Eccentricity of Orbit Calculator

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The Two Body Problem

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Elliptical Orbits

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Fundamental Parameters

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Elliptical Orbit Parameters

Orbital Position as Function of Time

✖Distance Between Two Foci is defined as the distance between the two focus, F1 and F2.ⓘ Distance Between Two Foci [d_foci]			+10% -10%
✖Semi Major Axis of Elliptic Orbit is half of the major axis, which is the longest diameter of the ellipse describing the orbit.ⓘ Semi Major Axis of Elliptic Orbit [a_e]			+10% -10%

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

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Formula

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Eccentricity of Orbit

Formula

`"e"_{"e"} = "d"_{"foci"}/(2*"a"_{"e"})`

Example

`"0.602125"="20400km"/(2*"16940km")`

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Eccentricity of Orbit Solution

STEP 0: Pre-Calculation Summary

Formula Used

Eccentricity of Elliptical Orbit = Distance Between Two Foci/(2*Semi Major Axis of Elliptic Orbit)
e_e = d_foci/(2*a_e)
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.
Distance Between Two Foci - (Measured in Meter) - Distance Between Two Foci is defined as the distance between the two focus, F1 and F2.
Semi Major Axis of Elliptic Orbit - (Measured in Meter) - Semi Major Axis of Elliptic Orbit is half of the major axis, which is the longest diameter of the ellipse describing the orbit.

STEP 1: Convert Input(s) to Base Unit

Distance Between Two Foci: 20400 Kilometer --> 20400000 Meter (Check conversion here)
Semi Major Axis of Elliptic Orbit: 16940 Kilometer --> 16940000 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

e_e = d_foci/(2*a_e) --> 20400000/(2*16940000)

Evaluating ... ...

e_e = 0.602125147579693

STEP 3: Convert Result to Output's Unit

0.602125147579693 --> No Conversion Required

FINAL ANSWER

0.602125147579693 ≈ 0.602125 <-- Eccentricity of Elliptical Orbit

(Calculation completed in 00.004 seconds)

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Created by Karavadiya Divykumar Rasikbhai

Hindustan Institute of Technology and Science (HITS), Chennai, Indian

Karavadiya Divykumar Rasikbhai has created this Calculator and 10+ more calculators!

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Indian Institute of Information Technology, Design And Manufacturing (IIITDM ), Jabalpur

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< 17 Elliptical Orbit Parameters Calculators

True Anomaly in Elliptic Orbit Given Radial Position, Eccentricity, and Angular Momentum

Go True Anomaly in Elliptical Orbit = acos((Angular Momentum of Elliptic Orbit^2/([GM.Earth]*Radial Position in Elliptical Orbit)-1)/Eccentricity of Elliptical Orbit)

Time Period of Elliptical Orbit given Semi-Major Axis

Go Time Period of Elliptic Orbit = 2*pi*Semi Major Axis of Elliptic Orbit^2*sqrt(1-Eccentricity of Elliptical Orbit^2)/Angular Momentum of Elliptic Orbit

Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum

Go Radial Velocity of Satellite = [GM.Earth]*Eccentricity of Elliptical Orbit*sin(True Anomaly in Elliptical Orbit)/Angular Momentum of Elliptic Orbit

Eccentricity of Elliptical Orbit given Apogee and Perigee

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)

Time Period for One Complete Revolution given Angular Momentum

Go Time Period of Elliptic Orbit = (2*pi*Semi Major Axis of Elliptic Orbit*Semi Minor Axis of Elliptic Orbit)/Angular Momentum of Elliptic Orbit

Elliptical Orbit Time Period given Angular Momentum and Eccentricity

Go Time Period of Elliptic Orbit = (2*pi)/[GM.Earth]^2*(Angular Momentum of Elliptic Orbit/sqrt(1-Eccentricity of Elliptical Orbit^2))^3

Time Period of Elliptical Orbit given Angular Momentum

Go Time Period of Elliptic Orbit = (2*pi)/[GM.Earth]^2*(Angular Momentum of Elliptic Orbit/sqrt(1-Eccentricity of Elliptical Orbit^2))^3

Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity

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

Specific Energy of Elliptic Orbit given Angular Momentum

Go Specific Energy of Elliptical Orbit = -1/2*[GM.Earth]^2/Angular Momentum of Elliptic Orbit^2*(1-Eccentricity of Elliptical Orbit^2)

Azimuth-Averaged Radius Given Apogee and Perigee Radii

Go Azimuth Averaged Radius = sqrt(Apogee Radius in Elliptic Orbit*Perigee Radius in Elliptic Orbit)

Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii

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

Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity

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

Radial Velocity in Elliptic Orbit given Radial Position and Angular Momentum

Go Radial Velocity of Satellite = Angular Momentum of Elliptic Orbit/Radial Position in Elliptical Orbit

Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity

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

Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius

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

Eccentricity of Orbit

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

Specific Energy of Elliptic Orbit given Semi Major Axis

Go Specific Energy of Elliptical Orbit = -[GM.Earth]/(2*Semi Major Axis of Elliptic Orbit)

Eccentricity of Orbit Formula

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

How does a rocket make enough thrust to escape earths gravity?

It uses a chemical reaction to turn its fuel into very large amounts of gas. The gas—exhaust—is channeled from the combustion chamber through a hole to a nozzle that directs the gas downward, away from the rocket. Through Newton's Third Law, the force of the escaping gas, carefully oriented, pushes the rocket in the opposite direction.

How to Calculate Eccentricity of Orbit?

Eccentricity of Orbit calculator uses Eccentricity of Elliptical Orbit = Distance Between Two Foci/(2*Semi Major Axis of Elliptic Orbit) to calculate the Eccentricity of Elliptical Orbit, The Eccentricity of Orbit formula is defined as a mathematical expression used to determine the degree of elongation or deviation from a perfect circle in the path of a celestial body or satellite. Eccentricity of Elliptical Orbit is denoted by e_e symbol.

How to calculate Eccentricity of Orbit using this online calculator? To use this online calculator for Eccentricity of Orbit, enter Distance Between Two Foci (d_foci) & Semi Major Axis of Elliptic Orbit (a_e) and hit the calculate button. Here is how the Eccentricity of Orbit calculation can be explained with given input values -> 0.06464 = 20400000/(2*16940000).

FAQ

What is Eccentricity of Orbit?

The Eccentricity of Orbit formula is defined as a mathematical expression used to determine the degree of elongation or deviation from a perfect circle in the path of a celestial body or satellite and is represented as e_e = d_foci/(2*a_e) or Eccentricity of Elliptical Orbit = Distance Between Two Foci/(2*Semi Major Axis of Elliptic Orbit). Distance Between Two Foci is defined as the distance between the two focus, F1 and F2 & Semi Major Axis of Elliptic Orbit is half of the major axis, which is the longest diameter of the ellipse describing the orbit.

How to calculate Eccentricity of Orbit?

The Eccentricity of Orbit formula is defined as a mathematical expression used to determine the degree of elongation or deviation from a perfect circle in the path of a celestial body or satellite is calculated using Eccentricity of Elliptical Orbit = Distance Between Two Foci/(2*Semi Major Axis of Elliptic Orbit). To calculate Eccentricity of Orbit, you need Distance Between Two Foci (d_foci) & Semi Major Axis of Elliptic Orbit (a_e). With our tool, you need to enter the respective value for Distance Between Two Foci & Semi Major Axis of 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 Distance Between Two Foci & Semi Major Axis of Elliptic Orbit. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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