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Statement of a problem № 3179

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For the Centaur rocket use the data given below: Initial mass m0 = 2.72x10^6 kg Mass at burn-out velocity, mB = 2.52x10^6 kg Relative velocity of exhaust gases vr = 55 km/s Rate of change of mass, dm/dt = 1290 kg/s. Find (a) the rocket thrust, (b) net acceleration at the beginning, (c) time to reach the burn-out velocity, (d) the burn-out velocity.

Solution:
For the Centaur rocket use the data given below: Initial mass m0 = 2.72x10^6 kg

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