Time since Periapsis in Parabolic Orbit given Mean Anomaly Calculator

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The Two Body Problem

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Parabolic Orbits

Circular Orbits

Elliptical Orbits

Fundamental Parameters

Hyperbolic Orbits

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Orbital Position as Function of Time

Parabolic Orbit Parameters

✖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 [M_p]			+10% -10%

✖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 given Mean Anomaly [t_p]

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Formula

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Time since Periapsis in Parabolic Orbit given Mean Anomaly

Formula

`"t"_{"p"} = ("h"_{"p"}^3*"M"_{"p"})/"[GM.Earth]"^2`

Example

`"3577.828s"=(("73508km²/s")^3*"82°")/"[GM.Earth]"^2`

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Time since Periapsis in Parabolic Orbit given Mean Anomaly Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Constants Used

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

Variables Used

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.
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.

STEP 1: Convert Input(s) to Base Unit

Angular Momentum of Parabolic Orbit: 73508 Square Kilometer per Second --> 73508000000 Squaer Meter per Second (Check conversion here)
Mean Anomaly in Parabolic Orbit: 82 Degree --> 1.43116998663508 Radian (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

t_p = (h_p^3*M_p)/[GM.Earth]^2 --> (73508000000^3*1.43116998663508)/[GM.Earth]^2

Evaluating ... ...

t_p = 3577.82824696055

STEP 3: Convert Result to Output's Unit

3577.82824696055 Second --> No Conversion Required

FINAL ANSWER

3577.82824696055 ≈ 3577.828 Second <-- Time since Periapsis in Parabolic Orbit

(Calculation completed in 00.007 seconds)

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< 4 Orbital Position as Function of Time Calculators

True Anomaly in Parabolic Orbit given Mean Anomaly

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

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

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

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

Time since Periapsis in Parabolic Orbit given Mean Anomaly Formula

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

Why are parabolic trajectories also called escape trajectories?

If the body of some mass m is launched on a parabolic trajectory, it will coast to infinity, arriving there with zero velocity relative to central body. It will not return. Parabolic paths are therefore called escape trajectories.

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

Time since Periapsis in Parabolic Orbit given Mean Anomaly calculator uses Time since Periapsis in Parabolic Orbit = (Angular Momentum of Parabolic Orbit^3*Mean Anomaly in Parabolic Orbit)/[GM.Earth]^2 to calculate the Time since Periapsis in Parabolic Orbit, The Time Since Periapsis in Parabolic Orbit given Mean Anomaly formula is defined as the time that has elapsed since an object in a parabolic orbit passed through periapsis (the point of closest approach to the central body) based on the mean anomaly. Time since Periapsis in Parabolic Orbit is denoted by t_p symbol.

How to calculate Time since Periapsis in Parabolic Orbit given Mean Anomaly using this online calculator? To use this online calculator for Time since Periapsis in Parabolic Orbit given Mean Anomaly, enter Angular Momentum of Parabolic Orbit (h_p) & Mean Anomaly in Parabolic Orbit (M_p) and hit the calculate button. Here is how the Time since Periapsis in Parabolic Orbit given Mean Anomaly calculation can be explained with given input values -> 3577.828 = (73508000000^3*1.43116998663508)/[GM.Earth]^2.

FAQ

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

The Time Since Periapsis in Parabolic Orbit given Mean Anomaly formula is defined as the time that has elapsed since an object in a parabolic orbit passed through periapsis (the point of closest approach to the central body) based on the mean anomaly and is represented as t_p = (h_p^3*M_p)/[GM.Earth]^2 or Time since Periapsis in Parabolic Orbit = (Angular Momentum of Parabolic Orbit^3*Mean Anomaly in Parabolic Orbit)/[GM.Earth]^2. 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 & Mean Anomaly in Parabolic Orbit is the fraction of orbit's period that has elapsed since the orbiting body passed periapsis.

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

The Time Since Periapsis in Parabolic Orbit given Mean Anomaly formula is defined as the time that has elapsed since an object in a parabolic 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 Parabolic Orbit = (Angular Momentum of Parabolic Orbit^3*Mean Anomaly in Parabolic Orbit)/[GM.Earth]^2. To calculate Time since Periapsis in Parabolic Orbit given Mean Anomaly, you need Angular Momentum of Parabolic Orbit (h_p) & Mean Anomaly in Parabolic Orbit (M_p). With our tool, you need to enter the respective value for Angular Momentum of Parabolic Orbit & Mean 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.

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