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thrust of a rocket = -uR = Th
u = velocity of exhaust relative to rocket
R = rate of mass ejection
we need R
Newton's II law: F̂ᵣₑ = mâ
Th - mg = ma (gravity free, hence g = 0)
=> Th = ma = 240000 N = uR = 2000R
=> R = 240000/2000 = 120 kg/s
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