Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius 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

✖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 of Elliptic Orbit [h_e]			+10% -10%
✖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.ⓘ Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius [v_apogee]

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Formula

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Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius

Formula

`"v"_{"apogee"} = "h"_{"e"}/"r"_{"e,apogee"}`

Example

`"2.425304km/s"="65750km²/s"/"27110km"`

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

STEP 0: Pre-Calculation Summary

Formula Used

Velocity of Satellite at Apogee = Angular Momentum of Elliptic Orbit/Apogee Radius in Elliptic Orbit
v_apogee = h_e/r_e,apogee
This formula uses 3 Variables

Variables Used

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.
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.

STEP 1: Convert Input(s) to Base Unit

Angular Momentum of Elliptic Orbit: 65750 Square Kilometer per Second --> 65750000000 Squaer Meter per Second (Check conversion here)
Apogee Radius in Elliptic Orbit: 27110 Kilometer --> 27110000 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

v_apogee = h_e/r_e,apogee --> 65750000000/27110000

Evaluating ... ...

v_apogee = 2425.30431575065

STEP 3: Convert Result to Output's Unit

2425.30431575065 Meter per Second -->2.42530431575065 Kilometer per Second (Check conversion here)

FINAL ANSWER

2.42530431575065 ≈ 2.425304 Kilometer per Second <-- Velocity of Satellite at Apogee

(Calculation completed in 00.004 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)

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

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

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

Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius calculator uses Velocity of Satellite at Apogee = Angular Momentum of Elliptic Orbit/Apogee Radius in Elliptic Orbit to calculate the Velocity of Satellite at Apogee, The Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius formula is defined as the velocity of the object at the farthest point of its orbit, known as the apogee. This formula allows for the calculation of the apogee velocity based on two critical parameters: angular momentum and apogee radius. Velocity of Satellite at Apogee is denoted by v_apogee symbol.

How to calculate Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius using this online calculator? To use this online calculator for Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius, enter Angular Momentum of Elliptic Orbit (h_e) & Apogee Radius in Elliptic Orbit (r_e,apogee) and hit the calculate button. Here is how the Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius calculation can be explained with given input values -> 0.002425 = 65750000000/27110000.

FAQ

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

The Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius formula is defined as the velocity of the object at the farthest point of its orbit, known as the apogee. This formula allows for the calculation of the apogee velocity based on two critical parameters: angular momentum and apogee radius and is represented as v_apogee = h_e/r_e,apogee or Velocity of Satellite at Apogee = Angular Momentum of Elliptic Orbit/Apogee Radius in Elliptic Orbit. 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 represents the maximum distance between an orbiting body and the object it orbits.

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

The Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius formula is defined as the velocity of the object at the farthest point of its orbit, known as the apogee. This formula allows for the calculation of the apogee velocity based on two critical parameters: angular momentum and apogee radius is calculated using Velocity of Satellite at Apogee = Angular Momentum of Elliptic Orbit/Apogee Radius in Elliptic Orbit. To calculate Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius, you need Angular Momentum of Elliptic Orbit (h_e) & Apogee Radius in Elliptic Orbit (r_e,apogee). With our tool, you need to enter the respective value for Angular Momentum of Elliptic Orbit & Apogee Radius in Elliptic 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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