Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity Calculator

✖Angular Momentum of Elliptic Orbit is a fundamental physical quantity that characterizes the rotational motion of an object in orbit around a celestial body, such as a planet or a star.ⓘ Angular Momentum of Elliptic Orbit [h_e]			+10% -10%
✖Eccentricity of Elliptical Orbit is a measure of how stretched or elongated the orbit's shape is.ⓘ Eccentricity of Elliptical Orbit [e_e]			+10% -10%

✖Apogee Radius in Elliptic Orbit represents the maximum distance between an orbiting body and the object it orbits.ⓘ Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity [r_e,apogee]

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Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity Solution

STEP 0: Pre-Calculation Summary

Formula Used

Apogee Radius in Elliptic Orbit = Angular Momentum of Elliptic Orbit^2/([GM.Earth]*(1-Eccentricity of Elliptical Orbit))
r_e,apogee = h_e^2/([GM.Earth]*(1-e_e))
This formula uses 1 Constants, 3 Variables

Constants Used

[GM.Earth] - Earth’s Geocentric Gravitational Constant Value Taken As 3.986004418E+14

Variables Used

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.
Angular Momentum of Elliptic Orbit - (Measured in Squaer Meter per Second) - Angular Momentum of Elliptic Orbit is a fundamental physical quantity that characterizes the rotational motion of an object in orbit around a celestial body, such as a planet or a star.
Eccentricity of Elliptical Orbit - Eccentricity of Elliptical Orbit is a measure of how stretched or elongated the orbit's shape is.

STEP 1: Convert Input(s) to Base Unit

Angular Momentum of Elliptic Orbit: 65750 Square Kilometer per Second --> 65750000000 Squaer Meter per Second (Check conversion here)
Eccentricity of Elliptical Orbit: 0.6 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

r_e,apogee = h_e^2/([GM.Earth]*(1-e_e)) --> 65750000000^2/([GM.Earth]*(1-0.6))

Evaluating ... ...

r_e,apogee = 27114009.7115668

STEP 3: Convert Result to Output's Unit

27114009.7115668 Meter -->27114.0097115668 Kilometer (Check conversion here)

FINAL ANSWER

27114.0097115668 ≈ 27114.01 Kilometer <-- Apogee Radius in Elliptic Orbit

(Calculation completed in 00.035 seconds)

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Indian Institute of Technology, Kharagpur (IIT KGP), West Bengal

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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

Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity Formula

LaTeX Go

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

What is Eccentricity ?

Eccentricity is a measure of how much an elliptical orbit deviates from a perfect circle. In orbital mechanics, it quantifies the elongation or flattening of an orbit.Eccentricity is a fundamental parameter in orbital mechanics and plays a crucial role in determining various aspects of an orbit, including its shape, size, and dynamics. It affects the orbital period, velocity, and energy of an orbiting object, as well as its closest and farthest distances from the central body.

How to Calculate Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity?

Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity calculator uses Apogee Radius in Elliptic Orbit = Angular Momentum of Elliptic Orbit^2/([GM.Earth]*(1-Eccentricity of Elliptical Orbit)) to calculate the Apogee Radius in Elliptic Orbit, Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity formula is defined as the maximum distance of an object in an elliptical orbit from the central body, which is a critical parameter in understanding the orbital path of celestial bodies or artificial satellites. Apogee Radius in Elliptic Orbit is denoted by r_e,apogee symbol.

How to calculate Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity using this online calculator? To use this online calculator for Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity, enter Angular Momentum of Elliptic Orbit (h_e) & Eccentricity of Elliptical Orbit (e_e) and hit the calculate button. Here is how the Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity calculation can be explained with given input values -> 27.11401 = 65750000000^2/([GM.Earth]*(1-0.6)).

FAQ

What is Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity?

Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity formula is defined as the maximum distance of an object in an elliptical orbit from the central body, which is a critical parameter in understanding the orbital path of celestial bodies or artificial satellites and is represented as r_e,apogee = h_e^2/([GM.Earth]*(1-e_e)) or Apogee Radius in Elliptic Orbit = Angular Momentum of Elliptic Orbit^2/([GM.Earth]*(1-Eccentricity of Elliptical Orbit)). Angular Momentum of Elliptic Orbit is a fundamental physical quantity that characterizes the rotational motion of an object in orbit around a celestial body, such as a planet or a star & Eccentricity of Elliptical Orbit is a measure of how stretched or elongated the orbit's shape is.

How to calculate Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity?

Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity formula is defined as the maximum distance of an object in an elliptical orbit from the central body, which is a critical parameter in understanding the orbital path of celestial bodies or artificial satellites is calculated using Apogee Radius in Elliptic Orbit = Angular Momentum of Elliptic Orbit^2/([GM.Earth]*(1-Eccentricity of Elliptical Orbit)). To calculate Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity, you need Angular Momentum of Elliptic Orbit (h_e) & Eccentricity of Elliptical Orbit (e_e). With our tool, you need to enter the respective value for Angular Momentum of Elliptic Orbit & Eccentricity of Elliptical Orbit and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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