elements_to_state_vector
Convert orbital elements (semi_major_axis, eccentricity, etc.) into a position and velocity state vector in the J2000 inertial frame for spacecraft trajectory calculations.
Instructions
Convert orbital elements to state vector in J2000 frame.
Args: orbital_elements: Dict with orbital elements (semi_major_axis_m, eccentricity, etc.)
Returns: JSON string with position [x,y,z] in meters and velocity [vx,vy,vz] in m/s in the J2000 inertial frame.
Raises: No exceptions are raised directly; errors are returned as formatted strings.
Input Schema
| Name | Required | Description | Default |
|---|---|---|---|
| orbital_elements | Yes |
Output Schema
| Name | Required | Description | Default |
|---|---|---|---|
| result | Yes |