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Question

In outer space where gravity is zero, acceleration of a rocket of mass 100 kg is $12 m / s^{2}$ . If velocity of exhaust gases relative to the rocket is 300 m/s, then rate of consumption of fuel is

Moderate

Solution

T = Thrust generated = 100 x 12 N = 1200 N
Now, $V_{r} \frac{dm}{dt} = T \Rightarrow \frac{dm}{dt} = \frac{T}{V_{r}} = \frac{1200}{300} kg / s = 4 kg / s$

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