Description: 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.
To Search:
File list (Check if you may need any files):
ProjectCode
...........\.dep.inc
...........\build
...........\.....\Debug
...........\.....\.....\Cygwin_4.x-Windows
...........\.....\.....\..................\main.o
...........\.....\.....\..................\main.o.d
...........\dist
...........\....\Debug
...........\....\.....\Cygwin_4.x-Windows
...........\....\.....\..................\numericalproject.exe
...........\main.cpp
...........\Makefile
...........\nbproject
...........\.........\configurations.xml
...........\.........\Makefile-Debug.mk
...........\.........\Makefile-impl.mk
...........\.........\Makefile-Release.mk
...........\.........\Makefile-variables.mk
...........\.........\Package-Debug.bash
...........\.........\Package-Release.bash
...........\.........\private
...........\.........\.......\configurations.xml
...........\.........\.......\Makefile-variables.mk
...........\.........\.......\private.xml
...........\.........\project.xml
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