Mean Anomaly in Parabolic Orbit given Time since Periapsis Calculator

✖The Time since Periapsis in Parabolic 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 Parabolic Orbit [t_p]			+10% -10%
✖Angular Momentum of Parabolic Orbit is a fundamental physical quantity that characterizes the rotational motion of an object in orbit around a celestial body, such as a planet or a star.ⓘ Angular Momentum of Parabolic Orbit [h_p]			+10% -10%

✖Mean Anomaly in Parabolic Orbit is the fraction of orbit's period that has elapsed since the orbiting body passed periapsis.ⓘ Mean Anomaly in Parabolic Orbit given Time since Periapsis [M_p]

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Mean Anomaly in Parabolic Orbit given Time since Periapsis Solution

STEP 0: Pre-Calculation Summary

Formula Used

Mean Anomaly in Parabolic Orbit = ([GM.Earth]^2*Time since Periapsis in Parabolic Orbit)/Angular Momentum of Parabolic Orbit^3
M_p = ([GM.Earth]^2*t_p)/h_p^3
This formula uses 1 Constants, 3 Variables

Constants Used

[GM.Earth] - Earth’s Geocentric Gravitational Constant Value Taken As 3.986004418E+14

Variables Used

Mean Anomaly in Parabolic Orbit - (Measured in Radian) - Mean Anomaly in Parabolic Orbit is the fraction of orbit's period that has elapsed since the orbiting body passed periapsis.
Time since Periapsis in Parabolic Orbit - (Measured in Second) - The Time since Periapsis in Parabolic 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.
Angular Momentum of Parabolic Orbit - (Measured in Squaer Meter per Second) - Angular Momentum of Parabolic Orbit is a fundamental physical quantity that characterizes the rotational motion of an object in orbit around a celestial body, such as a planet or a star.

STEP 1: Convert Input(s) to Base Unit

Time since Periapsis in Parabolic Orbit: 3578 Second --> 3578 Second No Conversion Required
Angular Momentum of Parabolic Orbit: 73508 Square Kilometer per Second --> 73508000000 Squaer Meter per Second (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

M_p = ([GM.Earth]^2*t_p)/h_p^3 --> ([GM.Earth]^2*3578)/73508000000^3

Evaluating ... ...

M_p = 1.43123868970806

STEP 3: Convert Result to Output's Unit

1.43123868970806 Radian -->82.0039363961214 Degree (Check conversion here)

FINAL ANSWER

82.0039363961214 ≈ 82.00394 Degree <-- Mean Anomaly in Parabolic Orbit

(Calculation completed in 00.020 seconds)

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

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Created by Harsh Raj

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

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< Orbital Position as Function of Time Calculators

True Anomaly in Parabolic Orbit given Mean Anomaly

LaTeX Go True Anomaly in Parabolic Orbit = 2*atan((3*Mean Anomaly in Parabolic Orbit+sqrt((3*Mean Anomaly in Parabolic Orbit)^2+1))^(1/3)-(3*Mean Anomaly in Parabolic Orbit+sqrt((3*Mean Anomaly in Parabolic Orbit)^2+1))^(-1/3))

Mean Anomaly in Parabolic Orbit given True Anomaly

LaTeX Go Mean Anomaly in Parabolic Orbit = tan(True Anomaly in Parabolic Orbit/2)/2+tan(True Anomaly in Parabolic Orbit/2)^3/6

Time since Periapsis in Parabolic Orbit given Mean Anomaly

LaTeX Go Time since Periapsis in Parabolic Orbit = (Angular Momentum of Parabolic Orbit^3*Mean Anomaly in Parabolic Orbit)/[GM.Earth]^2

Mean Anomaly in Parabolic Orbit given Time since Periapsis

LaTeX Go Mean Anomaly in Parabolic Orbit = ([GM.Earth]^2*Time since Periapsis in Parabolic Orbit)/Angular Momentum of Parabolic Orbit^3

Mean Anomaly in Parabolic Orbit given Time since Periapsis Formula

LaTeX Go

Mean Anomaly in Parabolic Orbit = ([GM.Earth]^2*Time since Periapsis in Parabolic Orbit)/Angular Momentum of Parabolic Orbit^3
M_p = ([GM.Earth]^2*t_p)/h_p^3

What is trajectories ?

Trajectories refer to the paths followed by objects as they move through space or other mediums. In physics and engineering, trajectories are often studied to understand and predict the motion of objects, such as projectiles, celestial bodies, spacecraft, particles, and more.

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

Mean Anomaly in Parabolic Orbit given Time since Periapsis calculator uses Mean Anomaly in Parabolic Orbit = ([GM.Earth]^2*Time since Periapsis in Parabolic Orbit)/Angular Momentum of Parabolic Orbit^3 to calculate the Mean Anomaly in Parabolic Orbit, The Mean Anomaly in Parabolic Orbit given Time Since Periapsis formula is a parameter used to describe the position of an object in its orbit relative to a reference point. It's similar to the mean anomaly in elliptical orbits, but adapted for parabolic trajectories, given the time since periapsis , the mean anomaly in a parabolic orbit can be calculated using equations specific to parabolic orbits. Mean Anomaly in Parabolic Orbit is denoted by M_p symbol.

How to calculate Mean Anomaly in Parabolic Orbit given Time since Periapsis using this online calculator? To use this online calculator for Mean Anomaly in Parabolic Orbit given Time since Periapsis, enter Time since Periapsis in Parabolic Orbit (t_p) & Angular Momentum of Parabolic Orbit (h_p) and hit the calculate button. Here is how the Mean Anomaly in Parabolic Orbit given Time since Periapsis calculation can be explained with given input values -> 6568.417 = ([GM.Earth]^2*3578)/73508000000^3.

FAQ

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

The Mean Anomaly in Parabolic Orbit given Time Since Periapsis formula is a parameter used to describe the position of an object in its orbit relative to a reference point. It's similar to the mean anomaly in elliptical orbits, but adapted for parabolic trajectories, given the time since periapsis , the mean anomaly in a parabolic orbit can be calculated using equations specific to parabolic orbits and is represented as M_p = ([GM.Earth]^2*t_p)/h_p^3 or Mean Anomaly in Parabolic Orbit = ([GM.Earth]^2*Time since Periapsis in Parabolic Orbit)/Angular Momentum of Parabolic Orbit^3. The Time since Periapsis in Parabolic 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 & Angular Momentum of Parabolic Orbit is a fundamental physical quantity that characterizes the rotational motion of an object in orbit around a celestial body, such as a planet or a star.

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

The Mean Anomaly in Parabolic Orbit given Time Since Periapsis formula is a parameter used to describe the position of an object in its orbit relative to a reference point. It's similar to the mean anomaly in elliptical orbits, but adapted for parabolic trajectories, given the time since periapsis , the mean anomaly in a parabolic orbit can be calculated using equations specific to parabolic orbits is calculated using Mean Anomaly in Parabolic Orbit = ([GM.Earth]^2*Time since Periapsis in Parabolic Orbit)/Angular Momentum of Parabolic Orbit^3. To calculate Mean Anomaly in Parabolic Orbit given Time since Periapsis, you need Time since Periapsis in Parabolic Orbit (t_p) & Angular Momentum of Parabolic Orbit (h_p). With our tool, you need to enter the respective value for Time since Periapsis in Parabolic Orbit & Angular Momentum of Parabolic 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 Mean Anomaly in Parabolic Orbit?

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

Mean Anomaly in Parabolic Orbit = tan(True Anomaly in Parabolic Orbit/2)/2+tan(True Anomaly in Parabolic Orbit/2)^3/6

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