using the configured integrator (RK4, ABM4, or Gauss-Jackson). Includes the contact-coupled multi-body RK4 entry points used when contact pairs are registered.
integrator: astrodyn-owned vocabulary for integrator selection and state.
interactions: Interaction stage: the per-body force / torque computations between the gravity and force-collection stages — drag, flat-plate and cannonball SRP, gravity-gradient torque, and contact pairs.
kinematic_propagation: Kinematic state propagation: walks a MassStorage tree pre-order from each root and derives every kinematic child’s instantaneous composite-body state from its parent’s state composed with the per-link attach geometry.
nutation_j2000: J2000 Nutation matrix and equation of equinoxes computation.
pipeline: Canonical pipeline stage ordering shared by every JEOD adapter.
planet_config: Planet configuration presets — single source of truth for simulation setup.
precession_j2000: J2000 Precession matrix computation.
recipes: Named building blocks and pre-composed mission scenarios.
relativistic: Post-Newtonian (PPN) relativistic gravity correction.
rotation_j2000: J2000 GAST rotation and full RNP composition.
rotation_mars: Mars rotation model (IAU Pathfinder orientation).
rotation_model: Rotation-model selector that drives a planet’s per-step T_inertial→pfix update (Earth RNP, Mars principal-axis, lunar DE421 libration, or static identity).
rotation_moon: Moon rotation model (IAU 2009 simplified).
simulation_builder: Declarative scenario builder shared by the standalone runner and the Bevy adapter.
source_frames: Mapping from a gravity source to its frame-tree nodes.
source_handle: Typed wrapper around source-table indices used by crate::VehicleBuilder.
source_state: Source-state mutators that operate on a FrameTree + SourceFrameIds slice.
sources: Gravity source registry entries.
validation: Per-body and whole-scenario validation: cross-checks vehicle configuration, gravity / atmosphere / SRP wiring, integrator compatibility, and contact-pair consistency. Adapters call validate_body before stepping; misconfigurations surface as ValidationError variants instead of silently producing bad physics.
vehicle_builder: Typestate vehicle builder for the typed pipeline.
vehicle_config: Vehicle-level configuration types.
wrench: Composite-rigid-body wrench aggregation: walks a MassStorage tree leaves → root and accumulates each child’s (force, torque) into the root’s totals via the parallel-axis arm (shift_wrench_to_parent).

Macros§

define_planet: Define a new compile-time Planet marker type.
define_vehicle: Define a new compile-time Vehicle marker type.

Structs§

AerodynamicForce: Aerodynamic force and torque on a vehicle.
AtmosphereState: Atmospheric state at a given position.
AttachCombineInputs: Inputs to combine_states_at_attach.
BodyAttitude: RootInertial → body attitude of vehicle V, witnessed unit-norm and scalar-first / left-transformation (JEOD canonical).
BodyFrame: Body (CoM-centered) frame of vehicle V. Rotates with the vehicle.
CalendarDate: Gregorian calendar date+time representation.
ClosureJointKinematicsSpec: Declarative specification for a joint that pins a fixed rotation about a single axis with no time dependence — the kinematic-only degenerate case useful for closing kinematic loops.
ContactFacet: A single contact geometry + material combination.
ContactMaterial: Spring-damper plus Coulomb-friction contact material.
DetachedSubtreeState: Composite-body inertial state of a free-flying mass-tree subtree (i.e. a tree root that is not the integrated body). All fields are in the simulation’s root inertial frame.
DragConfig: Vehicle drag configuration for the ballistic (default) model.
DragConfigTyped: Typed sibling of DragConfig.
DynamicsConfig: Per-body dynamics-mode toggles consumed by the integrator.
Earth: Planet marker for Earth.
EarthLightingState: Complete earth lighting state computed for one observer position.
Ecef: Earth-centered Earth-fixed frame (ITRF-like). Rotates with Earth.
Ephemeris: Planetary ephemeris reader backed by ANISE (pure Rust SPICE).
ExponentialAtmosphere: Exponential atmosphere model parameters.
FlatPlate: A single flat plate on a vehicle surface.
FlatPlateParams: Optical properties shared by one or more flat plates.
FlatPlateSrpResult: Result of flat-plate SRP computation with thermal emission.
FlatPlateThermal: Thermal properties for a flat plate facet.
FrameAttachInputs: Inputs to derive_frame_attached_state.
FrameDerivatives: Frame-state derivatives: translational and rotational acceleration. The integrator’s per-step output.
FrameDerivativesTyped: Typed sibling of FrameDerivatives.
FrameTransform: Proper rotation taking vectors expressed in From to the same vectors expressed in To.
FrameTree: Arena-based frame tree. Portable (no ECS dependency).
GeodeticState: Geodetic coordinates on a reference ellipsoid.
GravParam: Gravitational parameter μ = GM tagged with the source planet P.
GravityAcceleration: Gravitational acceleration, gradient tensor, and potential for a body.
GravityAccelerationTyped: Typed sibling of GravityAcceleration.
GravityBodyInputs: Per-body inputs the gravity stage driver consumes.
GravityControl: Per-source gravity selector — point-mass vs. spherical harmonics, degree / order, gradient flags, and third-body / Battin / relativistic toggles.
GravityControls: Ordered list of GravityControl entries — one per gravity source active for the vehicle. The pipeline accumulates each source’s contribution into the vehicle’s net gravity acceleration in iteration order.
GravitySource: Per-body gravity payload: gravitational parameter mu plus the GravityModel that selects between point-mass and spherical-harmonics evaluation.
GroundFacet: Infinite-surface “ground” facet anchored to a planet via a Terrain model.
InertiaTensor: Mass moment of inertia tensor (kg·m²) expressed in frame F.
IntegOrigin: The integration-frame origin: position and velocity of the integration-frame origin expressed in root-inertial coordinates.
IntegrationFrame: A body’s integration frame — a non-rotating quasi-inertial frame whose origin generally differs from the root inertial origin.
JointKinematicsSpec: Declarative specification for a kinematically driven single-axis joint.
KinematicChildInputs: Inputs to compute_kinematic_child_state.
LightingBody: Apparent parameters of a celestial body as seen from the observer.
LightingParams: Lighting parameters for a body pair (light source occulted by another body).
Lvlh: Local Vertical / Local Horizontal frame relative to chief vehicle Chief. Z axis points planet-ward; Y opposes orbital angular momentum; X completes the right-handed triad (approximately along-track in near-circular orbits).
LvlhFrame: LVLH frame state: rotation matrix, angular velocity, and origin position/velocity.
Mars: Planet marker for Mars.
MassNode: Mass-tree wildcard inertial-flavor frame for kinematic-propagation scratch state.
MassNodeOutputs: Output of a single-node composition step.
MassNodeView: Read-only view of one node in a mass tree, as needed by the composition kernel.
MassPointState: Position and orientation of a mass point relative to a parent frame.
MassProperties: Rigid-body mass / inertia / CoM-offset block.
MassPropertiesTyped: Typed sibling of MassProperties parameterized by a vehicle marker V. Mass becomes a uom::si::f64::Mass, inertia is wrapped in InertiaTensor<BodyFrame<V>>, and the center-of-mass position carries the StructuralFrame<V> phantom tag.
MassTree: Arena-based mass tree. Portable, no ECS dependency.
MetAtmosphere: MET (Marshall Engineering Thermosphere) atmosphere model configuration.
Moon: Planet marker for Moon.
MultiDofJointKinematicsSpec: Declarative specification for a multi-DOF kinematic joint.
Ned: North-East-Down topocentric frame relative to chief vehicle Chief.
OrbitalElements: Classical orbital elements computed from Cartesian state vectors.
PlanetFixed: Planet-fixed frame for any planet P. Rotates with that planet.
PlanetInertial: A particular planet’s inertial (non-rotating, J2000-aligned) frame, centered at the planet’s CoM.
PlanetShape: Planetary shape parameters (reference ellipsoid).
Qty3: Componentwise 3-vector: each of x, y, z carries the dimension D, and the whole vector carries the frame tag F.
RadiationForce: Radiation pressure force and torque on a vehicle.
RefFrameRot: Rotational state of a frame relative to its parent.
RefFrameState: Combined translational + rotational state of a frame relative to its parent. The untyped storage form used by crate::FrameTree.
RefFrameTrans: Translational state of a frame relative to its parent.
ResolvedRelativisticSource: Resolved source for relativistic correction computation.
ResolvedSource: Information about a gravity source resolved from a source identifier.
RootInertial: The simulation’s root inertial frame — the unique inertial node at the top of the frame tree.
RotationalState: Rotational state of a rigid body.
RotationalStateTyped: Typed sibling of RotationalState parameterized by a vehicle marker V. The attitude is a BodyAttitude<V> — the wrapper owns the JEOD left-multiply convention so callers cannot integrate via raw multiply and accidentally swap operand order (issue #252). Angular velocity carries the BodyFrame<V> phantom tag.
SelfPlanet: Phantom marker for “this entity’s own planet” — used by ECS adapters whose per-entity components carry PlanetFixed<P> phantoms but whose planet identity is determined at runtime by the entity itself.
SelfRef: Phantom marker for “this entity’s own vehicle frame” — used by ECS adapters whose per-entity components carry frame phantoms but whose vehicle identity is determined at runtime by the entity itself.
SimulationTime: Complete simulation time state across all time scales.
SinusoidalJointKinematicsSpec: Declarative specification for a single-axis joint whose angle is a sinusoidal function of time:
SixDofState: Combined translational + rotational state for 6-DOF integration.
SixDofStateTyped: Typed sibling of SixDofState carrying a vehicle phantom V on the rotational half and a frame phantom F on the translational half. Composes TranslationalStateTyped<F> and RotationalStateTyped<V> without introducing new arithmetic — both halves carry their own to_untyped / from_untyped_unchecked boundaries already.
SphericalTerrain: Spherical-Earth terrain — ground at a fixed planet radius.
StructuralFrame: Structural (geometric-origin) frame of vehicle V. Rotates with vehicle.
Sun: Planet marker for Sun.
TidalBody: A body that raises tides on the primary (e.g., Moon, Sun).
TidalConfig: Configuration for solid body tidal effects on a gravity source.
TidalConfigTyped: Typed sibling of TidalConfig.
TimeManager: Time manager: maintains all time scale values and propagates updates.
TotalForce: Net body force / torque, the integrator’s input each step.
TotalForceTyped: Typed sibling of TotalForce.
TranslationalState: Translational state in the integration frame.
TranslationalStateTyped: Typed sibling of TranslationalState carrying a frame phantom on the position and velocity components. Defaults to the inertial frame to match the existing untyped storage convention; override with an explicit frame tag for non-inertial integrations.
Wrench: Plain (force, torque) pair in some implicit frame, used by the orchestration walk to stage the per-node accumulator before writing back into the storage layer. The frame discipline lives at the caller — by the time a Wrench crosses module boundaries, the orchestration layer (astrodyn::wrench) tags it with the owning entity’s structural frame.
kilogram: Re-export of uom::si::mass::kilogram for typed-quantity callers that need the unit token directly (Mass::new::<kilogram>(420_000.0), mass.get::<kilogram>()). Adapter crates that consume astrodyn but not uom (the production-path layer rule) reach through this alias. The kilogram is the SI unit of mass. It is defined by taking the fixed numerical value of the Planck constant h to be 6.626 070 15 × 10⁻³⁴ when expressed in the unit J s, which is equal to kg m² s⁻¹, where the meter and the second are defined in terms of c and ∆ν_Cs.

Enums§

EphemerisBody: Solar system body identifiers for ephemeris queries.
EphemerisError: Ephemeris errors.
EulerSequence: The 12 possible Euler rotation sequences.
GeoIndexType: Type of geomagnetic index provided.
GravityGradient: Self-documenting selector for the gravity-gradient tensor flag at the GravityControl constructor seam. Replaces the bare bool the spherical / non-spherical constructors used to accept, so a call site reads as GravityControl::new_spherical(earth, GravityGradient::Skip) rather than the bare-bool form, and the reader does not need to remember which boolean polarity meant what.
GravityModel: Gravity-model selector — point-mass (μ/r²) vs. spherical-harmonics (Gottlieb-recursion Cnm/Snm evaluation).
JointKinematicsModel: Unifying enum over the kinematic-only joint specifications shipped today: constant-rate single-axis (JointKinematicsSpec), sinusoidal single-axis (SinusoidalJointKinematicsSpec), closure single-axis (ClosureJointKinematicsSpec), and multi-DOF chains (MultiDofJointKinematicsSpec).
LvlhAngularVelocityFrame: Frame in which the user-supplied LVLH-relative angular velocity is expressed.
Phase: Which phase of JEOD’s runtime is being mirrored when evaluating ground contact.
RefFrameKind: Runtime kind of a reference-frame tree node. Mirrors the runtime tags JEOD uses to distinguish inertial, planet-fixed, and body frames.
SingleDofKinematics: Per-DOF kinematic style for a single axis inside a MultiDofJointKinematicsSpec chain.
TimeScaleId: Identifies a time scale in the converter graph.

Constants§

AXIS_NORM_TOL: Tolerance on axis_in_parent.length_squared() - 1 accepted by evaluate.
EARTH_K2: Default Love number k2 for Earth solid body tides.
J2000_TAI_TJT: TAI TJT at J2000.0 TT epoch. TT = TAI + 32.184s, so TAI is 32.184s behind TT. 32.184s = 32.184/86400 days = 0.000372500 days TAI TJT = 11544.5 - 0.000372500 = 11544.499627500
J2000_TT_JD: J2000.0 epoch as Julian Date: 2000-01-01 12:00:00 TT.
J2000_TT_TJT: J2000.0 as TJT: MJD 51544.5 - 40000 = 11544.5
MAX_MULTI_DOF_AXES: Maximum number of DOFs a MultiDofJointKinematicsSpec can carry.
SECONDS_PER_DAY: Seconds per day.
SOLAR_RADIUS: Solar radius in m (matching JEOD radiation_source.hh).
TAI_TT_OFFSET: TT - TAI offset in seconds (exact by definition).

Traits§

Array3Ext: Extension trait on [f64; 3] (raw component arrays from CSVs or JEOD initial conditions) producing frame-tagged 3-vectors.
CompatibleVehiclePair: Paired-vehicle compatibility: fires when a (Subject, Reference) (or (Parent, Child)) pair on one value does not match the pair on the slot it’s being passed into.
F64Ext: Unit-construction extension on f64.
Frame: Compile-time reference frame tag.
FrameStorage: Read-only access to a frame tree, abstracting over the underlying storage. Implementors: FrameTree (arena), and Bevy adapters such as astrodyn_bevy’s RelativeFrameState SystemParam.
MassStorage: Storage-agnostic read view of a mass tree.
Planet: Compile-time planet tag used to parameterize planet-fixed frames.
Terrain: Planetary terrain model that maps a planet-fixed query position to a ground point and outward surface normal.
Vec3Ext: Extension trait on glam::DVec3 producing frame-tagged 3-vectors.
Vehicle: Compile-time vehicle tag used to parameterize vehicle-relative frames.

Functions§

abm4_translational_step: Advance translational state by one ABM4 step.
accumulate_gravity: Accumulate gravity from all sources for a single body.
accumulate_gravity_typed: Typed sibling of accumulate_gravity.
accumulate_relativistic_corrections: Compute post-Newtonian relativistic corrections for all gravity controls that have relativistic: true.
accumulate_relativistic_corrections_typed: Typed sibling of accumulate_relativistic_corrections.
calendar_to_tjt: Convert a Gregorian calendar date to truncated Julian time (TJT).
collect_and_resolve_forces: Collect all interaction forces and torques, resolve frame transforms, and compute frame derivatives.
collect_and_resolve_forces_typed: Typed sibling of collect_and_resolve_forces.
combine_states_at_attach: Combine two free-body states into one rigid body, conserving linear momentum (about the integration-frame origin) and angular momentum (about the new combined CoM). See module docs for the algorithm and JEOD source mapping.
compute_ballistic_drag: Compute ballistic aerodynamic drag force.
compute_ballistic_drag_typed: Typed sibling of compute_ballistic_drag.
compute_body_geodetic: Compute the geodetic state of a body in inertial coordinates.
compute_body_geodetic_typed: Typed sibling of compute_body_geodetic.
compute_body_solar_beta: Compute the solar beta angle from raw position / velocity / Sun position.
compute_body_solar_beta_typed: Typed sibling of compute_body_solar_beta.
compute_cannonball_srp: Compute cannonball SRP force using JEOD’s RadiationDefaultSurface formula.
compute_cannonball_srp_typed: Typed sibling of compute_cannonball_srp.
compute_delta_c20: Compute the first-order tidal delta coefficient ΔC20.
compute_delta_c20_typed: Typed sibling of compute_delta_c20.
compute_earth_lighting: Raw kernel: compute earth lighting conditions for an observer.
compute_earth_lighting_typed: Typed sibling of compute_earth_lighting.
compute_euler_angles_from_matrix_typed: Typed sibling for the file-private compute_euler_angles_from_matrix_impl kernel.
compute_flat_plate_srp_thermal: Compute SRP force, torque, and temperature derivatives from flat plates with thermal emission.
compute_frame_derivatives: Compute translational and rotational frame derivatives from collected forces.
compute_gravity_torque: Compute gravity gradient torque on a rigid body.
compute_gravity_torque_typed: Typed sibling of compute_gravity_torque.
compute_kinematic_child_state: Derive a kinematic child’s instantaneous composite-body state from the parent’s composite-body state and the per-link attach geometry.
compute_matrix_from_euler_angles_typed: Typed sibling for the file-private compute_matrix_from_euler_angles_impl kernel.
compute_quaternion_from_euler_angles_typed: Typed sibling for the file-private compute_quaternion_from_euler_angles_impl kernel.
compute_relative_state_typed: Typed sibling of FrameTree::compute_relative_state returning a RefFrameStateTyped<From, To>. The caller asserts the supplied frame IDs correspond to frames whose markers are From and To — the arena is heterogeneous and stores untyped RefFrameState per node, so this is a from_untyped_unchecked boundary lift.
compute_shadow_fraction: Compute the illumination fraction for a vehicle considering shadowing by a celestial body (conical shadow model).
compute_t_inertial_struct: Compute the inertial-to-structural rotation matrix from component transforms.
compute_t_parent_this_from_tjt: Convenience: compute T_parent_this from simulation time parameters.
compute_t_parent_this_from_tjt_with_polar: Convenience: compute T_parent_this from simulation time parameters with optional polar motion.
compute_t_parent_this_from_tjt_with_polar_typed: Typed sibling of compute_t_parent_this_from_tjt_with_polar returning the rotation already wrapped as a typed FrameTransform<RootInertial, PlanetFixed<P>>. Generic over the planet phantom P so consumers in different planet pipelines (Earth / Mars / Moon) share one entry shape.
compute_translational_derivatives: Compute translational-only frame derivatives (no rotational dynamics).
default_leap_second_table: Create the default leap second table from hardcoded JEOD data.
derive_frame_attached_state: Compute the attached body’s composite-body inertial state from the parent reference frame’s current state, the (frozen-at-attach) rigid-body parent→structure offset, and the body’s structure→composite CoM offset.
dimensionless: Convenience constructor — wrap a raw f64 (dimensionless) as a typed Ratio.
evaluate_body_gravity_typed: Per-body gravity composition: applies the RF.10 integ-origin shift, accumulates Newtonian gravity, and adds the post-Newtonian relativistic correction in a single call.
evaluate_closure_kinematics: Evaluate a ClosureJointKinematicsSpec.
evaluate_joint_kinematics: Evaluate the joint kinematics at elapsed time t (seconds since the joint’s initial_angle_rad reference).
evaluate_multi_dof_kinematics: Evaluate a MultiDofJointKinematicsSpec at elapsed time t.
evaluate_sinusoidal_kinematics: Evaluate a SinusoidalJointKinematicsSpec at elapsed time t (seconds since the joint’s reference epoch).
frame_compute_relative_state_via_storage: Compute the state of to relative to from. Generic counterpart to FrameTree::compute_relative_state.
frame_origin: Get the position and velocity of a frame relative to the root inertial frame. Mirrors astrodyn_runner::Simulation::frame_origin so consumers that don’t own a Simulation (the Bevy adapter) can compute frame origins using only the frame tree.
frame_origin_typed: Typed sibling of frame_origin returning the frame’s position and velocity already wrapped as Position<F> / Velocity<F>. The frame marker F is the root frame’s marker (the result expresses the query frame’s origin in root-relative coordinates) — caller asserts the root is F. For the Bevy adapter and astrodyn_runner today, the root is by construction inertial, so callers pass F = Inertial.
init_from_mean_anomaly: Initialize translational state from Keplerian orbital elements (mean anomaly).
init_from_orbital_elements_typed: Typed sibling of init_from_orbital_elements.
init_rot_from_lvlh: Initialize rotational state from an LVLH-relative attitude + angular velocity.
propagate_forward: Forward propagation: compute a derived frame state from a source frame state and a relative mass point offset.
radians: Convenience constructor — wrap a raw f64 (radians) as a typed Angle.
recompute_composites_via_storage: Drive compute_node_composite in post-order over every root in the storage and return the outputs keyed by node id.
run_gravity_stage: Drive the gravity stage across an adapter-supplied iterator of bodies.
shift_wrench_to_parent: Single-link parallel-axis wrench shift.
solar_flux_at_distance: Compute solar flux at a given distance from the Sun.
sync_pfix_rotation: Sync a planet-fixed frame node’s rotation state from a computed matrix.
tjt_to_calendar: Convert truncated Julian time (TJT) to a Gregorian calendar date.
ut1_to_gmst_seconds: Convert UT1 days since noon 2000-01-01 to GMST in sidereal seconds.

Type Aliases§

Acceleration: Acceleration in frame F. Base SI unit: m/s².
Angle: Quantity type alias using the default base units.
AngularAcceleration: Angular acceleration in frame F. Base SI unit: rad/s².
AngularVelocity: Angular velocity in frame F. Base SI unit: rad/s.
Force: Force in frame F. Base SI unit: newtons.
FrameId: Handle into the FrameTree arena.
JeodQuat: The JEOD canonical quaternion type: scalar-first, left-transformation.
Mass: Quantity type alias using the default base units.
MassBodyId: Handle into the MassTree arena.
Position: Position in frame F (default: RootInertial). Base SI unit: meters.
Ratio: Quantity type alias using the default base units.
Torque: Torque in frame F. Base SI unit: N·m.
Velocity: Velocity in frame F. Base SI unit: m/s.

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§Per-body functions (primary API for ECS integration)

§Standalone runner

§Re-export discipline

§Pipeline ordering

§Quick start

Re-exports§

Modules§

Macros§

Structs§

Enums§

Constants§

Traits§

Functions§

Type Aliases§

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