Here is the data I have been given;
mass = 3.4*10^6 kg (at lift off)
mass of first stage propellants = 2.0*10^6
propellant consumption rate = 1.4*10^4 kg/s
g = 9.8 m/s/s
Find the thrust of the engines at lift-off.
2. Relevant equations
a = T-mg/m
3. The attempt at a solution
So mg = (3.4*10^6)*9.8 = 3.332*10^7
m = 3.4*10^6
∴a = T-3.332*10^7/3.4*10^6
I have two unknowns here, I thought there might be a way of finding either acceleration or thrust using mass, propellant mass and propellant consumption?
I have searched through my HSC texts and haven’t been able to find an equation where I can find ‘a’ or ‘T’ without needing one to find the other.