77. (a) The thrust of the rocket is given by T= Rvrelwhere Ris the rate of fuel consumption and vrelis the speed of the exhaust gas relative to the rocket. For this problem R= 480 kg/s and vrel= 3.27 ×103m/s, so T=×=×480327 10157 1036kg sm sN.bgch..(b) The mass of fuel ejected is given by Mfuel= RtΔ, where Δtis the time interval of the burn. Thus, Mfuel= (480 kg/s)(250 s) = 1.20
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