Difference between revisions of "Propulsion"
| Line 17: | Line 17: | ||
ISP = Specific impulse (Seconds) | ISP = Specific impulse (Seconds) | ||
| − | n = efficiency of engine, for an [[ion thruster]] this is between 0,2 and 0,8, for a [[Propellant|chemical rocket]], essentially 1. | + | n = efficiency of engine, for an [[ion thruster]] this is between 0,2 and 0,8, for a [[Propellant|chemical rocket]], or [[Nuclear thermal propulsion|nuclear thermal rocket]], essentially 1. |
9,81 conversion factor | 9,81 conversion factor | ||
| Line 39: | Line 39: | ||
Ev = Exhaust velocity (m/s) | Ev = Exhaust velocity (m/s) | ||
| − | ===Velocity=== | + | ===Velocity (Rocket equation)=== |
V = Ev x ln(M<sub>o</sub>/M<sub>f</sub>) | V = Ev x ln(M<sub>o</sub>/M<sub>f</sub>) | ||
Revision as of 09:39, 9 August 2019
Contents
Theory
Propulsion equation
This is the equation that links the electrical power, the propulsive force and the ISP.
P = F x ISP *9,81 / 2n or P= F x Ev /2n
where:
P = power (Watts)
F = Engine force (Newtons)
ISP = Specific impulse (Seconds)
n = efficiency of engine, for an ion thruster this is between 0,2 and 0,8, for a chemical rocket, or nuclear thermal rocket, essentially 1.
9,81 conversion factor
Ev = Exhaust velocity (m/s)
Specific impulse
ISP = Ev / 9,81
ISP = Specific impulse (Seconds)
Ev = Exhaust velocity (m/s)
Fuel consumption
m = F/Ev
m = Fuel consumption (kg/s)
F = Force (Newtons)
Ev = Exhaust velocity (m/s)
Velocity (Rocket equation)
V = Ev x ln(Mo/Mf)
Ev = Exhaust velocity (m/s)
V = ship final velocity (m/s)
ln = natural logarithm
Mo = Initial mass of the ship (kg)
Mf = Final mass of the ship (kg)
The propulsive force is the force the engines produce to push the ship. This is factor of the available electrical energy, the engine efficiency and the propulsive system ISP and ejection velocity.
