Specific Energy of Elliptic Orbit given Semi Major Axis Calculator

✖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]

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✖Specific Energy of Elliptical Orbit is the total orbital energy per unit mass of an orbiting body. It is the sum of the kinetic energy and the gravitational potential energy.ⓘ Specific Energy of Elliptic Orbit given Semi Major Axis [ε_e]

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Specific Energy of Elliptic Orbit given Semi Major Axis Solution

STEP 0: Pre-Calculation Summary

Formula Used

Specific Energy of Elliptical Orbit = -[GM.Earth]/(2*Semi Major Axis of Elliptic Orbit)
ε_e = -[GM.Earth]/(2*a_e)
This formula uses 1 Constants, 2 Variables

Constants Used

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

Variables Used

Specific Energy of Elliptical Orbit - (Measured in Joule per Kilogram) - Specific Energy of Elliptical Orbit is the total orbital energy per unit mass of an orbiting body. It is the sum of the kinetic energy and the gravitational potential energy.
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

Semi Major Axis of Elliptic Orbit: 16940 Kilometer --> 16940000 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

ε_e = -[GM.Earth]/(2*a_e) --> -[GM.Earth]/(2*16940000)

Evaluating ... ...

ε_e = -11765066.1688312

STEP 3: Convert Result to Output's Unit

-11765066.1688312 Joule per Kilogram -->-11765.0661688312 Kilojoule per Kilogram (Check conversion here)

FINAL ANSWER

-11765.0661688312 ≈ -11765.066169 Kilojoule per Kilogram <-- Specific Energy of Elliptical Orbit

(Calculation completed in 00.020 seconds)

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Created by Karavadiya Divykumar Rasikbhai

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

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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

Specific Energy of Elliptic Orbit given Semi Major Axis Formula

LaTeX Go

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

What is Specific energy?

Specific energy, in physics, engineering, and mechanics, refers to the energy per unit mass possessed by a system or object. It's a measure of energy concentration or density relative to mass.

What is the specific energy of an elliptical orbit?

For an elliptic orbit the specific orbital energy is the negative of the additional energy required to accelerate a mass of one kilogram to escape velocity.

How to Calculate Specific Energy of Elliptic Orbit given Semi Major Axis?

Specific Energy of Elliptic Orbit given Semi Major Axis calculator uses Specific Energy of Elliptical Orbit = -[GM.Earth]/(2*Semi Major Axis of Elliptic Orbit) to calculate the Specific Energy of Elliptical Orbit, Specific Energy of Elliptic Orbit given Semi Major Axis formula is defined as a measure of the total energy of an object in an elliptical orbit around a celestial body, which is a critical parameter in understanding the motion of objects in space. Specific Energy of Elliptical Orbit is denoted by ε_e symbol.

How to calculate Specific Energy of Elliptic Orbit given Semi Major Axis using this online calculator? To use this online calculator for Specific Energy of Elliptic Orbit given Semi Major Axis, enter Semi Major Axis of Elliptic Orbit (a_e) and hit the calculate button. Here is how the Specific Energy of Elliptic Orbit given Semi Major Axis calculation can be explained with given input values -> -11.765066 = -[GM.Earth]/(2*16940000).

FAQ

What is Specific Energy of Elliptic Orbit given Semi Major Axis?

Specific Energy of Elliptic Orbit given Semi Major Axis formula is defined as a measure of the total energy of an object in an elliptical orbit around a celestial body, which is a critical parameter in understanding the motion of objects in space and is represented as ε_e = -[GM.Earth]/(2*a_e) or Specific Energy of Elliptical Orbit = -[GM.Earth]/(2*Semi Major Axis of Elliptic Orbit). 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 Specific Energy of Elliptic Orbit given Semi Major Axis?

Specific Energy of Elliptic Orbit given Semi Major Axis formula is defined as a measure of the total energy of an object in an elliptical orbit around a celestial body, which is a critical parameter in understanding the motion of objects in space is calculated using Specific Energy of Elliptical Orbit = -[GM.Earth]/(2*Semi Major Axis of Elliptic Orbit). To calculate Specific Energy of Elliptic Orbit given Semi Major Axis, you need Semi Major Axis of Elliptic Orbit (a_e). With our tool, you need to enter the respective value for 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 Specific Energy of Elliptical Orbit?

In this formula, Specific Energy of Elliptical Orbit uses Semi Major Axis of Elliptic Orbit. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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