Orbit Analysis Lab

Orbital mechanics calculators and analysis tools for mission planning

Input Parameters

Calculate the orbital period of a satellite based on its semi-major axis using Kepler's Third Law.

Semi-Major Axis (km) Distance from Earth's center to orbit

Results

Orbital Period

—

Altitude —

Revolutions/Day —

Input Parameters

Calculate orbital velocity and escape velocity for a given altitude.

Altitude (km) Height above Earth's surface

Results

Orbital Velocity

—

Escape Velocity

—

Input Parameters

Calculate delta-V requirements for a Hohmann transfer between two circular orbits.

Initial Orbit Altitude (km)

Final Orbit Altitude (km)

Results

Total Delta-V

—

ΔV1 (Burn 1) —

ΔV2 (Burn 2) —

Transfer Time —

Input Parameters

Calculate ground track spacing and coverage parameters.

Altitude (km)

Inclination (degrees)

Results

Ground Track Spacing —

Max Latitude Coverage —

Repeat Cycle —

Mission Parameters

Calculate total delta-V budget for a complete mission profile.

Orbit Insertion (m/s)

Station Keeping (m/s/year)

Mission Duration (years)

Deorbit (m/s)

Contingency Margin (%)

Delta-V Budget Breakdown

Total Budget (with margin)

—

Breakdown

Orbit Insertion: —

Station Keeping: —

Deorbit: —

Subtotal: —

Contingency: —