state_vector_to_elements
Convert a spacecraft's position and velocity into classical orbital elements for orbit characterization.
Instructions
Convert state vector to classical orbital elements.
Args: state_vector: Dict with position_m and velocity_ms arrays
Returns: JSON string with classical orbital elements (a, e, i, RAAN, omega, nu).
Raises: No exceptions are raised directly; errors are returned as formatted strings.
Input Schema
| Name | Required | Description | Default |
|---|---|---|---|
| state_vector | Yes |
Output Schema
| Name | Required | Description | Default |
|---|---|---|---|
| result | Yes |