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

✖Apogee Radius in Elliptic Orbit represents the maximum distance between an orbiting body and the object it orbits.ⓘ Apogee Radius in Elliptic Orbit [r_e,apogee]			+10% -10%
✖Velocity of Satellite at Apogee refers to the speed at which a satellite travels when it is at its farthest point from the celestial body it is orbiting, such as Earth.ⓘ Velocity of Satellite at Apogee [v_apogee]			+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 Apogee Radius and Apogee Velocity [h_e]

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

STEP 0: Pre-Calculation Summary

Formula Used

Angular Momentum of Elliptic Orbit = Apogee Radius in Elliptic Orbit*Velocity of Satellite at Apogee
h_e = r_e,apogee*v_apogee
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.
Apogee Radius in Elliptic Orbit - (Measured in Meter) - Apogee Radius in Elliptic Orbit represents the maximum distance between an orbiting body and the object it orbits.
Velocity of Satellite at Apogee - (Measured in Meter per Second) - Velocity of Satellite at Apogee refers to the speed at which a satellite travels when it is at its farthest point from the celestial body it is orbiting, such as Earth.

STEP 1: Convert Input(s) to Base Unit

Apogee Radius in Elliptic Orbit: 27110 Kilometer --> 27110000 Meter (Check conversion here)
Velocity of Satellite at Apogee: 2.425304316 Kilometer per Second --> 2425.304316 Meter per Second (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

h_e = r_e,apogee*v_apogee --> 27110000*2425.304316

Evaluating ... ...

h_e = 65750000006.76

STEP 3: Convert Result to Output's Unit

65750000006.76 Squaer Meter per Second -->65750.00000676 Square Kilometer per Second (Check conversion here)

FINAL ANSWER

65750.00000676 ≈ 65750 Square Kilometer per Second <-- Angular Momentum of Elliptic Orbit

(Calculation completed in 00.004 seconds)

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< Elliptical Orbit Parameters Calculators

Eccentricity of Elliptical Orbit given Apogee and Perigee

LaTeX 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)

Apogee Radius of Elliptic Orbit Given Angular Momentum and Eccentricity

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

Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii

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

Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity

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

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

LaTeX Go

Angular Momentum of Elliptic Orbit = Apogee Radius in Elliptic Orbit*Velocity of Satellite at Apogee
h_e = r_e,apogee*v_apogee

What is Apogee Velocity ?

Apogee velocity refers to the velocity of an object at its apogee, which is the point in its orbit where it is farthest from the central body it is orbiting, in orbital mechanics, the velocity of an object in orbit is not constant; it changes as the object moves along its elliptical path due to the influence of gravitational forces. At apogee, the object reaches its maximum distance from the central body and thus experiences its lowest orbital velocity in its elliptical orbit.

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

Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity calculator uses Angular Momentum of Elliptic Orbit = Apogee Radius in Elliptic Orbit*Velocity of Satellite at Apogee to calculate the Angular Momentum of Elliptic Orbit, Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity formula is defined as a measure of the tendency of an object to resist changes in its rotational motion as it orbits around a central body in an elliptical path. Angular Momentum of Elliptic Orbit is denoted by h_e symbol.

How to calculate Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity using this online calculator? To use this online calculator for Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity, enter Apogee Radius in Elliptic Orbit (r_e,apogee) & Velocity of Satellite at Apogee (v_apogee) and hit the calculate button. Here is how the Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity calculation can be explained with given input values -> 0.065606 = 27110000*2425.304316.

FAQ

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

Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity formula is defined as a measure of the tendency of an object to resist changes in its rotational motion as it orbits around a central body in an elliptical path and is represented as h_e = r_e,apogee*v_apogee or Angular Momentum of Elliptic Orbit = Apogee Radius in Elliptic Orbit*Velocity of Satellite at Apogee. Apogee Radius in Elliptic Orbit represents the maximum distance between an orbiting body and the object it orbits & Velocity of Satellite at Apogee refers to the speed at which a satellite travels when it is at its farthest point from the celestial body it is orbiting, such as Earth.

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

Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity formula is defined as a measure of the tendency of an object to resist changes in its rotational motion as it orbits around a central body in an elliptical path is calculated using Angular Momentum of Elliptic Orbit = Apogee Radius in Elliptic Orbit*Velocity of Satellite at Apogee. To calculate Angular Momentum in Elliptic Orbit Given Apogee Radius and Apogee Velocity, you need Apogee Radius in Elliptic Orbit (r_e,apogee) & Velocity of Satellite at Apogee (v_apogee). With our tool, you need to enter the respective value for Apogee Radius in Elliptic Orbit & Velocity of Satellite at Apogee 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 Apogee Radius in Elliptic Orbit & Velocity of Satellite at Apogee. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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