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

✖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]

⎘ Copy

👎

Formula

✖

Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius

Formula

v apogee = \frac{h e}{r e,apogee}

Example

2.425304 km/s = \frac{65750 km²/s}{27110 km}

Calculator

LaTeX

Reset

👍

Download Elliptical Orbits Formulas PDF PDF Image

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)

You are here -

Home » Physics » Orbital Mechanics » The Two Body Problem » Elliptical Orbits » Aerospace » Elliptical Orbit Parameters » Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius

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!

< Elliptical Orbit Parameters Calculators

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)

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))

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 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 Formula

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

What is Apogee ?

The term "apogee" typically refers to the highest point or farthest distance in an object's orbit around a central body. In the context of orbits around Earth or another celestial body, apogee specifically refers to the point where the orbiting object is farthest from the central body.

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, Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius formula is defined as the maximum velocity an object achieves in an elliptical orbit, which depends on the angular momentum and apogee radius of the orbit, providing crucial information for space mission design and celestial mechanics studies. 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?

Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius formula is defined as the maximum velocity an object achieves in an elliptical orbit, which depends on the angular momentum and apogee radius of the orbit, providing crucial information for space mission design and celestial mechanics studies 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?

Apogee Velocity in Elliptic Orbit Given Angular Momentum and Apogee Radius formula is defined as the maximum velocity an object achieves in an elliptical orbit, which depends on the angular momentum and apogee radius of the orbit, providing crucial information for space mission design and celestial mechanics studies 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.

Home

FREE PDFs

🔍 Search