Rocket science. A rocket has total mass $M_i=360 \mathrm{~kg}$, including 330 kg of fuel and oxidizer. In interstellar space, it starts from rest at the position $x=0$, turns on its engine at time $t=0$, and puts out exhaust with relative speed $v_r=$ $1500 \mathrm{~m} / \mathrm{s}$ at the constant rate $k=2.50 \mathrm{~kg} / \mathrm{s}$. The fuel will last for an actual burn time of $330 \mathrm{~kg} /(2.5 \mathrm{~kg} / \mathrm{s})=132 \mathrm{~s}$, but define a "projected depletion time" as $T_p=M_i / k=$ $360 \mathrm{~kg} /(2.5 \mathrm{~kg} / \mathrm{s})=144 \mathrm{~s}$ (which would be the burn time if the rocket could use its payload and fuel tanks, and even the walls of the combustion chamber as fuel). (a) Show that during the burn the velocity of the rocket as a function of time is given by
$$
v(t)=-v_r \ln \left(1-\frac{t}{T_p}\right)
$$
(b) Make a graph of the velocity of the rocket as a function of time for times running from 0 to 132 s . (c) Show that the acceleration of the rocket is $$
a(t)=\frac{v_{\varepsilon}}{T_p-t}
$$
(d) Graph the acceleration as a function of time. (e) Show that the position of the rocket is
$$
x(t)=v_q\left(T_p-t\right) \ln \left(1-\frac{t}{T_p}\right)+v_c t
$$
(f) Graph the position during the burn as a function of time.