propagate_orbit_j2
Propagate an orbit with J2 perturbations by numerically integrating initial orbital elements over a given time span, returning state vectors at each step.
Instructions
Propagate orbit with J2 perturbations using numerical integration.
Args: initial_state: Initial orbital state (elements or state vector) propagation_time_s: Propagation time in seconds time_step_s: Integration time step in seconds
Returns: JSON string with propagated state vectors at each time step.
Raises: No exceptions are raised directly; errors are returned as formatted strings.
Input Schema
| Name | Required | Description | Default |
|---|---|---|---|
| initial_state | Yes | ||
| propagation_time_s | Yes | ||
| time_step_s | No |
Output Schema
| Name | Required | Description | Default |
|---|---|---|---|
| result | Yes |