Time since Periapsis in Hyperbolic Orbit given Mean Anomaly Calculator

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The Two Body Problem

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Hyperbolic Orbits

Circular Orbits

Elliptical Orbits

Fundamental Parameters

Parabolic Orbits

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Orbital Position as Function of Time

Hperbolic Orbit Parameters

✖Angular Momentum of Hyperbolic 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 Hyperbolic Orbit [h_h]			+10% -10%
✖Eccentricity of Hyperbolic Orbit describes how much the orbit differs from a perfect circle, and this value typically falls between 1 and infinity.ⓘ Eccentricity of Hyperbolic Orbit [e_h]			+10% -10%
✖The Mean Anomaly in Hyperbolic Orbit is a time-related parameter that represents the angular distance covered by an object in its hyperbolic trajectory since passing through periapsis.ⓘ Mean Anomaly in Hyperbolic Orbit [M_h]			+10% -10%

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

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Formula

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Time since Periapsis in Hyperbolic Orbit given Mean Anomaly

Formula

`"t" = "h"_{"h"}^3/("[GM.Earth]"^2*("e"_{"h"}^2-1)^(3/2))*"M"_{"h"}`

Example

`"2042.397s"=("65700km²/s")^3/("[GM.Earth]"^2*(("1.339")^2-1)^(3/2))*"46.29°"`

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Time since Periapsis in Hyperbolic Orbit given Mean Anomaly Solution

STEP 0: Pre-Calculation Summary

Formula Used

Time since Periapsis = Angular Momentum of Hyperbolic Orbit^3/([GM.Earth]^2*(Eccentricity of Hyperbolic Orbit^2-1)^(3/2))*Mean Anomaly in Hyperbolic Orbit
t = h_h^3/([GM.Earth]^2*(e_h^2-1)^(3/2))*M_h
This formula uses 1 Constants, 4 Variables

Constants Used

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

Variables Used

Time since Periapsis - (Measured in Second) - The Time since Periapsis is a measure of the duration that has passed since an object in orbit, such as a satellite, passed through its closest point to the central body, known as periapsis.
Angular Momentum of Hyperbolic Orbit - (Measured in Squaer Meter per Second) - Angular Momentum of Hyperbolic 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.
Eccentricity of Hyperbolic Orbit - Eccentricity of Hyperbolic Orbit describes how much the orbit differs from a perfect circle, and this value typically falls between 1 and infinity.
Mean Anomaly in Hyperbolic Orbit - (Measured in Radian) - The Mean Anomaly in Hyperbolic Orbit is a time-related parameter that represents the angular distance covered by an object in its hyperbolic trajectory since passing through periapsis.

STEP 1: Convert Input(s) to Base Unit

Angular Momentum of Hyperbolic Orbit: 65700 Square Kilometer per Second --> 65700000000 Squaer Meter per Second (Check conversion here)
Eccentricity of Hyperbolic Orbit: 1.339 --> No Conversion Required
Mean Anomaly in Hyperbolic Orbit: 46.29 Degree --> 0.807912910748023 Radian (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

t = h_h^3/([GM.Earth]^2*(e_h^2-1)^(3/2))*M_h --> 65700000000^3/([GM.Earth]^2*(1.339^2-1)^(3/2))*0.807912910748023

Evaluating ... ...

t = 2042.39729017283

STEP 3: Convert Result to Output's Unit

2042.39729017283 Second --> No Conversion Required

FINAL ANSWER

2042.39729017283 ≈ 2042.397 Second <-- Time since Periapsis

(Calculation completed in 00.004 seconds)

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

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Created by Harsh Raj

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

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National Institute Of Technology (NIT), Hamirpur

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< 5 Orbital Position as Function of Time Calculators

Time since Periapsis in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly

Go Time since Periapsis = Angular Momentum of Hyperbolic Orbit^3/([GM.Earth]^2*(Eccentricity of Hyperbolic Orbit^2-1)^(3/2))*(Eccentricity of Hyperbolic Orbit*sinh(Eccentric Anomaly in Hyperbolic Orbit)-Eccentric Anomaly in Hyperbolic Orbit)

True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity

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

Hyperbolic Eccentric Anomaly given Eccentricity and True Anomaly

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

Mean Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly

Go Mean Anomaly in Hyperbolic Orbit = Eccentricity of Hyperbolic Orbit*sinh(Eccentric Anomaly in Hyperbolic Orbit)-Eccentric Anomaly in Hyperbolic Orbit

Time since Periapsis in Hyperbolic Orbit given Mean Anomaly

Go Time since Periapsis = Angular Momentum of Hyperbolic Orbit^3/([GM.Earth]^2*(Eccentricity of Hyperbolic Orbit^2-1)^(3/2))*Mean Anomaly in Hyperbolic Orbit

Time since Periapsis in Hyperbolic Orbit given Mean Anomaly Formula

Time since Periapsis = Angular Momentum of Hyperbolic Orbit^3/([GM.Earth]^2*(Eccentricity of Hyperbolic Orbit^2-1)^(3/2))*Mean Anomaly in Hyperbolic Orbit
t = h_h^3/([GM.Earth]^2*(e_h^2-1)^(3/2))*M_h

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 Hyperbolic Orbit given Mean Anomaly?

Time since Periapsis in Hyperbolic Orbit given Mean Anomaly calculator uses Time since Periapsis = Angular Momentum of Hyperbolic Orbit^3/([GM.Earth]^2*(Eccentricity of Hyperbolic Orbit^2-1)^(3/2))*Mean Anomaly in Hyperbolic Orbit to calculate the Time since Periapsis, The Time Since Periapsis in Hyperbolic Orbit given Mean Anomaly formula is defined as time that has elapsed since an object in a hyperbolic orbit passed through periapsis (the point of closest approach to the central body) based on the mean anomaly. Time since Periapsis is denoted by t symbol.

How to calculate Time since Periapsis in Hyperbolic Orbit given Mean Anomaly using this online calculator? To use this online calculator for Time since Periapsis in Hyperbolic Orbit given Mean Anomaly, enter Angular Momentum of Hyperbolic Orbit (h_h), Eccentricity of Hyperbolic Orbit (e_h) & Mean Anomaly in Hyperbolic Orbit (M_h) and hit the calculate button. Here is how the Time since Periapsis in Hyperbolic Orbit given Mean Anomaly calculation can be explained with given input values -> 2042.397 = 65700000000^3/([GM.Earth]^2*(1.339^2-1)^(3/2))*0.807912910748023.

FAQ

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

The Time Since Periapsis in Hyperbolic Orbit given Mean Anomaly formula is defined as time that has elapsed since an object in a hyperbolic orbit passed through periapsis (the point of closest approach to the central body) based on the mean anomaly and is represented as t = h_h^3/([GM.Earth]^2*(e_h^2-1)^(3/2))*M_h or Time since Periapsis = Angular Momentum of Hyperbolic Orbit^3/([GM.Earth]^2*(Eccentricity of Hyperbolic Orbit^2-1)^(3/2))*Mean Anomaly in Hyperbolic Orbit. Angular Momentum of Hyperbolic 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, Eccentricity of Hyperbolic Orbit describes how much the orbit differs from a perfect circle, and this value typically falls between 1 and infinity & The Mean Anomaly in Hyperbolic Orbit is a time-related parameter that represents the angular distance covered by an object in its hyperbolic trajectory since passing through periapsis.

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

The Time Since Periapsis in Hyperbolic Orbit given Mean Anomaly formula is defined as time that has elapsed since an object in a hyperbolic orbit passed through periapsis (the point of closest approach to the central body) based on the mean anomaly is calculated using Time since Periapsis = Angular Momentum of Hyperbolic Orbit^3/([GM.Earth]^2*(Eccentricity of Hyperbolic Orbit^2-1)^(3/2))*Mean Anomaly in Hyperbolic Orbit. To calculate Time since Periapsis in Hyperbolic Orbit given Mean Anomaly, you need Angular Momentum of Hyperbolic Orbit (h_h), Eccentricity of Hyperbolic Orbit (e_h) & Mean Anomaly in Hyperbolic Orbit (M_h). With our tool, you need to enter the respective value for Angular Momentum of Hyperbolic Orbit, Eccentricity of Hyperbolic Orbit & Mean Anomaly in Hyperbolic 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 this formula, Time since Periapsis uses Angular Momentum of Hyperbolic Orbit, Eccentricity of Hyperbolic Orbit & Mean Anomaly in Hyperbolic Orbit. We can use 1 other way(s) to calculate the same, which is/are as follows -

Time since Periapsis = Angular Momentum of Hyperbolic Orbit^3/([GM.Earth]^2*(Eccentricity of Hyperbolic Orbit^2-1)^(3/2))*(Eccentricity of Hyperbolic Orbit*sinh(Eccentric Anomaly in Hyperbolic Orbit)-Eccentric Anomaly in Hyperbolic Orbit)

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