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Mean Anomaly Formula

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Mean Anomaly is the fraction of an elliptical orbit's period that has elapsed since the orbiting body passed periapsis. Check FAQs

M = E - e \cdot \sin (E)

M - Mean Anomaly?E - Eccentric Anomaly?e - Eccentricity?

Mean Anomaly Example

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With units

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Here is how the Mean Anomaly equation looks like with Values.

Here is how the Mean Anomaly equation looks like with Units.

Here is how the Mean Anomaly equation looks like.

31.9587 = 36 - 0.12 \cdot \sin (36)

31.9587° = 36° - 0.12 \cdot \sin (36°)

31.9587 = 36 - 0.12 \cdot \sin (36)

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Mean Anomaly Solution

Follow our step by step solution on how to calculate Mean Anomaly?

FIRST Step Consider the formula

M = E - e \cdot \sin (E)

Next Step Substitute values of Variables

∴

M = 36° - 0.12 \cdot \sin (36°)

Next Step Convert Units

∴

M = 0.6283rad - 0.12 \cdot \sin (0.6283rad)

Next Step Prepare to Evaluate

∴

M = 0.6283 - 0.12 \cdot \sin (0.6283)

Next Step Evaluate

∴

M = 0.557784300442755rad

Next Step Convert to Output's Unit

∴

M = 31.958686294033°

LAST Step Rounding Answer

∴

M = 31.9587°

Mean Anomaly Formula Elements

Variables

Functions

Mean Anomaly

Mean Anomaly is the fraction of an elliptical orbit's period that has elapsed since the orbiting body passed periapsis.

Symbol: M

Measurement: AngleUnit: °

Note: Value should be less than 360.

Formulas to find Mean Anomaly

Eccentric Anomaly

Eccentric anomaly refers to an angular parameter that describes the position of a satellite in its elliptical orbit relative to the central body (usually the Earth).

Symbol: E

Measurement: AngleUnit: °

Note: Value should be less than 180.

Formulas to find Eccentric Anomaly

Eccentricity

Eccentricity refers to a characteristic of the orbit followed by a satellite around its primary body, typically the Earth.

Symbol: e

Measurement: NAUnit: Unitless

Note: Value should be between 0 to 1.

Formulas to find Eccentricity

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.

Syntax: sin(Angle)

Other formulas in Satellite Orbital Characteristics category

Go Anomalistic Period

T AP = \frac{2 \cdot π}{n}

Go Local Sidereal Time

LST = GST + E long

Go Mean Motion of Satellite

n = \sqrt{\frac{[GM.Earth]}{{a semi}^{3}}}

Go Nominal Mean Motion

n o = \sqrt{\frac{[GM.Earth]}{{a semi}^{3}}}

How to Evaluate Mean Anomaly?

Mean Anomaly evaluator uses Mean Anomaly = Eccentric Anomaly-Eccentricity*sin(Eccentric Anomaly) to evaluate the Mean Anomaly, The Mean Anomaly formula is defined as the fraction of an elliptical orbit's period that has elapsed since the orbiting body passed periapsis, expressed as an angle that can be used in calculating the position of that body in the classical two-body problem. Mean Anomaly is denoted by M symbol.

How to evaluate Mean Anomaly using this online evaluator? To use this online evaluator for Mean Anomaly, enter Eccentric Anomaly (E) & Eccentricity (e) and hit the calculate button.

FAQs on Mean Anomaly

What is the formula to find Mean Anomaly?

The formula of Mean Anomaly is expressed as Mean Anomaly = Eccentric Anomaly-Eccentricity*sin(Eccentric Anomaly). Here is an example- 1831.098 = 0.62831853071784-0.12*sin(0.62831853071784).

How to calculate Mean Anomaly?

With Eccentric Anomaly (E) & Eccentricity (e) we can find Mean Anomaly using the formula - Mean Anomaly = Eccentric Anomaly-Eccentricity*sin(Eccentric Anomaly). This formula also uses Sine (sin) function(s).

Can the Mean Anomaly be negative?

No, the Mean Anomaly, measured in Angle cannot be negative.

Which unit is used to measure Mean Anomaly?

Mean Anomaly is usually measured using the Degree[°] for Angle. Radian[°], Minute[°], Second[°] are the few other units in which Mean Anomaly can be measured.

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