- #1
randomking333
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The rocket equation given by Delta V = Ve ln (Mo/M) says that Ve is the exhaust velocity of the rocket.
The orbital velocity for Low Earth Orbit is about 7.8 Km/s. How then, is this velocity attained by a rocket which is fuelled only by a bipropellant rocket engine producing an exhaust velocity of 4.4 Km/s. Using conservation of momentum, the heavier mass of the rocket won't reach the velocity of the exhaust?
Pls explain to me how this works..
THanks in advance
The orbital velocity for Low Earth Orbit is about 7.8 Km/s. How then, is this velocity attained by a rocket which is fuelled only by a bipropellant rocket engine producing an exhaust velocity of 4.4 Km/s. Using conservation of momentum, the heavier mass of the rocket won't reach the velocity of the exhaust?
Pls explain to me how this works..
THanks in advance