Velocity change by running engine for 1 year

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Homework Help Overview

The problem involves a rocket engine with a specified exhaust velocity and mass flow rate, asking for the thrust produced and the change in velocity achievable over one year of continuous operation. The context is within the field of rocket propulsion and dynamics.

Discussion Character

  • Mixed

Approaches and Questions Raised

  • Participants discuss the calculation of thrust and the implications of mass loss over time. There are differing opinions on whether to treat the mass as constant or to account for the decreasing mass of the rocket due to fuel consumption.

Discussion Status

Multiple interpretations of the problem are being explored, with some participants suggesting the use of the thrust-to-mass ratio for acceleration while others advocate for the logarithmic mass ratio approach. There is no explicit consensus on which method to adopt for calculating the change in velocity.

Contextual Notes

Participants note that the assumption of constant mass may not yield accurate results, as a significant portion of the rocket's mass will be expended during operation. There is also a lack of clarity regarding the treatment of gravitational forces in the calculations.

pridet8
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Homework Statement



A rocket engine has an exhaust velocity of 20,000 m/sec. The mass flow (dm/dt) rate is 1 milligram per second.
a) What is the thrust produced by the engine?
b) The engine propels a 200 kg space craft. What change in velocity is achievable by running the engine continuously for one solid year?
note1: assume a constant mass for the system.
note2: One year = 31.56 x 10^6 seconds.

Homework Equations


Thrust = -Ve*(dm/dt)

Change in velocity = V - Vo = Ve*(ln Mo/M)


The Attempt at a Solution


a) Thrust = 20000m/s *(.000001kg/s) = .02N

b) 20000*(ln 200kg/31.56kg) = 36928.6 m/s^2

My question: Part A I believe is right but part b I am having trouble believing. Should I just keep it simple since the mass is constant at 200 kg? Thus giving a new equation which would be
a = (Thrust - W)/M

which is (.02N - (200kg*9.8m/s2))/200kg = 9.79m/s^2
 
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in V - Vo = Ve * ln(Mo/M), Mo is the initial mass of the rocket including propellant, and M is the final mass of the rocket including leftover propellant.

There's no mention in the problem that you should account for the gravity of a planet or start, so you can use a = (Thrust)/M. You still have to compute the velocity change from the accelerations and the duration.

The assumption that the mass is constant won't give an accurate solution, since more than 30 kg of the 200 kg will disappear.
 
So then the velocity change will be:

a= Thrust/M

Where Thrust = .02 N and M = 200kg
= .0001 m/s^2

Velocity @ 3.156 x 10^6 seconds = (.0001m/s^2)*500s = 315.6m/s

Then the velocity change will be from 20,000m/s - 315.6m/s = 19684.4 m/s
 
******Velocity @ 3.156 x 10^6 seconds = (.0001m/s^2)*500s = 315.6m/s********

I meant (.0001m/s^2)*3.156 x 10^6
 
pridet8 said:
******Velocity @ 3.156 x 10^6 seconds = (.0001m/s^2)*500s = 315.6m/s********

I meant (.0001m/s^2)*3.156 x 10^6

It's actually 31.56 x 10^6 second.

I don't understand why you subtracted the velocity change from 20000 m/s. What is wanted is just the velocity change.
 
So which one should I use then?

The ln with mass ratio which gave me an answer of: 3411.02 m/s

Or the a = f/m which gave me a change of : 3156 m/s
 
pridet8 said:
So which one should I use then?

The ln with mass ratio which gave me an answer of: 3411.02 m/s

Or the a = f/m which gave me a change of : 3156 m/s

As I said: The assumption that the mass is constant won't give an accurate solution, since more than 30 kg of the 200 kg will disappear.
 

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