# Kepler Orbit Solver

Numerically solve Kepler’s equation E − e·sin(E) = M for eccentric anomaly E, true anomaly ν, orbital radius and relative speed, with Newton/bisection/fixed-point methods, convergence history and an SVG orbit diagram

> Canonical page: https://elysiatools.com/en/tools/kepler-orbit-solver

- **Category:** Astronomy

- **Keywords:** kepler, kepler equation, orbit, eccentric anomaly, true anomaly, mean anomaly, celestial mechanics, newton raphson, two-body problem, astronomy

## Overview

Given mean anomaly M (degrees), eccentricity e, and optional semi-major axis a (AU), this tool solves Kepler’s transcendental equation M = E − e·sin(E) for the eccentric anomaly E, then derives the true anomaly ν, orbital radius r, and relative speed. Three solver methods (Newton-Raphson, bisection, fixed-point) are available with full iteration history. The report renders an SVG orbit diagram and classifies the orbit (circular / elliptical / parabolic / hyperbolic).

## Inputs

- **Mean Anomaly (M, degrees)** (number): e.g. 45
- **Eccentricity (e)** (number): 0.0 (circle) to 1.0 (parabola); e.g. 0.3
- **Semi-major Axis (a, AU)** (number): e.g. 1.0 (Earth); leave 0 to express r in units of a
- **Solver Method** (select)
- **Max iterations** (number)
- **Tolerance** (select)

## When to use

- When calculating the precise position and velocity of a celestial body or satellite in an elliptical orbit from its mean anomaly.
- When comparing the convergence speed and numerical stability of Newton-Raphson, bisection, and fixed-point iteration methods.
- When generating visual SVG orbit diagrams showing the focus, periapsis, apoapsis, and current orbital radius vector.

## How it works

- Input the mean anomaly (M) in degrees, the orbital eccentricity (e), and optionally the semi-major axis (a) in astronomical units.
- Select your preferred numerical solver method (Newton-Raphson, bisection, or fixed-point iteration) along with the maximum iteration limit and convergence tolerance.
- The tool numerically solves for the eccentric anomaly (E), computes the true anomaly (ν), orbital radius (r), and relative speed, and renders the SVG orbit visualization.

## Use cases

- Orbital mechanics homework verification for astronomy students studying the two-body problem.
- Satellite mission planning to determine instantaneous orbital positions and relative velocities.
- Numerical analysis studies comparing the convergence rates of different root-finding algorithms on transcendental equations.

## Frequently asked questions

### What is Kepler's equation?

Kepler's equation, E − e·sin(E) = M, relates the geometric position of a body in an elliptical orbit (eccentric anomaly E) to the time elapsed since periapsis (mean anomaly M).

### Which solver method should I choose?

The Newton-Raphson method is recommended for most orbits due to its quadratic convergence, though bisection is preferred for extreme eccentricities where fixed-point iteration may diverge.

### How is the relative speed calculated?

It is derived using the vis-viva equation, expressing the orbital speed relative to the circular orbit speed at that distance.

### Can this tool solve parabolic or hyperbolic orbits?

The tool classifies the orbit based on eccentricity, but Kepler's standard equation E − e·sin(E) = M specifically solves bound elliptical (0 ≤ e < 1) and circular (e = 0) orbits.

### What happens if I leave the semi-major axis (a) as 0?

If the semi-major axis is set to 0, the tool calculates the orbital radius (r) in relative units of a rather than absolute Astronomical Units (AU).

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