Time since Periapsis in Elliptic Orbit given Mean Anomaly Calculator

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The Two Body Problem

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Elliptical Orbits

Circular Orbits

Fundamental Parameters

Hyperbolic Orbits

Parabolic Orbits

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Orbital Position as Function of Time

Elliptical Orbit Parameters

✖Mean Anomaly in Elliptical Orbit is the fraction of an orbit's period that has elapsed since the orbiting body passed periapsis.ⓘ Mean Anomaly in Elliptical Orbit [M_e]			+10% -10%
✖The time period of Elliptic Orbit is the amount of time a given astronomical object takes to complete one orbit around another object.ⓘ Time Period of Elliptic Orbit [T_e]			+10% -10%

✖The Time since Periapsis in Elliptical Orbit is a measure of the duration that has passed since an object in orbit, passed through its closest point to the central body, known as periapsis.ⓘ Time since Periapsis in Elliptic Orbit given Mean Anomaly [t_e]

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Formula

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Time since Periapsis in Elliptic Orbit given Mean Anomaly

Formula

`"t"_{"e"} = "M"_{"e"}*"T"_{"e"}/(2*pi)`

Example

`"4091.042s"="67.25°"*"21900s"/(2*pi)`

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Time since Periapsis in Elliptic Orbit given Mean Anomaly Solution

STEP 0: Pre-Calculation Summary

Formula Used

Time since Periapsis in Elliptical Orbit = Mean Anomaly in Elliptical Orbit*Time Period of Elliptic Orbit/(2*pi)
t_e = M_e*T_e/(2*pi)
This formula uses 1 Constants, 3 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Time since Periapsis in Elliptical Orbit - (Measured in Second) - The Time since Periapsis in Elliptical Orbit is a measure of the duration that has passed since an object in orbit, passed through its closest point to the central body, known as periapsis.
Mean Anomaly in Elliptical Orbit - (Measured in Radian) - Mean Anomaly in Elliptical Orbit is the fraction of an orbit's period that has elapsed since the orbiting body passed periapsis.
Time Period of Elliptic Orbit - (Measured in Second) - The time period of Elliptic Orbit is the amount of time a given astronomical object takes to complete one orbit around another object.

STEP 1: Convert Input(s) to Base Unit

Mean Anomaly in Elliptical Orbit: 67.25 Degree --> 1.17373392196597 Radian (Check conversion here)
Time Period of Elliptic Orbit: 21900 Second --> 21900 Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

t_e = M_e*T_e/(2*pi) --> 1.17373392196597*21900/(2*pi)

Evaluating ... ...

t_e = 4091.04166666591

STEP 3: Convert Result to Output's Unit

4091.04166666591 Second --> No Conversion Required

FINAL ANSWER

4091.04166666591 ≈ 4091.042 Second <-- Time since Periapsis in Elliptical Orbit

(Calculation completed in 00.004 seconds)

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Home » Physics » Orbital Mechanics » The Two Body Problem » Elliptical Orbits » Orbital Position as Function of Time » Time since Periapsis in Elliptic Orbit given Mean Anomaly

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Indian Institute of Technology, Kharagpur (IIT KGP), West Bengal

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< 6 Orbital Position as Function of Time Calculators

Time since Periapsis in Elliptic Orbit given Eccentric Anomaly and Time Period

Go Time since Periapsis in Elliptical Orbit = (Eccentric Anomaly-Eccentricity of Elliptical Orbit*sin(Eccentric Anomaly))*Time Period of Elliptic Orbit/(2*Pi(6))

Eccentric Anomaly in Elliptic Orbit given True Anomaly and Eccentricity

Go Eccentric Anomaly = 2*atan(sqrt((1-Eccentricity of Elliptical Orbit)/(1+Eccentricity of Elliptical Orbit))*tan(True Anomaly in Elliptical Orbit/2))

True Anomaly in Elliptic Orbit given Eccentric Anomaly and Eccentricity

Go True Anomaly in Elliptical Orbit = 2*atan(sqrt((1+Eccentricity of Elliptical Orbit)/(1-Eccentricity of Elliptical Orbit))*tan(Eccentric Anomaly/2))

Mean Anomaly in Elliptic Orbit given Eccentric Anomaly and Eccentricity

Go Mean Anomaly in Elliptical Orbit = Eccentric Anomaly-Eccentricity of Elliptical Orbit*sin(Eccentric Anomaly)

Time since Periapsis in Elliptic Orbit given Mean Anomaly

Go Time since Periapsis in Elliptical Orbit = Mean Anomaly in Elliptical Orbit*Time Period of Elliptic Orbit/(2*pi)

Mean Anomaly in Elliptic Orbit given Time since Periapsis

Go Mean Anomaly in Elliptical Orbit = (2*pi*Time since Periapsis in Elliptical Orbit)/Time Period of Elliptic Orbit

Time since Periapsis in Elliptic Orbit given Mean Anomaly Formula

Time since Periapsis in Elliptical Orbit = Mean Anomaly in Elliptical Orbit*Time Period of Elliptic Orbit/(2*pi)
t_e = M_e*T_e/(2*pi)

Geometric Visualization of Mean Anomaly

The mean anomaly, M, is the angle which describes the position of a satellite in its orbit, relative to perigee. At perigee, the Mean Anomaly is zero, it increases to 180 degrees at apogee, then back to perigee at 360 degrees.

How to Calculate Time since Periapsis in Elliptic Orbit given Mean Anomaly?

Time since Periapsis in Elliptic Orbit given Mean Anomaly calculator uses Time since Periapsis in Elliptical Orbit = Mean Anomaly in Elliptical Orbit*Time Period of Elliptic Orbit/(2*pi) to calculate the Time since Periapsis in Elliptical Orbit, The Time Since Periapsis in Elliptic Orbit given Mean Anomaly formula is defined as time that has elapsed since an object in an elliptic orbit passed through periapsis (the point of closest approach to the central body) based on the mean anomaly. Time since Periapsis in Elliptical Orbit is denoted by t_e symbol.

How to calculate Time since Periapsis in Elliptic Orbit given Mean Anomaly using this online calculator? To use this online calculator for Time since Periapsis in Elliptic Orbit given Mean Anomaly, enter Mean Anomaly in Elliptical Orbit (M_e) & Time Period of Elliptic Orbit (T_e) and hit the calculate button. Here is how the Time since Periapsis in Elliptic Orbit given Mean Anomaly calculation can be explained with given input values -> 4091.042 = 1.17373392196597*21900/(2*pi).

FAQ

What is Time since Periapsis in Elliptic Orbit given Mean Anomaly?

The Time Since Periapsis in Elliptic Orbit given Mean Anomaly formula is defined as time that has elapsed since an object in an elliptic orbit passed through periapsis (the point of closest approach to the central body) based on the mean anomaly and is represented as t_e = M_e*T_e/(2*pi) or Time since Periapsis in Elliptical Orbit = Mean Anomaly in Elliptical Orbit*Time Period of Elliptic Orbit/(2*pi). Mean Anomaly in Elliptical Orbit is the fraction of an orbit's period that has elapsed since the orbiting body passed periapsis & The time period of Elliptic Orbit is the amount of time a given astronomical object takes to complete one orbit around another object.

How to calculate Time since Periapsis in Elliptic Orbit given Mean Anomaly?

The Time Since Periapsis in Elliptic Orbit given Mean Anomaly formula is defined as time that has elapsed since an object in an elliptic orbit passed through periapsis (the point of closest approach to the central body) based on the mean anomaly is calculated using Time since Periapsis in Elliptical Orbit = Mean Anomaly in Elliptical Orbit*Time Period of Elliptic Orbit/(2*pi). To calculate Time since Periapsis in Elliptic Orbit given Mean Anomaly, you need Mean Anomaly in Elliptical Orbit (M_e) & Time Period of Elliptic Orbit (T_e). With our tool, you need to enter the respective value for Mean Anomaly in Elliptical Orbit & Time Period of Elliptic Orbit and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Time since Periapsis in Elliptical Orbit?

In this formula, Time since Periapsis in Elliptical Orbit uses Mean Anomaly in Elliptical Orbit & Time Period of Elliptic Orbit. We can use 1 other way(s) to calculate the same, which is/are as follows -

Time since Periapsis in Elliptical Orbit = (Eccentric Anomaly-Eccentricity of Elliptical Orbit*sin(Eccentric Anomaly))*Time Period of Elliptic Orbit/(2*Pi(6))

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