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Eccentricity of Elliptical Orbit given Apogee and Perigee Formula

GoEccentricity of Orbit Formula

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Eccentricity of Elliptical Orbit is a measure of how stretched or elongated the orbit's shape is. Check FAQs

e e = \frac{r e,apogee - r e,perigee}{r e,apogee + r e,perigee}

e_e - Eccentricity of Elliptical Orbit?r_e,apogee - Apogee Radius in Elliptic Orbit?r_e,perigee - Perigee Radius in Elliptic Orbit?

Eccentricity of Elliptical Orbit given Apogee and Perigee Example

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Here is how the Eccentricity of Elliptical Orbit given Apogee and Perigee equation looks like with Values.

Here is how the Eccentricity of Elliptical Orbit given Apogee and Perigee equation looks like with Units.

Here is how the Eccentricity of Elliptical Orbit given Apogee and Perigee equation looks like.

0.6 = \frac{27110 - 6778}{27110 + 6778}

0.6 = \frac{27110km - 6778km}{27110km + 6778km}

0.6 = \frac{27110 - 6778}{27110 + 6778}

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Eccentricity of Elliptical Orbit given Apogee and Perigee Solution

Follow our step by step solution on how to calculate Eccentricity of Elliptical Orbit given Apogee and Perigee?

FIRST Step Consider the formula

e e = \frac{r e,apogee - r e,perigee}{r e,apogee + r e,perigee}

Next Step Substitute values of Variables

∴

e e = \frac{27110km - 6778km}{27110km + 6778km}

Next Step Convert Units

∴

e e = \frac{2.7E+7m - 6.8E+6m}{2.7E+7m + 6.8E+6m}

Next Step Prepare to Evaluate

∴

e e = \frac{2.7E+7 - 6.8E+6}{2.7E+7 + 6.8E+6}

Next Step Evaluate

∴

e e = 0.599976392823418

LAST Step Rounding Answer

∴

e e = 0.6

Eccentricity of Elliptical Orbit given Apogee and Perigee Formula Elements

Variables

Eccentricity of Elliptical Orbit

Eccentricity of Elliptical Orbit is a measure of how stretched or elongated the orbit's shape is.

Symbol: e_e

Measurement: NAUnit: Unitless

Note: Value should be between 0 to 1.

Formulas to find Eccentricity of Elliptical Orbit

Apogee Radius in Elliptic Orbit

Apogee Radius in Elliptic Orbit represents the maximum distance between an orbiting body and the object it orbits.

Symbol: r_e,apogee

Measurement: LengthUnit: km

Note: Value should be greater than 0.

Formulas to find Apogee Radius in Elliptic Orbit

Perigee Radius in Elliptic Orbit

Perigee Radius in Elliptic Orbit refers to the distance between the center of the Earth and the point in a satellite's orbit that is closest to the Earth's surface.

Symbol: r_e,perigee

Measurement: LengthUnit: km

Note: Value should be greater than 0.

Formulas to find Perigee Radius in Elliptic Orbit

Other Formulas to find Eccentricity of Elliptical Orbit

Go Eccentricity of Orbit

e e = \frac{d foci}{2 \cdot a e}

Other formulas in Elliptical Orbit Parameters category

Go Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity

h e = r e,apogee \cdot v apogee

Go Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity

r e,apogee = \frac{{h e}^{2}}{[GM.Earth] \cdot (1 - e e)}

Go Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii

a e = \frac{r e,apogee + r e,perigee}{2}

Go Azimuth-Averaged Radius Given Apogee and Perigee Radii

r θ = \sqrt{r e,apogee \cdot r e,perigee}

How to Evaluate Eccentricity of Elliptical Orbit given Apogee and Perigee?

Eccentricity of Elliptical Orbit given Apogee and Perigee evaluator uses Eccentricity of Elliptical Orbit = (Apogee Radius in Elliptic Orbit-Perigee Radius in Elliptic Orbit)/(Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit) to evaluate the Eccentricity of Elliptical Orbit, Eccentricity of Elliptical Orbit given Apogee and Perigee formula is defined as a measure of how elliptical an orbit is, with higher values indicating a more elongated shape and lower values indicating a more circular shape, providing a way to describe the shape of an elliptical orbit in space. Eccentricity of Elliptical Orbit is denoted by e_e symbol.

How to evaluate Eccentricity of Elliptical Orbit given Apogee and Perigee using this online evaluator? To use this online evaluator for Eccentricity of Elliptical Orbit given Apogee and Perigee, enter Apogee Radius in Elliptic Orbit (r_e,apogee) & Perigee Radius in Elliptic Orbit (r_e,perigee) and hit the calculate button.

FAQs on Eccentricity of Elliptical Orbit given Apogee and Perigee

What is the formula to find Eccentricity of Elliptical Orbit given Apogee and Perigee?

The formula of Eccentricity of Elliptical Orbit given Apogee and Perigee is expressed as Eccentricity of Elliptical Orbit = (Apogee Radius in Elliptic Orbit-Perigee Radius in Elliptic Orbit)/(Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit). Here is an example- 0.599976 = (27110000-6778000)/(27110000+6778000).

How to calculate Eccentricity of Elliptical Orbit given Apogee and Perigee?

With Apogee Radius in Elliptic Orbit (r_e,apogee) & Perigee Radius in Elliptic Orbit (r_e,perigee) we can find Eccentricity of Elliptical Orbit given Apogee and Perigee using the formula - Eccentricity of Elliptical Orbit = (Apogee Radius in Elliptic Orbit-Perigee Radius in Elliptic Orbit)/(Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit).

What are the other ways to Calculate Eccentricity of Elliptical Orbit?

Here are the different ways to Calculate Eccentricity of Elliptical Orbit-

Eccentricity of Elliptical Orbit=Distance Between Two Foci/(2*Semi Major Axis of Elliptic Orbit)

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