Why is this wrong THRUST? i showed work

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The discussion focuses on a rocket physics problem involving thrust calculations for a deep space mission. The user attempts to determine the required amount of fuel and oxidizer using the equation vf = ve ln(mi/mf), where vf is the final velocity, ve is the exhaust speed, mi is the initial mass, and mf is the final mass. The user mistakenly calculates the total mass instead of isolating the fuel mass needed. Clarification is sought on how to correctly interpret the problem to find the specific fuel and oxidizer requirements. Accurate calculations are essential for determining the effective propulsion needed for the mission.
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why is this wrong...THRUST?? i showed work!

Homework Statement



A rocket for use in deep space is to have the capability of boosting a total load (payload plus the rocket frame and engine) of 2.25 metric tons to a speed of 10 000 m/s.
If a different fuel and engine design could give an exhaust speed of 4600 m/s, what amount of fuel and oxidizer would be required for the same task?
metric tons

Homework Equations



vf=ve ln(mi/mf)

The Attempt at a Solution



10000=4600ln(x/2.25)
x= 19.71
but its wrong. can you help?
 
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The question asks for the amount of fuel and oxidizer, not the total mass of the vehicle.
 

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