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Trouble with a Rocket Propulsion question (Variable Mass & Momentum)
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[QUOTE="vparam, post: 6613610, member: 699919"] [B]Homework Statement:[/B] A fully fueled rocket has a mass of 21,000 kg, of which 15,000 kg is fuel. The burned fuel is spewed out the rear at a rate of 190 kg/s with a speed of 2800 m/s relative to the rocket. If the rocket is fired vertically upward calculate its final velocity at burnout (all fuel used up). Ignore air resistance and assume g is a constant 9.80 m/s^2. [B]Relevant Equations:[/B] M * dv/dt = ∑F_ext + v_rel * dM/dt I chose to set the upwards direction to be positive and dM/dt = R = 190 kg/s, so I can solve the problem in variable form and plug in. With the only external force being gravity, this gives M(t) * dv/dt = -M(t) * g + v_rel * R where M(t) is the remaining mass of the rocket. Rearranging this equation gives: dv/dt = -((v_rel * R)/M(t)) - g Since R is constant, M(t) = M_0 - R * t, where M_0 is the initial mass of the rocket. Plugging in gives: dv/dt = -((v_rel * R)/(M_0 - R * t)) - g. Solving as a separable differential equation, I arrived at the answer (assuming v = 0 at t = 0): v(t) = -g * t + v_rel * ln(M_0 - R * t). However, after plugging in values, I'm not able to get the correct answer. The solution instead has a different equation for v(t): v(t) = -g * t + v_rel * ln(M/M_0). Any help about where I could be going wrong with the physical setup or the math of this problem would be much appreciated. Thanks in advance! [/QUOTE]
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Trouble with a Rocket Propulsion question (Variable Mass & Momentum)
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