Time since Periapsis in Parabolic Orbit given Mean Anomaly Calculator

✖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]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Parabolic Orbits Formulas PDF PDF Image

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 00.014 seconds)

You are here -

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

Credits

Created by Harsh Raj

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

Harsh Raj has created this Calculator and 50+ more calculators!

Verified by Kartikay Pandit

National Institute Of Technology (NIT), Hamirpur

Kartikay Pandit has verified this Calculator and 400+ more calculators!

< 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

Time since Periapsis in Parabolic Orbit given Mean Anomaly Formula

LaTeX Go

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

What ia angular Momemtum ?

Angular momentum is a fundamental concept in physics that describes the rotational motion of an object around an axis. It is a vector quantity defined as the product of an object's moment of inertia and its angular velocity.

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.

Home

FREE PDFs

🔍 Search