Rocket propulsion equation: what's the error here?

In summary, the conversation discusses the equation for rocket motion which involves the change in momentum and velocity, as well as external forces acting on the rocket. The speaker realizes their mistake and corrects it, emphasizing that momentum is conserved and therefore the sum of external forces is equal to zero. It is also noted that total, not partial, derivatives should be used in the equation.
  • #1
yucheng
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Equation for rocket motion:
$$\frac{d \mathbf{P}}{d t} = M\frac{d \mathbf{v}}{d t} - \mathbf{u}\frac{d M}{d t}$$

But $$\mathbf{F}=\frac{d \mathbf{P}}{d t}=M\frac{d \mathbf{v}}{d t}$$

So $$M\frac{d \mathbf{v}}{d t} = M\frac{d \mathbf{v}}{d t} - \mathbf{u}\frac{d M}{d t}$$

And $$- \mathbf{u}\frac{d M}{d t}=0$$

Now, what's wrong? Thanks in advance!
 
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  • #2
Ok, I messed up. Momentum is conserved. So ##\mathbf{F}=0##!
 
  • #3
yucheng said:
Ok, I messed up. Momentum is conserved. So ##\mathbf{F}=0##!
I am glad you sorted that out because it saved me some writing. More generally ##\vec F## represents the sum of external forces acting on the rocket. Also, you should be using total, not partial derivatives here.
 
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1. What is the rocket propulsion equation and how is it used?

The rocket propulsion equation, also known as the Tsiolkovsky rocket equation, is a mathematical formula that describes the motion of a rocket in terms of its mass, velocity, and the amount of propellant it carries. It is used to calculate the velocity change (delta-v) that a rocket can achieve based on its initial mass, final mass, and specific impulse of its propellant.

2. What are the variables in the rocket propulsion equation?

The variables in the rocket propulsion equation are:

  • Initial mass (m0): the total mass of the rocket at the beginning of its flight, including the mass of the propellant.
  • Final mass (mf): the total mass of the rocket at the end of its flight, after all propellant has been expended.
  • Exhaust velocity (ve): the speed at which propellant is expelled from the rocket.
  • Specific impulse (Isp): a measure of the efficiency of a rocket's propellant, defined as the thrust produced per unit of propellant mass consumed.
  • Gravity constant (g): the acceleration due to gravity, which varies depending on the location of the rocket.

3. What is the error in the rocket propulsion equation?

The error in the rocket propulsion equation is that it assumes a constant exhaust velocity and specific impulse throughout the entire flight of the rocket. In reality, these values may change due to factors such as air resistance, variations in atmospheric pressure, and changes in the rocket's altitude and velocity.

4. How does the error in the rocket propulsion equation affect the accuracy of calculations?

The error in the rocket propulsion equation can significantly affect the accuracy of calculations, especially for longer and more complex rocket flights. The assumption of constant exhaust velocity and specific impulse can lead to overestimation or underestimation of the actual velocity change and can also affect the trajectory of the rocket.

5. How can the error in the rocket propulsion equation be minimized?

The error in the rocket propulsion equation can be minimized by taking into account the changing values of exhaust velocity and specific impulse throughout the flight of the rocket. This can be done by breaking the flight into smaller segments and calculating the values at each segment. Additionally, using more advanced equations that account for these variations can also help reduce the error.

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