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

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The discussion focuses on calculating the semi-major axis of a satellite's new elliptical orbit after a speed increase. Initially, the satellite is in a geostationary orbit with a radius of approximately 4.22 x 10^7 m. After firing its engine, the satellite enters an elliptical orbit with an eccentricity of 0.35. Participants discuss the need to determine the new orbital period to find the semi-major axis, emphasizing the relationship between eccentricity and the semi-major axis. The conversation highlights the importance of understanding orbital mechanics to solve the problem effectively.
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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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