Nominal Mean Motion Solution

STEP 0: Pre-Calculation Summary
Formula Used
Nominal Mean Motion = sqrt([GM.Earth]/Semi Major Axis^3)
no = 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
Nominal Mean Motion - (Measured in Radian per Second) - Nominal Mean Motion refers to the average rate at which a satellite orbits around a celestial body, such as the Earth.
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
no = sqrt([GM.Earth]/asemi^3) --> sqrt([GM.Earth]/581700^3)
Evaluating ... ...
no = 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 <-- Nominal Mean Motion
(Calculation completed in 00.020 seconds)

Credits

Created by Shobhit Dimri
Bipin Tripathi Kumaon Institute of Technology (BTKIT), Dwarahat
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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)

Nominal Mean Motion Formula

Nominal Mean Motion = sqrt([GM.Earth]/Semi Major Axis^3)
no = sqrt([GM.Earth]/asemi^3)

What does orbital motion mean?

Orbital Motion refers to the movement of a satellite around a celestial body, such as the Earth, following a specific path known as an orbit.

How to Calculate Nominal Mean Motion?

Nominal Mean Motion calculator uses Nominal Mean Motion = sqrt([GM.Earth]/Semi Major Axis^3) to calculate the Nominal Mean Motion, The Nominal Mean Motion 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. Nominal Mean Motion is denoted by no symbol.

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

FAQ

What is Nominal Mean Motion?
The Nominal Mean Motion 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 no = sqrt([GM.Earth]/asemi^3) or Nominal 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 Nominal Mean Motion?
The Nominal Mean Motion 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 Nominal Mean Motion = sqrt([GM.Earth]/Semi Major Axis^3). To calculate Nominal Mean Motion, 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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