Eccentricity of Elliptical Orbit given Apogee and Perigee Calculator

✖Apogee Radius in Elliptic Orbit represents the maximum distance between an orbiting body and the object it orbits.ⓘ Apogee Radius in Elliptic Orbit [r_e,apogee]			+10% -10%
✖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.ⓘ Perigee Radius in Elliptic Orbit [r_e,perigee]			+10% -10%

✖Eccentricity of Elliptical Orbit is a measure of how stretched or elongated the orbit's shape is.ⓘ Eccentricity of Elliptical Orbit given Apogee and Perigee [e_e]

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Eccentricity of Elliptical Orbit given Apogee and Perigee Solution

STEP 0: Pre-Calculation Summary

Formula Used

Eccentricity of Elliptical Orbit = (Apogee Radius in Elliptic Orbit-Perigee Radius in Elliptic Orbit)/(Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit)
e_e = (r_e,apogee-r_e,perigee)/(r_e,apogee+r_e,perigee)
This formula uses 3 Variables

Variables Used

Eccentricity of Elliptical Orbit - Eccentricity of Elliptical Orbit is a measure of how stretched or elongated the orbit's shape is.
Apogee Radius in Elliptic Orbit - (Measured in Meter) - Apogee Radius in Elliptic Orbit represents the maximum distance between an orbiting body and the object it orbits.
Perigee Radius in Elliptic Orbit - (Measured in Meter) - 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.

STEP 1: Convert Input(s) to Base Unit

Apogee Radius in Elliptic Orbit: 27110 Kilometer --> 27110000 Meter (Check conversion here)
Perigee Radius in Elliptic Orbit: 6778 Kilometer --> 6778000 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

e_e = (r_e,apogee-r_e,perigee)/(r_e,apogee+r_e,perigee) --> (27110000-6778000)/(27110000+6778000)

Evaluating ... ...

e_e = 0.599976392823418

STEP 3: Convert Result to Output's Unit

0.599976392823418 --> No Conversion Required

FINAL ANSWER

0.599976392823418 ≈ 0.599976 <-- Eccentricity of Elliptical Orbit

(Calculation completed in 00.004 seconds)

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< Elliptical Orbit Parameters Calculators

Eccentricity of Elliptical Orbit given Apogee and Perigee

LaTeX Go Eccentricity of Elliptical Orbit = (Apogee Radius in Elliptic Orbit-Perigee Radius in Elliptic Orbit)/(Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit)

Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity

LaTeX Go Apogee Radius in Elliptic Orbit = Angular Momentum of Elliptic Orbit^2/([GM.Earth]*(1-Eccentricity of Elliptical Orbit))

Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii

LaTeX Go Semi Major Axis of Elliptic Orbit = (Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit)/2

Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity

LaTeX Go Angular Momentum of Elliptic Orbit = Apogee Radius in Elliptic Orbit*Velocity of Satellite at Apogee

Eccentricity of Elliptical Orbit given Apogee and Perigee Formula

LaTeX Go

What is gravity ?

Gravity is a fundamental force of nature that governs the interactions between objects with mass or energy. It is responsible for the attraction between physical bodies and is one of the four fundamental forces in the universe, along with electromagnetism, the weak nuclear force, and the strong nuclear force.

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

Eccentricity of Elliptical Orbit given Apogee and Perigee calculator 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 calculate 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 calculate Eccentricity of Elliptical Orbit given Apogee and Perigee using this online calculator? To use this online calculator 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. Here is how the Eccentricity of Elliptical Orbit given Apogee and Perigee calculation can be explained with given input values -> 0.599976 = (27110000-6778000)/(27110000+6778000).

FAQ

What is Eccentricity of Elliptical Orbit given Apogee and Perigee?

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 and is represented as e_e = (r_e,apogee-r_e,perigee)/(r_e,apogee+r_e,perigee) or Eccentricity of Elliptical Orbit = (Apogee Radius in Elliptic Orbit-Perigee Radius in Elliptic Orbit)/(Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit). Apogee Radius in Elliptic Orbit represents the maximum distance between an orbiting body and the object it orbits & 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.

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

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 is calculated using 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 calculate Eccentricity of Elliptical Orbit given Apogee and Perigee, you need Apogee Radius in Elliptic Orbit (r_e,apogee) & Perigee Radius in Elliptic Orbit (r_e,perigee). With our tool, you need to enter the respective value for Apogee Radius in Elliptic Orbit & Perigee Radius in Elliptic Orbit and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Eccentricity of Elliptical Orbit?

In this formula, Eccentricity of Elliptical Orbit uses Apogee Radius in Elliptic Orbit & Perigee Radius in Elliptic Orbit. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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