Classical Dynamics of Particles and Systems · Problem 9-65
Motion in a Noninertial Reference Frame — Marion & Thornton
Physics — Mechanics · rocket-motion-model
Problem
In a typical model rocket (Estes Alpha III) the Estes C6 solid rocket engine provides a total impulse of 8.5 N⋅s. Assume the total rocket mass at launch is 54 g and that it has a rocket engine of mass 20 g that burns evenly for 1.5 s. The rocket diameter is 24 mm. Assume a constant burn rate of the propellent mass (11 g), a rocket exhaust speed 800 m/s, vertical ascent, and drag coefficient cw=0.75. Determine
(a) The speed and altitude at engine burnout,
(b) Maximum height and time it occurs,
(c) Maximum acceleration,
(d) Total flight time, and
(e) Speed at ground impact.
Produce a plot of altitude and speed versus time. For simplicity, because the propellent mass is only 20\% of the total mass, assume a constant mass during rocket burning.