Hi there I'm in desperate need for your help! I need to solve the rocket motion equation numerically in Maple or some other program. I'm having trouble writing the ODs in the program and setting up all their parameters. I have derived the rocket motion equation in a single dimension: [tex] \frac {d\vec v_r(t)}{dt} = - \, \frac {\dot m_e(t)} {m_r(t)} \, \vec v_e(t) [/tex] I assume that the change of mass is constant and the exhaust velocity is constant. Let's say that the rocket has an initial mass of 1 kg, an empty mass of 0.1 kg and the exhaust velocity 5 m/s.