What is the equation for the velocity of a rocket as a function of time?

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Homework Help Overview

The discussion revolves around deriving the equation for the velocity of a rocket as a function of time, specifically in the context of rocket propulsion and momentum conservation. The problem involves a rocket with a specific mass and fuel consumption rate, and participants are analyzing the equations related to momentum before and after fuel is burned.

Discussion Character

  • Exploratory, Mathematical reasoning, Assumption checking

Approaches and Questions Raised

  • Participants are attempting to derive the relationship between the change in velocity and the mass of fuel burned, questioning the steps taken to arrive at specific equations. There is discussion about rearranging terms and clarifying the meaning of constants in the derived equations.

Discussion Status

There is an ongoing exploration of the mathematical relationships involved, with some participants questioning the correctness of quoted equations and the assumptions behind them. Guidance has been offered regarding the integration of terms, but no consensus has been reached on the final form of the equations.

Contextual Notes

Participants are working with specific values for mass and fuel consumption, and there is uncertainty regarding the interpretation of constants in the equations. The discussion reflects a learning environment where assumptions and definitions are being critically examined.

Samuelriesterer
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I am stuck on how my teacher got to the last equation in #4.

Problem Statement:

A 2,000 kg rocket carrying 3000 kg of fuel is drifting in space when it fires its engine. While operating, the rocket engine burns 20 kg of fuel per second and the exhaust gasses leave the rocket at an exhaust velocity of Ve =300 m/s relative to the rocket.

Relative equations:

p = mv

Work done:

1) At some moment while the engine is firing, the rocket has mass M and is moving at velocity v, as is all the fuel it contains. After a short time Δt, the rocket has burned an amount of fuel Δm which leaves the rocket at velocity ve relative to the rocket. Write expressions for the total momentum before Δm is burned and after Δm is exhausted.

pi = MVi
pf = (M - ∆M)(Vi + ∆V) + ∆M(Vi –Ve)

2) Set the two expressions in (1) equal and expand any products of sums and differences.

(M - ∆M)(Vi + ∆V) + ∆M(Vi –Ve) = MVi →
M Vi - Vi∆M + M∆V +∆M∆V + ∆M Vi - ∆MVe = M Vi →
- Vi∆M + M∆V +∆M∆V + ∆M Vi - ∆MVe = 0 →
M∆V +∆M∆V - ∆MVe = 0

3) Delete any terms which are a product of two factors of Δm, Δv in any combination (they will be much smaller than other terms as Δt shrinks to zero).

M∆V +∆M∆V - ∆MVe = 0 →
M∆V - ∆MVe = 0 →
M∆V = ∆MVe

4) Now take a limit as Δt shrinks to zero and integrate from t = 0 to t to find an expression for the velocity of the rocket as a function of time.

M∆V = ∆MVe →

(M∆V)/(M∆t) = (∆MVe)/(M∆t) →

∆V/∆Vt = (∆MVe)/(M∆t) →

∆V/∆Vt = (Ve/M) (∆M/∆t) - Not entirely sure how he came to this or to the next equation:

V = Kt + Vi

5) Integrate from Δm = 0 to 3000 kg (t= 0 to [3000 kg/20kg/s]). to find the change in the velocity of the rocket.
 
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Samuelriesterer said:
∆V/∆Vt = (∆MVe)/(M∆t) →

∆V/∆Vt = (Ve/M) (∆M/∆t) - Not entirely sure how he came to this
It's a simple rearrangement of terms:
##\frac{\Delta M V_e}{M \Delta t} =
\frac{V_e \Delta M }{M \Delta t}= \frac{V_e}{M} \frac{\Delta M }{ \Delta t}##
But don't you mean
##\frac{\Delta V}{ \Delta t} = \frac{V_e}{M} \frac{\Delta M }{ \Delta t}##?
Samuelriesterer said:
or to the next equation:
V = Kt + Vi
Are you sure you've quoted that correctly? What is K here? That equation looks like uniform acceleration, which is not what will happen.
 
Sorry, the K I believe is a constant
 
Samuelriesterer said:
Sorry, the K I believe is a constant
Well, as I said, that'd be wrong.
You have ##
\frac{d V}{d t} = \frac{V_e}{M} \frac{d M }{d t}##
What do you get by integrating that?
 
##tV + C = (tVe)/(M) + C## ?
 
Samuelriesterer said:
##tV + C = (tVe)/(M) + C## ?
No. You have
##\int \frac{d V}{d t}dt = \int \frac{V_e}{M} \frac{d M }{d t}dt##
Simplify both sides.
 

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