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Mean Motion of Satellite Calculator

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✖The Semi major axis can be used to determine the size of satellite's orbit. It is half of the major axis.ⓘ Semi Major Axis [a_semi]

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✖Mean Motion is angular speed required for a body to complete an orbit, assuming constant speed in circular orbit that takes same time as variable speed elliptical orbit of actual body.ⓘ Mean Motion of Satellite [n]

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Mean Motion of Satellite Solution

STEP 0: Pre-Calculation Summary

Formula Used

Mean Motion = sqrt([GM.Earth]/Semi Major Axis^3)
n = sqrt([GM.Earth]/a_semi^3)
This formula uses 1 Constants, 1 Functions, 2 Variables

Constants Used

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

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

Mean Motion - (Measured in Radian per Second) - Mean Motion is angular speed required for a body to complete an orbit, assuming constant speed in circular orbit that takes same time as variable speed elliptical orbit of actual body.
Semi Major Axis - (Measured in Meter) - The Semi major axis can be used to determine the size of satellite's orbit. It is half of the major axis.

STEP 1: Convert Input(s) to Base Unit

Semi Major Axis: 581.7 Kilometer --> 581700 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

n = sqrt([GM.Earth]/a_semi^3) --> sqrt([GM.Earth]/581700^3)

Evaluating ... ...

n = 0.0450008059755109

STEP 3: Convert Result to Output's Unit

0.0450008059755109 Radian per Second --> No Conversion Required

FINAL ANSWER

0.0450008059755109 ≈ 0.045001 Radian per Second <-- Mean Motion

(Calculation completed in 00.004 seconds)

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Bipin Tripathi Kumaon Institute of Technology (BTKIT), Dwarahat

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< Satellite Orbital Characteristics Calculators

Mean Anomaly

LaTeX Go Mean Anomaly = Eccentric Anomaly-Eccentricity*sin(Eccentric Anomaly)

Mean Motion of Satellite

LaTeX Go Mean Motion = sqrt([GM.Earth]/Semi Major Axis^3)

Local Sidereal Time

LaTeX Go Local Sidereal Time = Greenwich Sidereal Time+East Longitude

Anomalistic Period

LaTeX Go Anomalistic Period = (2*pi)/Mean Motion

Mean Motion of Satellite Formula

LaTeX Go

Mean Motion = sqrt([GM.Earth]/Semi Major Axis^3)
n = sqrt([GM.Earth]/a_semi^3)

What is the units of mean motion?

The mean motion is simply one revolution divided by this time, or, with dimensions of radians per unit time, degrees per unit time or revolutions per unit time. The value of mean motion depends on the circumstances of the particular gravitating system.

How to Calculate Mean Motion of Satellite?

Mean Motion of Satellite calculator uses Mean Motion = sqrt([GM.Earth]/Semi Major Axis^3) to calculate the Mean Motion, The Mean Motion of Satellite formula is defined as the angular speed required for a body to complete one orbit, assuming constant speed in a circular orbit which completes in the same time as the variable speed, elliptical orbit of the actual body. Mean Motion is denoted by n symbol.

How to calculate Mean Motion of Satellite using this online calculator? To use this online calculator for Mean Motion of Satellite, enter Semi Major Axis (a_semi) and hit the calculate button. Here is how the Mean Motion of Satellite calculation can be explained with given input values -> 4.7E-6 = sqrt([GM.Earth]/581700^3).

FAQ

What is Mean Motion of Satellite?

The Mean Motion of Satellite formula is defined as the angular speed required for a body to complete one orbit, assuming constant speed in a circular orbit which completes in the same time as the variable speed, elliptical orbit of the actual body and is represented as n = sqrt([GM.Earth]/a_semi^3) or Mean Motion = sqrt([GM.Earth]/Semi Major Axis^3). The Semi major axis can be used to determine the size of satellite's orbit. It is half of the major axis.

How to calculate Mean Motion of Satellite?

The Mean Motion of Satellite formula is defined as the angular speed required for a body to complete one orbit, assuming constant speed in a circular orbit which completes in the same time as the variable speed, elliptical orbit of the actual body is calculated using Mean Motion = sqrt([GM.Earth]/Semi Major Axis^3). To calculate Mean Motion of Satellite, you need Semi Major Axis (a_semi). With our tool, you need to enter the respective value for Semi Major Axis 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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