# A solid rocket motor is designed with a cylindrical end-burning propellant grain of length $1 \mathrm{~m}$ and diameter $32 \mathrm{~cm}$. The density of the propellant grain is $1750 \mathrm{~kg} / \mathrm{m}^{3}$. The specific impulse of the motor is $190 \mathrm{~s}$ and the acceleration due to gravity is $9.8 \mathrm{~m} / \mathrm{s}^{2}$. If the propellant burns for a period of $150 \mathrm{~s}$, then the thrust $(\mathrm{in} N)$ produced by the rocket motor is_____________

## Question ID - 155734 :- A solid rocket motor is designed with a cylindrical end-burning propellant grain of length $1 \mathrm{~m}$ and diameter $32 \mathrm{~cm}$. The density of the propellant grain is $1750 \mathrm{~kg} / \mathrm{m}^{3}$. The specific impulse of the motor is $190 \mathrm{~s}$ and the acceleration due to gravity is $9.8 \mathrm{~m} / \mathrm{s}^{2}$. If the propellant burns for a period of $150 \mathrm{~s}$, then the thrust $(\mathrm{in} N)$ produced by the rocket motor is_____________

3537

Answer Key : (1742 to 1752) -

1742 to 1752

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A liquid propellant rocket has the following component masses:
Mass of payload $=180 \mathrm{~kg}$
Mass of fuel $=470 \mathrm{~kg}$
Mass of oxidizer $=1170 \mathrm{~kg}$
Mass of structures $=150 \mathrm{~kg}$
Mass of guidance systems $=20 \mathrm{~kg}$

The effective exhaust velocity is $3136 \mathrm{~m} / \mathrm{s}$. The velocity increment (in $\mathrm{km} / \mathrm{s}$ ) of the rocket at burnout, while operating in outer space, is________________ 