The formula for eccentricity, e, of an orbit is given below, where a is the length of the semi-major axis and b is the length of the major axis.



Solve the formula for eccentricity for the length of the semi-major axis.



The correct equation for the length of the semi-major axis is equation .

When the length of the major axis is 4 inches and the eccentricity of the orbit is , the length of the semi-major axis is inches (round to the nearest hundredth).

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Answer:

Part 1) [tex]a=\frac{b}{\sqrt{1-e^2}}[/tex]

Part 2) [tex]a=4.62\ in[/tex]

Step-by-step explanation:

The correct question in the attached figure

Part 1)

we have the formula

[tex]e=\sqrt{1-\frac{b^2}{a^2}}[/tex]

where

e the eccentricity

a is the length of the semi-major axis

b is the length of the major axis

solve for a

That means

Isolate the variable a

[tex]e=\sqrt{1-\frac{b^2}{a^2}}[/tex]

squared both sides

[tex]e^2=1-\frac{b^2}{a^2}[/tex]

subtract 1 both sides

[tex]e^2-1=-\frac{b^2}{a^2}[/tex]

Multiply both sides by a^2

[tex](e^2-1)a^2=-b^2[/tex]

Divide both sides by (e^2-1)

[tex]a^2=\frac{-b^2}{e^2-1}[/tex]

Rewrite

[tex]a^2=\frac{-b^2}{-(1-e^2)}[/tex]

[tex]a^2=\frac{b^2}{(1-e^2)}[/tex]

square root both sides

[tex]a=\sqrt{\frac{b^2}{(1-e^2)}}[/tex]

simplify

[tex]a=\frac{b}{\sqrt{1-e^2}}[/tex]

Part 2) we have

[tex]b=4\ in\\e=1/2[/tex]

Solve for a

substitute in the formula of part 1)

[tex]a=\frac{4}{\sqrt{1-(1/2)^2}}=4.62\ in[/tex]

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