- #1
Serena_Greene
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I'm tyring to find the formula that is used to calculate rocket thrust.
Thanks
Serena
Thanks
Serena
Tide, Just as a quick aside, I would think that your assertion is not a special case at all, but the norm. Most rockets do not have throttling capabilities or variable exit geometries so the assumption of constant exhaust mass flow, I think, is a good one.Tide said:Try setting dm/dt to a constant value to handle the special case where the exhaust leaves at a constant rate.
The formula for rocket thrust is F = m x a, where F is the thrust force, m is the mass of gas being expelled from the rocket, and a is the acceleration of the gas.
The formula for rocket thrust represents Newton's Third Law of Motion, which states that for every action, there is an equal and opposite reaction.
The mass of gas being expelled from the rocket is calculated by multiplying the rate of fuel burn (dm/dt) by the time (t) the rocket is expelling the gas, or m = dm/dt x t.
The acceleration of the gas in the rocket is affected by the rate of fuel burn, the type and amount of propellant used, and the design and efficiency of the rocket engine.
Rocket thrust is typically measured in Newtons (N) or pounds of force (lbf). It can also be measured in specific impulse (Isp), which is a measure of the efficiency of the rocket engine.