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True Anomaly Calculator

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Satellite Orbital Characteristics Geostationary Orbit Radio Wave Propagation

✖Mean Anomaly is the fraction of an elliptical orbit's period that has elapsed since the orbiting body passed periapsis.ⓘ Mean Anomaly [M]			+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%

✖True Anomaly is an angular parameter that defines the position of a body moving along a keplerian orbit.ⓘ True Anomaly [v]

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True Anomaly Solution

STEP 0: Pre-Calculation Summary

Formula Used

True Anomaly = Mean Anomaly+(2*Eccentricity*sin(Mean Anomaly))
v = M+(2*e*sin(M))
This formula uses 1 Functions, 3 Variables

Functions Used

sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)

Variables Used

True Anomaly - (Measured in Second) - True Anomaly is an angular parameter that defines the position of a body moving along a keplerian orbit.
Mean Anomaly - (Measured in Radian) - Mean Anomaly is the fraction of an elliptical orbit's period that has elapsed since the orbiting body passed periapsis.
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 Anomaly: 31.958 Degree --> 0.557772322352243 Radian (Check conversion here)
Eccentricity: 0.12 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

v = M+(2*e*sin(M)) --> 0.557772322352243+(2*0.12*sin(0.557772322352243))

Evaluating ... ...

v = 0.684803715198158

STEP 3: Convert Result to Output's Unit

0.684803715198158 Second --> No Conversion Required

FINAL ANSWER

0.684803715198158 ≈ 0.684804 Second <-- True Anomaly

(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

True Anomaly Formula

LaTeX Go

True Anomaly = Mean Anomaly+(2*Eccentricity*sin(Mean Anomaly))
v = M+(2*e*sin(M))

What is Earth's true anomaly?

The true anomaly is the angle (as seen from the Sun) between the Earth and the perihelion of the orbit of the Earth. When the true anomaly is equal to 0 degrees, then the Earth is closest to the Sun (or: in its perihelion).

How to Calculate True Anomaly?

True Anomaly calculator uses True Anomaly = Mean Anomaly+(2*Eccentricity*sin(Mean Anomaly)) to calculate the True Anomaly, The True Anomaly formula is defined as an angular parameter that defines the position of a body moving along a Keplerian orbit. It is the angle between the direction of periapsis and the current position of the body, as seen from the main focus of the ellipse. True Anomaly is denoted by v symbol.

How to calculate True Anomaly using this online calculator? To use this online calculator for True Anomaly, enter Mean Anomaly (M) & Eccentricity (e) and hit the calculate button. Here is how the True Anomaly calculation can be explained with given input values -> 0.684804 = 0.557772322352243+(2*0.12*sin(0.557772322352243)).

FAQ

What is True Anomaly?

The True Anomaly formula is defined as an angular parameter that defines the position of a body moving along a Keplerian orbit. It is the angle between the direction of periapsis and the current position of the body, as seen from the main focus of the ellipse and is represented as v = M+(2*e*sin(M)) or True Anomaly = Mean Anomaly+(2*Eccentricity*sin(Mean Anomaly)). Mean Anomaly is the fraction of an elliptical orbit's period that has elapsed since the orbiting body passed periapsis & Eccentricity refers to a characteristic of the orbit followed by a satellite around its primary body, typically the Earth.

How to calculate True Anomaly?

The True Anomaly formula is defined as an angular parameter that defines the position of a body moving along a Keplerian orbit. It is the angle between the direction of periapsis and the current position of the body, as seen from the main focus of the ellipse is calculated using True Anomaly = Mean Anomaly+(2*Eccentricity*sin(Mean Anomaly)). To calculate True Anomaly, you need Mean Anomaly (M) & Eccentricity (e). With our tool, you need to enter the respective value for Mean Anomaly & 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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