DEPARTURE

ARRIVAL

INITIAL ORBIT

FINAL ORBIT

ALTITUDE

km

ALTITUDE

km

ALTITUDE

km

Δ INCLINATION

PLANET

Delta-V is the velocity change necessary to perform orbital maneuvers. Each stage of the rocket has a delta-v that depends on the stage fuel mass and the engine specific impulse. Before building the rocket, it is important to calculate the amount of delta-v required to perform the mission using this calculator. Once you have planned your mission, it is necessary to know your rocket's delta-v.

GET DELTA-V FROM VEHICLE ASSEMBLY BUILDING

Enter the vehicle assembly building and start creating your rocket! On the right side of the screen you can find the stages of your aircraft, and the amount of delta-v for each stage.

Once you have finished, launch your rocket. On the left side of the screen, there is a real time delta-v marker for each stage.

GET DELTA-V FROM THE FORMULA

The following equation returns the amount of delta-v per stage. To use this formula, you must know the stage mass with fuel, the mass without fuel and the specific impulse of the engine.

ΔV = ln(m0/mf) * Isp * g

m0 = Stage mass with fuel.

mf = Stage mass without fuel.

Isp = Engine specific impulse.

g = Kerbin surface gravity.

**KERBAL SPACE PROGRAM DELTA-V RESULTS**

KSP Delta-V Planner calculates the Delta-V for your next mission. Any orbit within the SOI and greater than the low orbit can be used if the departure and arrival planet are the same.

4711 m/s

**Planner values can be reduced to 0 by aerobreaking, so they are not included in the final result.

1

REACH LOW ORBIT 3400 m/s

2

ESCAPE BURN 931m/s

3

INTERCEPT 130m/s

4

ELLIPTICAL LO-SOI 250m/s

5

LANDING**

6

TOTAL 4711m/s

7

MAXIMUM PLANE CHANGE 10m/s

8

9

INITIAL ORBIT

FINAL ORBIT

Planet mass, SOI, stationary orbit, rotation period and equatorial radius can also be obteined at the Tracking Station.

Clicking on "Calculate" will display the results in this section of the page. Any suggestion is welcome. If you have identified an error, you can report it using the bottom right icon.

**HOW TO USE THIS TOOL**

DEPARTURE AND ARRIVAL PLANET ARE THE SAME

Select the initial and final orbit or any other altitude if it is within the SOI and higher than the atmosphere. This maneuvers are performed using Hohmann transfers in two steps.

When final orbit altitude higher than the initial orbit:

**First maneuver.** Burn prograde until reaching an elliptical orbit whose apoapsis is the altitude of the desired orbit.

**Second maneuver.** Burn prograde at the apoapsis of the elliptical orbit until reaching the final orbit.

If the final orbit is lower than the initial orbit:

**First step.** Burn retrograde until reaching an elliptical orbit whose periapsis is the altitude of the desired orbit.

**Second step.** Burn retrograde at the periapsis of the elliptical orbit until reaching the final orbit.