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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, thrust constant with altitude, we can approximate the vertical acceleration (Assuming vertical thrust) as: ay (t) = T-mog+mgt mo -rnt After 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): (T//2) то - т (T//2)–mog+rmgt mo-mt a_(t) = а, (t) Calculate the magnitude of velocity (in km/s) at t = 133 sec.

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, thrust constant with altitude, we can approximate the vertical acceleration (Assuming vertical thrust) as: ay (t) = T-mog+mgt mo -rnt After 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): (T//2) то - т (T//2)–mog+rmgt mo-mt a_(t) = а, (t) Calculate the magnitude of velocity (in km/s) at t = 133 sec.

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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, thrust constant with altitude, we can approximate the vertical acceleration (Assuming vertical thrust) as: Т-тод+тgt ay (t) : mo -mt After 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+mgt mo -mt Ay (t) : Calculate the magnitude of velocity (in km/s) at t = 133 sec.
Transcribed Image Text: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, thrust constant with altitude, we can approximate the vertical acceleration (Assuming vertical thrust) as: Т-тод+тgt ay (t) : mo -mt After 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+mgt mo -mt Ay (t) : Calculate the magnitude of velocity (in km/s) at t = 133 sec.
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