How Do You Calculate the Semi-Major Axis of a New Elliptical Orbit?

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Homework Help Overview

The discussion revolves around calculating the semi-major axis of a new elliptical orbit for a satellite that was initially in a geostationary orbit. The problem involves understanding the effects of a speed increase due to an engine firing, resulting in an elliptical orbit with a specified eccentricity.

Discussion Character

  • Exploratory, Conceptual clarification, Problem interpretation

Approaches and Questions Raised

  • Participants discuss the initial conditions of the satellite's orbit and the implications of the engine firing. There are attempts to relate the eccentricity and the semi-major axis, with some questioning how to derive the semi-major axis from the given parameters.

Discussion Status

Some participants have provided hints regarding the nature of the transfer between orbits, while others are seeking clarification on the terminology and the steps needed to calculate the semi-major axis. The conversation is ongoing, with multiple interpretations and approaches being explored.

Contextual Notes

There is a mention of the need for additional information to fully understand the problem setup, and participants are navigating the complexities of orbital mechanics without reaching a consensus on the next steps.

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Homework Statement


(a) A satellite is initially in a geostationary orbit around the Earth, so that the satellite always remains above the same point on the Earth’s equator. Show that the radius of the orbit is ##4.22\times 10^7##(b)An engine is briefly fired in the direction of the satellite’s motion, making the speed of the satellite suddenly increase to a speed ##v_p## and sending the satellite into an elliptical orbit with eccentricity ##e = 0.35##. What is the semi-major axis of the new orbit?

Homework Equations


Period: ##T=2\pi\sqrt{\frac{r^3}{GM_E}}##

Escape Velocity: ##V_{esc}=\sqrt{\frac{2GM_E}{r}}##

Eccentricity: ##e=\sqrt{1+\frac{2{\epsilon}L^2}{(GM_E)^2}}##

##e=\frac{r_a-r_b}{r_a+r_b}## where ##r_a=a(1-e)## and ##r_b=a(1+e)##

The Attempt at a Solution


Done the (a) part straight forward enough with the period formula.
So I subbed in my values to get:

##r=4.22\times 10^7 m##

##V_{esc}=4345 ms^{-1}##

What I don't understand is how to get the semi major axis. If someone could point me in the right direction that would be great. I think I have to get the new period of the orbit but I don't know how.
 
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teme92 said:

Homework Statement


An engine is briefly fired in the direction of the satellite’s motion, making the speed of the satellite suddenly increase to a speed ##v_p## and sending the satellite into an elliptical orbit with eccentricity ##e = 0.35##. What is the semi-major axis of the new orbit?

Homework Equations


Period: ##T=2\pi\sqrt{\frac{r^3}{GM_E}}##

Escape Velocity: ##V_{esc}=\sqrt{\frac{2GM_E}{r}}##

Eccentricity: ##e=\sqrt{1+\frac{2{\epsilon}L^2}{(GM_E)^2}}##

##e=\frac{r_a-r_b}{r_a+r_b}## where ##r_a=a(1-e)## and ##r_b=a(1+e)##

The Attempt at a Solution



So I subbed in my values to get:

##r=4.22\times 10^7 m##

##V_{esc}=4345 ms^{-1}##

What I don't understand is how to get the semi major axis. If someone could point me in the right direction that would be great. I think I have to get the new period of the orbit but I don't know how.
Have you posted the complete problem statement and/or all the information you were furnished?
 
Hey SteamKing I edited my post and put in more,I didn't think it was necessary sorry.
 
teme92 said:
Hey SteamKing I edited my post and put in more,I didn't think it was necessary sorry.
It normally wouldn't make a difference if this were Psychic Forums, rather than Physics Forums.

But, the additional information clarifies this thread greatly.
 
Ouch
 
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Hint: The transfer occur at perihelion.
 
What do you mean by transfer?
 
From the one orbit to the other.
 

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