Orbital Mechanics Calculator
Complete orbital mechanics calculations. Kepler's laws, Hohmann transfers, delta-v, Lagrange points, escape velocities, and relativistic effects.
Step 1 of 2
How to Use This Calculator
- Use the Kepler module to enter semi-major axis (AU) and central mass (solar masses) to compute Orbital Period and Mean Velocity.
- In the Hohmann Transfer section, enter departure and arrival orbit radii to get Total Delta-V (km/s) and Transfer Time (days).
- Check Lagrange Points to find stable gravitational equilibria — L4 and L5 are stable, L1/L2/L3 are unstable.
- Use the Roche Limit and Hill Sphere outputs to determine where a satellite will survive vs. be tidally disrupted.
- Review the orbital comparison chart against the solar system planets to contextualize your orbit.
What each input means
- Calculation Type
- Calculation mode to use.
- Central Body Mass (M☉)
- Mass in solar masses
- Semi-Major Axis (AU)
- Average orbital distance
- Eccentricity
- 0 = circle, <1 = ellipse, 1 = parabola
- Inclination (degrees)
- Angle from reference plane
- Starting Orbit (AU)
- Earth orbit = 1 AU
- Target Orbit (AU)
- Mars orbit ≈ 1.52 AU
- Parent Body Mass (Earth masses)
- Sun ≈ 333,000 Earth masses
- Primary Mass (M☉)
- Larger body (e.g., Sun)
- Secondary Mass (M☉)
- Smaller body (Earth ≈ 3e-6 M☉)
- Orbital Radius (AU)
- Mercury ≈ 0.387 AU
- Object Velocity (km/s)
- Mercury ≈ 47.87 km/s
How this is calculated
Formula
T² = (4π²/GM)a³ (Kepler's 3rd) | v = √(GM/r) | ΔV = v_transfer - v_circularWorked example, using the default values
- Identify Input Parameters4 parametersCalculation Type = 0, Central Body Mass (M☉) = 1, Semi-Major Axis (AU) = 1, Eccentricity = 0.017 = 18 input(s) provided
- Calculate Orbital PeriodOrbital Period0.9998918722467838 = 0.9998918722467838
- Calculate Mean VelocityMean Velocity29.7888993205065 = 29.7888993205065
- Calculate Orbital PeriodOrbital Period365.21050633813775 = 365.21050633813775
- Calculate PerihelionPerihelion0.983 = 0.983
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