Regression of Nodes Calculator

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Radio Wave Propagation

Geostationary Orbit

Satellite Orbital Characteristics

✖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 [n]			+10% -10%
✖SCOM Constant is typically related to the moment of inertia and other characteristics of the satellite, and it is specific to the particular satellite being analyzed.ⓘ SCOM Constant [SCOM]			+10% -10%
✖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]			+10% -10%
✖Eccentricity refers to a characteristic of the orbit followed by a satellite around its primary body, typically the Earth.ⓘ Eccentricity [e]			+10% -10%

✖Regression node refers to a node or point within a satellite network where regression testing is performed.ⓘ Regression of Nodes [n_reg]

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Formula

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Regression of Nodes

Formula

`"n"_{"reg"} = ("n"*"SCOM")/("a"_{"semi"}^2*(1-"e"^2)^2)`

Example

`"0.009044rad/s²"=("0.045rad/s"*"66063.2km²")/(("581.7km")^2*(1-("0.12")^2)^2)`

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Regression of Nodes Solution

STEP 0: Pre-Calculation Summary

Formula Used

Regression Node = (Mean Motion*SCOM Constant)/(Semi Major Axis^2*(1-Eccentricity^2)^2)
n_reg = (n*SCOM)/(a_semi^2*(1-e^2)^2)
This formula uses 5 Variables

Variables Used

Regression Node - (Measured in Radian per Square Second) - Regression node refers to a node or point within a satellite network where regression testing is performed.
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.
SCOM Constant - (Measured in Square Meter) - SCOM Constant is typically related to the moment of inertia and other characteristics of the satellite, and it is specific to the particular satellite being analyzed.
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.
Eccentricity - Eccentricity refers to a characteristic of the orbit followed by a satellite around its primary body, typically the Earth.

STEP 1: Convert Input(s) to Base Unit

Mean Motion: 0.045 Radian per Second --> 0.045 Radian per Second No Conversion Required
SCOM Constant: 66063.2 Square Kilometer --> 66063200000 Square Meter (Check conversion here)
Semi Major Axis: 581.7 Kilometer --> 581700 Meter (Check conversion here)
Eccentricity: 0.12 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

n_reg = (n*SCOM)/(a_semi^2*(1-e^2)^2) --> (0.045*66063200000)/(581700^2*(1-0.12^2)^2)

Evaluating ... ...

n_reg = 0.00904425092482818

STEP 3: Convert Result to Output's Unit

0.00904425092482818 Radian per Square Second --> No Conversion Required

FINAL ANSWER

0.00904425092482818 ≈ 0.009044 Radian per Square Second <-- Regression Node

(Calculation completed in 00.004 seconds)

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Created by Shobhit Dimri

Bipin Tripathi Kumaon Institute of Technology (BTKIT), Dwarahat

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< 14 Radio Wave Propagation Calculators

Rain Attenuation in Decibels

Go Rain Attenuation = Specific Attenuation*Rain Rate^Specific Attenuation Coefficient*Slant Length*Reduction Factor

Specific Attenuation in Clouds or Fogs

Go Specific Attenuation due to Clouds = (Total Content of Liquid Water*Specific Attenuation Coefficient)/sin(Angle of Elevation)

Regression of Nodes

Go Regression Node = (Mean Motion*SCOM Constant)/(Semi Major Axis^2*(1-Eccentricity^2)^2)

Earth Station Altitude

Go Earth Station Altitude = Height of Rain-Slant Length*sin(Angle of Elevation)

Rain Height

Go Height of Rain = Slant Length*sin(Angle of Elevation)+Earth Station Altitude

Distribution of Rain Attenuation

Go Distribution of Rain Attenuation = 1+((2*Horizontal Projection Length)/(pi*Diameter of Rain Cell))

Horizontal Projection of Slant Length

Go Horizontal Projection Length = Slant Length*cos(Angle of Elevation)

Effective Path Length

Go Effective Path Length = Total Attenuation/Specific Attenuation

Specific Attenuation

Go Specific Attenuation = Total Attenuation/Effective Path Length

Total Attenuation

Go Total Attenuation = Effective Path Length*Specific Attenuation

Effective Path Length using Reduction Factor

Go Effective Path Length = Slant Length*Reduction Factor

Reduction Factor using Slant Length

Go Reduction Factor = Effective Path Length/Slant Length

Slant Length

Go Slant Length = Effective Path Length/Reduction Factor

Plasma Frequency Terms of Electronic Density

Go Plasma Frequency = 9*sqrt(Electron Density)

Regression of Nodes Formula

Regression Node = (Mean Motion*SCOM Constant)/(Semi Major Axis^2*(1-Eccentricity^2)^2)
n_reg = (n*SCOM)/(a_semi^2*(1-e^2)^2)

What is regression of nodes?

Regression of nodes is a rotation of the orbital plane in the direction opposite to the satellite motion around the axis of rotation of the earth.

How to Calculate Regression of Nodes?

Regression of Nodes calculator uses Regression Node = (Mean Motion*SCOM Constant)/(Semi Major Axis^2*(1-Eccentricity^2)^2) to calculate the Regression Node, The Regression of Nodes formula is defined as the node that moves direction opposite to that direction of satellites. Regression Node is denoted by n_reg symbol.

How to calculate Regression of Nodes using this online calculator? To use this online calculator for Regression of Nodes, enter Mean Motion (n), SCOM Constant (SCOM), Semi Major Axis (a_semi) & Eccentricity (e) and hit the calculate button. Here is how the Regression of Nodes calculation can be explained with given input values -> 0.009044 = (0.045*66063200000)/(581700^2*(1-0.12^2)^2).

FAQ

What is Regression of Nodes?

The Regression of Nodes formula is defined as the node that moves direction opposite to that direction of satellites and is represented as n_reg = (n*SCOM)/(a_semi^2*(1-e^2)^2) or Regression Node = (Mean Motion*SCOM Constant)/(Semi Major Axis^2*(1-Eccentricity^2)^2). 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, SCOM Constant is typically related to the moment of inertia and other characteristics of the satellite, and it is specific to the particular satellite being analyzed, The Semi major axis can be used to determine the size of satellite's orbit. It is half of the major axis & Eccentricity refers to a characteristic of the orbit followed by a satellite around its primary body, typically the Earth.

How to calculate Regression of Nodes?

The Regression of Nodes formula is defined as the node that moves direction opposite to that direction of satellites is calculated using Regression Node = (Mean Motion*SCOM Constant)/(Semi Major Axis^2*(1-Eccentricity^2)^2). To calculate Regression of Nodes, you need Mean Motion (n), SCOM Constant (SCOM), Semi Major Axis (a_semi) & Eccentricity (e). With our tool, you need to enter the respective value for Mean Motion, SCOM Constant, Semi Major Axis & Eccentricity 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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