lambert_problem_solver
Solve Lambert's problem to compute transfer orbit velocities and orbital elements from two position vectors and time of flight, supporting prograde/retrograde directions and multiple revolutions.
Instructions
Solve Lambert's orbital boundary value problem.
Given two position vectors and time-of-flight, determine the orbit connecting them. This is foundational for interplanetary mission design and rendezvous trajectory planning.
Args: r1_m: Initial position vector [x, y, z] in meters r2_m: Final position vector [x, y, z] in meters tof_s: Time of flight in seconds direction: Transfer direction - "prograde" or "retrograde" num_revolutions: Number of complete revolutions (default 0 for short path) central_body: Central body name for gravitational parameter
Returns: JSON string with transfer orbit velocities, orbital elements, transfer angle, and timing information.
Raises: No exceptions are raised directly; errors are returned as JSON strings.
Input Schema
| Name | Required | Description | Default |
|---|---|---|---|
| r1_m | Yes | ||
| r2_m | Yes | ||
| tof_s | Yes | ||
| direction | No | prograde | |
| num_revolutions | No | ||
| central_body | No | earth |
Output Schema
| Name | Required | Description | Default |
|---|---|---|---|
| result | Yes |