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 rim = 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 as: T-mog+ngt mo - mt Calculate the altitude (in km) at t = 135 s. ay (t)

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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 as:
T-mog+mgt
mo -mt
Calculate the altitude (in km) at t = 135 s.
ay (t)
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 as: T-mog+mgt mo -mt Calculate the altitude (in km) at t = 135 s. ay (t)
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