Rocket Burning fuel causing change in mass

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SUMMARY

The discussion centers on calculating the final velocity of a rocket as it burns fuel, specifically addressing the changing mass of the rocket during fuel consumption. The initial scenario involves a 100 kg rocket with 50 kg of fuel, producing a thrust of 100 N. The derived formula for velocity, V=Ft/m, requires consideration of the rocket's mass change over time. The correct approach involves using the Rocket Equation and integrating a differential equation rather than relying on average mass, as acceleration is not constant during fuel burn.

PREREQUISITES
  • Understanding of Newton's laws of motion, specifically F=ma.
  • Familiarity with the Rocket Equation and its implications.
  • Basic calculus for integrating differential equations.
  • Knowledge of thrust and its relationship to mass and acceleration.
NEXT STEPS
  • Study the Rocket Equation in detail to understand its derivation and applications.
  • Learn about integrating differential equations in the context of changing mass systems.
  • Research real-world rocket fuel burn rates and their impact on thrust and acceleration.
  • Explore tutorials on rocket dynamics, such as those provided by NASA.
USEFUL FOR

Aerospace engineers, physics students, and anyone interested in rocket propulsion and dynamics will benefit from this discussion.

kaikalii
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I made up a scenario: Let's say I have a rocket at rest in space. The rocket initially weighs 100 kg, 50 kg of which is fuel. If the fuel burns at a constant rate of 1 kg/s and produces a thrust of 100 N out the back of the rocket, what will the rocket's velocity be after it runs out of fuel?

From F=ma and V=v0+at, I derived V=Ft/m. The force is 100 N, and it would take 50 s to burn 50 kg of fuel at 1 kg/s, so it would be V=100*50/m.

My question is: What would I use for the mass, since it is changing at the fuel burns? When I assumed that it was just the average mass, 75 kg, I got the final velocity ≈ 66.7 m/s. Am I supposed to just use the average mass since the fuel is burned at a constant rate? Does rocket fuel in the real world burn at a constant rate, or exponentially? If it was exponential, could I just use calculus to find the average mass and then plug it in?
 
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kaikalii said:
I made up a scenario: Let's say I have a rocket at rest in space. The rocket initially weighs 100 kg, 50 kg of which is fuel. If the fuel burns at a constant rate of 1 kg/s and produces a thrust of 100 N out the back of the rocket, what will the rocket's velocity be after it runs out of fuel?

From F=ma and V=v0+at, I derived V=Ft/m. The force is 100 N, and it would take 50 s to burn 50 kg of fuel at 1 kg/s, so it would be V=100*50/m.

My question is: What would I use for the mass, since it is changing at the fuel burns? When I assumed that it was just the average mass, 75 kg, I got the final velocity ≈ 66.7 m/s. Am I supposed to just use the average mass since the fuel is burned at a constant rate? Does rocket fuel in the real world burn at a constant rate, or exponentially? If it was exponential, could I just use calculus to find the average mass and then plug it in?

What you are asking about is known as the "Rocket Equation". Here is a tutorial from NASA:

http://exploration.grc.nasa.gov/education/rocket/rktpow.html

:smile:
 
kaikalii said:
My question is: What would I use for the mass

You need to use ## 50 + 50 ( 1 - \frac{t}{50} ) ##. Because the acceleration is not constant, you cannot use V=v0+at or work with an average mass though: you need to integrate a differential equation.
 

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