Consider a Falcon 9, a two-state-to-orbit launch vehicle. The take-off mass of Falcon 9 is Mto = 550,000 kg, the first stage fuel burn rate is m= 2500 kg/s over a maximum of 160 s, and constant thrust of T = 7500 kN. Making a lot of simplifying assumptions including constant gravity, no aerodynamic drag, thrustconstant with altitude, we can approximate the vertical acceleration (Assuming vertical thrust) as:Т-тод+тgtay (t) :mo -mtAfter 60 s, lets assumed that the rocket is turned by 45 deg so that the equations for acceleration become (assuming flat Earth, i.e., gravity is still in y-direction):az (t) :(T//2)mo -mt(T//2)-mog+mgtmo -mtAy (t) :Calculate the magnitude of velocity (in km/s) at t = 133 sec.

Given: The take-off mass of Falcon 9 is m0=550,000 kg The fuel burn rate is m˙=2500 kg/s The…

Answered: Consider a Falcon 9, a…

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