This tool calculates the change in velocity (delta v) for your spacecraft based on your input parameters.

## How to Use the Delta V Calculator

To use this Delta V calculator, input the initial mass of your spacecraft (in kilograms), the final mass after expelling the fuel (in kilograms), and the exhaust velocity (in meters per second). Once you’ve entered all the required parameters, click the “Calculate” button to get the result for Δv, which represents the change in velocity (in meters per second).

## How the Calculation Works

The Delta V (Δv) of a spacecraft can be calculated using the Tsiolkovsky rocket equation:

**Δv = V _{e} * ln(m_{0} / m_{f})**

Where:

- V
_{e}is the exhaust velocity. - m
_{0}is the initial mass. - m
_{f}is the final mass.

## Limitations

This calculator assumes that the exhaust velocity is constant and does not account for gravitational forces or other external forces acting on the spacecraft. It also assumes that the propulsion system is 100% efficient and that the only mass being expelled is fuel.

## Use Cases for This Calculator

### Calculate Delta V for Orbital Maneuvers

Calculate the delta V required for orbital maneuvers such as changing orbit altitude, inclination, or performing rendezvous with another spacecraft. Input your current and desired orbital parameters to determine the delta V needed.

### Estimate Delta V for Interplanetary Trajectories

Estimate the delta V required to move between different celestial bodies in the solar system. Input the departure and destination celestial bodies to calculate the delta V needed for interplanetary trajectory maneuvers like Hohmann transfers or inclination changes.

### Compute Delta V for Trans Lunar Injection

Compute the delta V necessary for a spacecraft to perform a Trans Lunar Injection (TLI) maneuver to leave Earth’s orbit and head towards the Moon. Enter the spacecraft’s current orbit and the desired lunar trajectory to calculate the required delta V.

### Calculate Delta V for Spacecraft Landing

Calculate the delta V required for a spacecraft to perform a landing on a celestial body like the Moon or Mars. Input the descent trajectory parameters to determine the delta V needed to slow down and land safely on the surface.

### Determine Delta V for Spacecraft Ascent

Determine the delta V needed for a spacecraft to ascend from the surface of a celestial body back to orbit. Input the ascent trajectory parameters to calculate the required delta V for the spacecraft to overcome gravity and reach orbit.

### Estimate Delta V for Aerobraking Maneuvers

Estimate the delta V savings from aerobraking maneuvers by entering the spacecraft’s periapsis and apoapsis altitudes. Calculate the delta V reduction achieved from using a planet’s atmosphere to slow down and adjust orbit without using onboard propellant.

### Compute Delta V for Hohmann Transfer Orbit

Compute the delta V required for a spacecraft to transfer between two circular orbits using a Hohmann transfer orbit. Input the radii of the departure and destination orbits to calculate the delta V needed for the transfer maneuver.

### Calculate Delta V for Orbit Circularization

Calculate the delta V needed to circularize an elliptical orbit into a circular orbit. Input the spacecraft’s current orbit parameters to determine the delta V required to adjust the velocity and altitude for a circular orbit.

### Estimate Delta V for Gravity Assist Maneuvers

Estimate the delta V savings from gravity assist maneuvers by entering the spacecraft’s approach and departure velocities relative to a planet or moon. Calculate the delta V reduction achieved from utilizing a celestial body’s gravitational pull to boost the spacecraft’s velocity.

### Determine Delta V for Station Keeping

Determine the delta V required for station keeping maneuvers to maintain a spacecraft’s position within a specific orbital range. Input the desired orbital parameters to calculate the delta V needed for small adjustments to counteract orbital perturbations.