Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity Calculator

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The Two Body Problem

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Elliptical Orbits

Circular Orbits

Fundamental Parameters

Hyperbolic Orbits

Parabolic Orbits

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Elliptical Orbit Parameters

Orbital Position as Function of Time

✖Perigee Radius in Elliptic Orbit refers to the distance between the center of the Earth and the point in a satellite's orbit that is closest to the Earth's surface.ⓘ Perigee Radius in Elliptic Orbit [r_e,perigee]			+10% -10%
✖Velocity of Satellite at Perigee is the velocity at which a satellite travels when it is at its closest point (perigee) to the celestial body it is orbiting, such as Earth.ⓘ Velocity of Satellite at Perigee [v_perigee]			+10% -10%

✖Angular Momentum of Elliptic 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 in Elliptic Orbit Given Perigee Radius and Perigee Velocity [h_e]

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Formula

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Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity

Formula

`"h"_{"e"} = "r"_{"e,perigee"}*"v"_{"perigee"}`

Example

`"65746.6km²/s"="6778km"*"9.7km/s"`

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Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity Solution

STEP 0: Pre-Calculation Summary

Formula Used

Angular Momentum of Elliptic Orbit = Perigee Radius in Elliptic Orbit*Velocity of Satellite at Perigee
h_e = r_e,perigee*v_perigee
This formula uses 3 Variables

Variables Used

Angular Momentum of Elliptic Orbit - (Measured in Squaer Meter per Second) - Angular Momentum of Elliptic 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.
Perigee Radius in Elliptic Orbit - (Measured in Meter) - Perigee Radius in Elliptic Orbit refers to the distance between the center of the Earth and the point in a satellite's orbit that is closest to the Earth's surface.
Velocity of Satellite at Perigee - (Measured in Meter per Second) - Velocity of Satellite at Perigee is the velocity at which a satellite travels when it is at its closest point (perigee) to the celestial body it is orbiting, such as Earth.

STEP 1: Convert Input(s) to Base Unit

Perigee Radius in Elliptic Orbit: 6778 Kilometer --> 6778000 Meter (Check conversion here)
Velocity of Satellite at Perigee: 9.7 Kilometer per Second --> 9700 Meter per Second (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

h_e = r_e,perigee*v_perigee --> 6778000*9700

Evaluating ... ...

h_e = 65746600000

STEP 3: Convert Result to Output's Unit

65746600000 Squaer Meter per Second -->65746.6 Square Kilometer per Second (Check conversion here)

FINAL ANSWER

65746.6 Square Kilometer per Second <-- Angular Momentum of Elliptic Orbit

(Calculation completed in 00.020 seconds)

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< 17 Elliptical Orbit Parameters Calculators

True Anomaly in Elliptic Orbit Given Radial Position, Eccentricity, and Angular Momentum

Go True Anomaly in Elliptical Orbit = acos((Angular Momentum of Elliptic Orbit^2/([GM.Earth]*Radial Position in Elliptical Orbit)-1)/Eccentricity of Elliptical Orbit)

Time Period of Elliptical Orbit given Semi-Major Axis

Go Time Period of Elliptic Orbit = 2*pi*Semi Major Axis of Elliptic Orbit^2*sqrt(1-Eccentricity of Elliptical Orbit^2)/Angular Momentum of Elliptic Orbit

Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum

Go Radial Velocity of Satellite = [GM.Earth]*Eccentricity of Elliptical Orbit*sin(True Anomaly in Elliptical Orbit)/Angular Momentum of Elliptic Orbit

Eccentricity of Elliptical Orbit given Apogee and Perigee

Go Eccentricity of Elliptical Orbit = (Apogee Radius in Elliptic Orbit-Perigee Radius in Elliptic Orbit)/(Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit)

Time Period for One Complete Revolution given Angular Momentum

Go Time Period of Elliptic Orbit = (2*pi*Semi Major Axis of Elliptic Orbit*Semi Minor Axis of Elliptic Orbit)/Angular Momentum of Elliptic Orbit

Elliptical Orbit Time Period given Angular Momentum and Eccentricity

Go Time Period of Elliptic Orbit = (2*pi)/[GM.Earth]^2*(Angular Momentum of Elliptic Orbit/sqrt(1-Eccentricity of Elliptical Orbit^2))^3

Time Period of Elliptical Orbit given Angular Momentum

Go Time Period of Elliptic Orbit = (2*pi)/[GM.Earth]^2*(Angular Momentum of Elliptic Orbit/sqrt(1-Eccentricity of Elliptical Orbit^2))^3

Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity

Go Apogee Radius in Elliptic Orbit = Angular Momentum of Elliptic Orbit^2/([GM.Earth]*(1-Eccentricity of Elliptical Orbit))

Specific Energy of Elliptic Orbit given Angular Momentum

Go Specific Energy of Elliptical Orbit = -1/2*[GM.Earth]^2/Angular Momentum of Elliptic Orbit^2*(1-Eccentricity of Elliptical Orbit^2)

Azimuth-Averaged Radius Given Apogee and Perigee Radii

Go Azimuth Averaged Radius = sqrt(Apogee Radius in Elliptic Orbit*Perigee Radius in Elliptic Orbit)

Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii

Go Semi Major Axis of Elliptic Orbit = (Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit)/2

Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity

Go Angular Momentum of Elliptic Orbit = Perigee Radius in Elliptic Orbit*Velocity of Satellite at Perigee

Radial Velocity in Elliptic Orbit given Radial Position and Angular Momentum

Go Radial Velocity of Satellite = Angular Momentum of Elliptic Orbit/Radial Position in Elliptical Orbit

Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity

Go Angular Momentum of Elliptic Orbit = Apogee Radius in Elliptic Orbit*Velocity of Satellite at Apogee

Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius

Go Velocity of Satellite at Apogee = Angular Momentum of Elliptic Orbit/Apogee Radius in Elliptic Orbit

Eccentricity of Orbit

Go Eccentricity of Elliptical Orbit = Distance Between Two Foci/(2*Semi Major Axis of Elliptic Orbit)

Specific Energy of Elliptic Orbit given Semi Major Axis

Go Specific Energy of Elliptical Orbit = -[GM.Earth]/(2*Semi Major Axis of Elliptic Orbit)

Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity Formula

Angular Momentum of Elliptic Orbit = Perigee Radius in Elliptic Orbit*Velocity of Satellite at Perigee
h_e = r_e,perigee*v_perigee

Kepler's Laws and Gravitational Attraction

Johannes Kepler's laws of planetary motion, developed in the 17th century, provided significant insights into the relationship between celestial bodies and gravity. Kepler's laws describe the elliptical orbits of planets and other objects in the solar system, all of which are governed by the gravitational pull of the central body, such as the Sun. These laws laid the foundation for understanding how gravity affects the motion of objects in space, paving the way for Sir Isaac Newton's formulation of the law of universal gravitation.

How to Calculate Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity?

Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity calculator uses Angular Momentum of Elliptic Orbit = Perigee Radius in Elliptic Orbit*Velocity of Satellite at Perigee to calculate the Angular Momentum of Elliptic Orbit, The Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity formula is defined as product of two fundamental parameters: perigee radius and perigee velocity. Angular Momentum of Elliptic Orbit is denoted by h_e symbol.

How to calculate Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity using this online calculator? To use this online calculator for Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity, enter Perigee Radius in Elliptic Orbit (r_e,perigee) & Velocity of Satellite at Perigee (v_perigee) and hit the calculate button. Here is how the Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity calculation can be explained with given input values -> 0.065747 = 6778000*9700.

FAQ

What is Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity?

The Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity formula is defined as product of two fundamental parameters: perigee radius and perigee velocity and is represented as h_e = r_e,perigee*v_perigee or Angular Momentum of Elliptic Orbit = Perigee Radius in Elliptic Orbit*Velocity of Satellite at Perigee. Perigee Radius in Elliptic Orbit refers to the distance between the center of the Earth and the point in a satellite's orbit that is closest to the Earth's surface & Velocity of Satellite at Perigee is the velocity at which a satellite travels when it is at its closest point (perigee) to the celestial body it is orbiting, such as Earth.

How to calculate Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity?

The Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity formula is defined as product of two fundamental parameters: perigee radius and perigee velocity is calculated using Angular Momentum of Elliptic Orbit = Perigee Radius in Elliptic Orbit*Velocity of Satellite at Perigee. To calculate Angular Momentum in Elliptic Orbit Given Perigee Radius and Perigee Velocity, you need Perigee Radius in Elliptic Orbit (r_e,perigee) & Velocity of Satellite at Perigee (v_perigee). With our tool, you need to enter the respective value for Perigee Radius in Elliptic Orbit & Velocity of Satellite at Perigee 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 Angular Momentum of Elliptic Orbit?

In this formula, Angular Momentum of Elliptic Orbit uses Perigee Radius in Elliptic Orbit & Velocity of Satellite at Perigee. We can use 1 other way(s) to calculate the same, which is/are as follows -

Angular Momentum of Elliptic Orbit = Apogee Radius in Elliptic Orbit*Velocity of Satellite at Apogee

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