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)

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)

College Physics

11th Edition

ISBN:9781305952300

Author:Raymond A. Serway, Chris Vuille

Publisher:Raymond A. Serway, Chris Vuille

Chapter1: Units, Trigonometry. And Vectors

Section: Chapter Questions

Problem 1CQ: Estimate the order of magnitude of the length, in meters, of each of the following; (a) a mouse, (b)...

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