Aerospace Engineering > GATE 2015 > Rocket Performance
A liquid propellant rocket has the following component masses:
Mass of payload =180 kg
Mass of fuel =470 kg
Mass of oxidizer=1170 kg
Mass of structures=150 kg
Mass of guidance systems =20 kg
The effective exhaust velocity is 3136 m/s. The velocity increment (in km/s) of the rocket at burnout, while operating in outer space, is
Mass of payload =180 kg
Mass of fuel =470 kg
Mass of oxidizer=1170 kg
Mass of structures=150 kg
Mass of guidance systems =20 kg
The effective exhaust velocity is 3136 m/s. The velocity increment (in km/s) of the rocket at burnout, while operating in outer space, is
Correct : 5.42 to 5.48
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