Ion-propulsion rockets have been proposed for use in space. They employ atomic ionization techniques and nuclear energy sources to produce extremely high exhaust velocities, perhaps as great as 8.00 ✕ 106 m/s. These techniques allows a much more favorable payload-to-fuel ratio. To illustrate this fact: (a) Calculate the increase in velocity in m/s of a 23,000-kg space probe that expels only 40.0-kg of its mass at the given exhaust velocity. m/s (b) These engines are usually designed to produce a very small thrust for a very long time—the type of engine that might be useful on a trip to the outer planets, for example. Calculate the acceleration in m/s2 of such an engine if it expels 4.50 ✕ 10−6 kg/s at the given velocity, assuming the acceleration due to gravity is negligible. m/s2
Ion-propulsion rockets have been proposed for use in space. They employ atomic ionization techniques and nuclear energy sources to produce extremely high exhaust velocities, perhaps as great as 8.00 ✕ 106 m/s. These techniques allows a much more favorable payload-to-fuel ratio. To illustrate this fact: (a) Calculate the increase in velocity in m/s of a 23,000-kg space probe that expels only 40.0-kg of its mass at the given exhaust velocity. m/s (b) These engines are usually designed to produce a very small thrust for a very long time—the type of engine that might be useful on a trip to the outer planets, for example. Calculate the acceleration in m/s2 of such an engine if it expels 4.50 ✕ 10−6 kg/s at the given velocity, assuming the acceleration due to gravity is negligible. m/s2
Classical Dynamics of Particles and Systems
5th Edition
ISBN:9780534408961
Author:Stephen T. Thornton, Jerry B. Marion
Publisher:Stephen T. Thornton, Jerry B. Marion
Chapter9: Dynamics Of A System Of Particles
Section: Chapter Questions
Problem 9.64P
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Ion-propulsion rockets have been proposed for use in space. They employ atomic ionization techniques and nuclear energy sources to produce extremely high exhaust velocities, perhaps as great as 8.00 ✕ 106 m/s. These techniques allows a much more favorable payload-to-fuel ratio. To illustrate this fact:
(a)
Calculate the increase in velocity in m/s of a 23,000-kg space probe that expels only 40.0-kg of its mass at the given exhaust velocity.
m/s
(b)
These engines are usually designed to produce a very small thrust for a very long time—the type of engine that might be useful on a trip to the outer planets, for example. Calculate the acceleration in m/s2 of such an engine if it expels 4.50 ✕ 10−6 kg/s at the given velocity, assuming the acceleration due to gravity is negligible.
m/s2
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