Rocket Propulsion Demo

This is a very simple demonstration of the dynamics of rocket propulsion.  The user can define the masses of the vehicle, the payload, and the fuel load as well as the mass burn rate for the fuel and the exhaust velocity.  The current velocity and acceleration are shown numerically in the lower left and graphically with a cyan and magenta arrow along side the rocket.  Air resistance is not considered in this simple demo.

• F_net = m_total a
• (m_vehicle + m_payload + m_fuel) a = (Thrust - Weight)
• a = (thrust - (m_vehicle + m_payload + m_fuel) * g) / (m_vehicle + m_payload + m_fuel),

where Thrust = Burn Rate * v_exhaust.

The mass of the fuel is determined through simple Euler integration,

• Burn Rate = dm / dt
• => dm = Burn Rate * dt