The objective is to find out the time at which the rocket reaches a speed of 1000m/s (3600km/hr). Analysis We know the following: * Initial mass of the rocket and fuel, 160000kg, or 160 metric tons. * Fuel combustion exhaust velocity relative to the rocket is assumed to be constant at 2200m/s * Fuel combustion rate is a constant 2680kg/sec2 * Gravitational acceleration is 9.8m/sec2 The following formula is used to calculate the upward velocity of the rocket while the fuel is providing thrust: V = u*loge(m0/(m0-qt))-g*t Now substituting the values in the formula we get: 1000 = 2200*log(160000 / (160000 – 9.8*t)) – 9.8*t which is too difficult to solve analytically so we use Bisection root-finding method. The source code is for a program that solves this problem with the given parameters.

ProjectCode
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