Mean Anomaly in Parabolic Orbit given True Anomaly Calculator

✖True Anomaly in Parabolic Orbit measures the angle between the object's current position and the perigee (the point of closest approach to the central body) when viewed from the focus of the orbit.ⓘ True Anomaly in Parabolic Orbit [θ_p]

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✖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 True Anomaly [M_p]

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Mean Anomaly in Parabolic Orbit given True Anomaly Solution

STEP 0: Pre-Calculation Summary

Formula Used

Mean Anomaly in Parabolic Orbit = tan(True Anomaly in Parabolic Orbit/2)/2+tan(True Anomaly in Parabolic Orbit/2)^3/6
M_p = tan(θ_p/2)/2+tan(θ_p/2)^3/6
This formula uses 1 Functions, 2 Variables

Functions Used

tan - The tangent of an angle is a trigonometric ratio of the length of the side opposite an angle to the length of the side adjacent to an angle in a right triangle., tan(Angle)

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.
True Anomaly in Parabolic Orbit - (Measured in Radian) - True Anomaly in Parabolic Orbit measures the angle between the object's current position and the perigee (the point of closest approach to the central body) when viewed from the focus of the orbit.

STEP 1: Convert Input(s) to Base Unit

True Anomaly in Parabolic Orbit: 115 Degree --> 2.0071286397931 Radian (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

M_p = tan(θ_p/2)/2+tan(θ_p/2)^3/6 --> tan(2.0071286397931/2)/2+tan(2.0071286397931/2)^3/6

Evaluating ... ...

M_p = 1.42943752234402

STEP 3: Convert Result to Output's Unit

1.42943752234402 Radian -->81.900737107965 Degree (Check conversion here)

FINAL ANSWER

81.900737107965 ≈ 81.90074 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 True Anomaly

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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 True Anomaly Formula

LaTeX Go

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

What is Mean Anomaly in Parabolic Orbit ?

In a parabolic orbit, the mean anomaly is a parameter used to describe the position of an object in its orbit relative to a reference point. Unlike in elliptical orbits, where the mean anomaly increases uniformly with time, in a parabolic orbit, the mean anomaly varies nonlinearly with time.

How to Calculate Mean Anomaly in Parabolic Orbit given True Anomaly?

Mean Anomaly in Parabolic Orbit given True Anomaly calculator uses Mean Anomaly in Parabolic Orbit = tan(True Anomaly in Parabolic Orbit/2)/2+tan(True Anomaly in Parabolic Orbit/2)^3/6 to calculate the Mean Anomaly in Parabolic Orbit, The Mean Anomaly in Parabolic Orbit given True Anomaly formula is a parameter used to describe the position of an object in its orbit relative to a reference point. While in elliptical orbits, the mean anomaly increases uniformly with time, in a parabolic orbit, the mean anomaly varies nonlinearly with time, given the true anomaly, which describes the current angular position of the object in its orbit relative to periapsis (the point of closest approach), the mean anomaly in a parabolic orbit can be calculated using specific equations derived from orbital mechanics principles. Mean Anomaly in Parabolic Orbit is denoted by M_p symbol.

How to calculate Mean Anomaly in Parabolic Orbit given True Anomaly using this online calculator? To use this online calculator for Mean Anomaly in Parabolic Orbit given True Anomaly, enter True Anomaly in Parabolic Orbit (θ_p) and hit the calculate button. Here is how the Mean Anomaly in Parabolic Orbit given True Anomaly calculation can be explained with given input values -> 4692.567 = tan(2.0071286397931/2)/2+tan(2.0071286397931/2)^3/6.

FAQ

What is Mean Anomaly in Parabolic Orbit given True Anomaly?

The Mean Anomaly in Parabolic Orbit given True Anomaly formula is a parameter used to describe the position of an object in its orbit relative to a reference point. While in elliptical orbits, the mean anomaly increases uniformly with time, in a parabolic orbit, the mean anomaly varies nonlinearly with time, given the true anomaly, which describes the current angular position of the object in its orbit relative to periapsis (the point of closest approach), the mean anomaly in a parabolic orbit can be calculated using specific equations derived from orbital mechanics principles and is represented as M_p = tan(θ_p/2)/2+tan(θ_p/2)^3/6 or Mean Anomaly in Parabolic Orbit = tan(True Anomaly in Parabolic Orbit/2)/2+tan(True Anomaly in Parabolic Orbit/2)^3/6. True Anomaly in Parabolic Orbit measures the angle between the object's current position and the perigee (the point of closest approach to the central body) when viewed from the focus of the orbit.

How to calculate Mean Anomaly in Parabolic Orbit given True Anomaly?

The Mean Anomaly in Parabolic Orbit given True Anomaly formula is a parameter used to describe the position of an object in its orbit relative to a reference point. While in elliptical orbits, the mean anomaly increases uniformly with time, in a parabolic orbit, the mean anomaly varies nonlinearly with time, given the true anomaly, which describes the current angular position of the object in its orbit relative to periapsis (the point of closest approach), the mean anomaly in a parabolic orbit can be calculated using specific equations derived from orbital mechanics principles is calculated using Mean Anomaly in Parabolic Orbit = tan(True Anomaly in Parabolic Orbit/2)/2+tan(True Anomaly in Parabolic Orbit/2)^3/6. To calculate Mean Anomaly in Parabolic Orbit given True Anomaly, you need True Anomaly in Parabolic Orbit (θ_p). With our tool, you need to enter the respective value for True Anomaly in 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 True Anomaly in Parabolic Orbit. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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