State ↔ elements
Convert between Cartesian state vectors and classical orbital elements.
SIDUS educational calculator. Category orbital. Tags: apollo, GNC, orbital. Pure SI. Not flight software.
Formula
h = r × v · e = (v×h)/μ − r̂ · a = 1/(2/r − v²/μ)
Cartesian ↔ classical elements
Primary sources
- Fundamentals of Astrodynamics and Applications (David A. Vallado): Standard reference for two-body, Lambert, maneuvers, and J2. Equations implemented independently in SIDUS.
- Orbital Mechanics for Engineering Students (Howard D. Curtis): Textbook derivations for Hohmann, vis-viva, rocket equation, elements.
- Apollo-11 AGC source (NASA / MIT (public domain listings)): Comanche055 & Luminary099 guidance computer source. Algorithms reimplemented from published equations, not copied as binary/listing dumps.
How do AI agents use this tool?
Read /llms.txt or call https://sidus.tools/api/mcp. Open the interactive page for live SI inputs.