propagate_numerical
Propagate satellite orbits with high-fidelity numerical integration, using configurable force models for gravity, drag, solar radiation pressure, third-body, and relativity.
Instructions
Propagate a satellite orbit using high-fidelity numerical integration.
Uses configurable force models: gravity, atmospheric drag, solar radiation pressure, third-body perturbations, and relativistic corrections.
Use list_propagation_options() to see available force model presets and overrides.
Args: epoch: Initial epoch (ISO string). state_eci: ECI Cartesian state [x,y,z,vx,vy,vz] in meters and m/s. target_epoch: Single target epoch (ISO string). start_epoch: Range start epoch (ISO string). end_epoch: Range end epoch (ISO string). step_seconds: Step size in seconds for range propagation (default 60). output_frame: Output coordinate frame (eci, ecef, gcrf, itrf, eme2000, koe_osc, koe_mean). angle_format: Angle format for KOE output ("degrees" or "radians"). force_model: Force model preset name (default "default"). spacecraft_params: [mass_kg, drag_area_m2, Cd, srp_area_m2, Cr]. Required for most presets. gravity_degree: Override gravity spherical harmonic degree. gravity_order: Override gravity spherical harmonic order. drag_model: Override drag model ("harris_priester", "nrlmsise00", "none"). enable_srp: Override solar radiation pressure toggle. enable_third_body: Override third-body perturbations toggle. enable_relativity: Override relativistic corrections toggle.
Input Schema
| Name | Required | Description | Default |
|---|---|---|---|
| epoch | Yes | ||
| end_epoch | No | ||
| state_eci | Yes | ||
| drag_model | No | ||
| enable_srp | No | ||
| force_model | No | default | |
| start_epoch | No | ||
| angle_format | No | degrees | |
| output_frame | No | eci | |
| step_seconds | No | ||
| target_epoch | No | ||
| gravity_order | No | ||
| gravity_degree | No | ||
| enable_relativity | No | ||
| enable_third_body | No | ||
| spacecraft_params | No |