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]/asemi^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]/asemi^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)

Credits

Created by Shobhit Dimri
Bipin Tripathi Kumaon Institute of Technology (BTKIT), Dwarahat
Shobhit Dimri has created this Calculator and 900+ more calculators!
Verified by Payal Priya
Birsa Institute of Technology (BIT), Sindri
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16 Satellite Orbital Characteristics Calculators

Position Vector
Go Position Vector = (Major Axis*(1-Eccentricity^2))/(1+Eccentricity*cos(True Anomaly))
Kepler's First Law
Go Eccentricity = sqrt((Semi Major Axis^2-Semi Minor Axis^2))/Semi Major Axis
Mean Anomaly
Go Mean Anomaly = Eccentric Anomaly-Eccentricity*sin(Eccentric Anomaly)
True Anomaly
Go True Anomaly = Mean Anomaly+(2*Eccentricity*sin(Mean Anomaly))
Universal Time
Go Universal Time = (1/24)*(Time in Hour+(Time in Minutes/60)+(Time in Seconds/3600))
Reference Time in Julian Centuries
Go Reference Time = (Julian Day-Julian Day Reference)/Julian Century
Julian Day
Go Julian Day = (Reference Time*Julian Century)+Julian Day Reference
Julian Century
Go Julian Century = (Julian Day-Julian Day Reference)/Reference Time
Nominal Mean Motion
Go Nominal Mean Motion = sqrt([GM.Earth]/Semi Major Axis^3)
Mean Motion of Satellite
Go Mean Motion = sqrt([GM.Earth]/Semi Major Axis^3)
Local Sidereal Time
Go Local Sidereal Time = Greenwich Sidereal Time+East Longitude
Kepler's Third Law
Go Semi Major Axis = ([GM.Earth]/Mean Motion^2)^(1/3)
Range Vector
Go Range Vector = Satellite Radius Vector-[Earth-R]
Orbital Period of Satellite in Minutes
Go Orbital Period in Minutes = 2*pi/Mean Motion
Anomalistic Period
Go Anomalistic Period = (2*pi)/Mean Motion
Universal Time Degree
Go Universal Time Degree = (Universal Time*360)

Mean Motion of Satellite Formula

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