This is the master list for equations!
- 1 Δ v
- 2 Rocket Efficiency
- 3 Exhaust Velocity of Propellant
- 4 Thrust to Weight
- 5 Average ISP
- 6 Fuel Consumption Rate
- 7 Burn Time
- 8 Suicide burn
- 9 Orbital Velocity
- 10 Orbital Period
- 11 Kepler's Third Law of Planetary Motion
- 12 SOI Radius
- 13 Max Payload
- 14 Eccentricity
- M t is total mass.
- M d is total mass minus fuel mass.
- "In" is a natural logarithm.
See the Δ v page for a comprehensive explanation of Δ v.
According to Stef:
Top to Bottom
- E_r is Efficiency of the rocket, and
- M_n < is Mass in tonnes of the succeeding stages.
Bottom to Top
Exhaust Velocity of Propellant
is the exhaust velocity of your propellant, and
is the standard gravity, which on Earth is:
Thrust to Weight
is force of thrust in kilonewtons (kN) and
is your rocket's mass in metric tons (t).
is the force of gravity. For example, on Earth , it is 9.8 m / s 2 .
If the TWR is greater than or equal to 1 your rocket will lift off the ground.
is the sum of all the forces, and
is the fuel consumption rate in kg / s.
Average ISP can also be calculated from each engine:
is the force in kilonewtons of the n th engine, including duplicates, and
is the ISP of the n th engine.
Fuel Consumption Rate
The same fuel flow rate.
Mass for that Time
Kepler's Third Law of Planetary Motion
R = Required Δ v for Mission
X = Max Payload in tonnes
E = Eccentricity
rmax = Apoapsis
rmin = Periapsis
Please allow a margin of error of 10% as well as user errors.