Magnitude of thrust of rocket (q50)

AI Thread Summary
The discussion centers on the calculation of thrust for a rocket problem, specifically using the formula ma=(3000-800)*20 to arrive at a thrust of 44kN. The user questions whether this approach is correct, noting they did not utilize the thrust equations involving exhaust velocity and mass flow rate. Responses indicate that the problem may not fundamentally require a deep understanding of rocket dynamics. The consensus suggests that while the user's method yields a correct answer, it overlooks more comprehensive rocket thrust principles. Clarity on the appropriate approach to such problems is emphasized.
jack1234
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For this question:
http://tinyurl.com/ynkshx

I just use ma=(3000-800)*20 =44kN to get the answer, and the answer is correct.
and haven't make use of
thrust=exhause velocity * dm/dt
or
change in velocity=exhause velocity*ln|initial mass/final mass|

So, just want to confirm am I solved this problem with correct approach, if not, what is the correct solution?
 
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That's right. It's not really much of a rocket problem, is it?
 
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