Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii Calculator

⤿

The Two Body Problem

⤿

Elliptical Orbits

Circular Orbits

Fundamental Parameters

Hyperbolic Orbits

Parabolic Orbits

⤿

Elliptical Orbit Parameters

Orbital Position as Function of Time

✖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%
✖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%

✖Semi Major Axis of Elliptic Orbit is half of the major axis, which is the longest diameter of the ellipse describing the orbit.ⓘ Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii [a_e]

⎘ Copy

👎

Formula

✖

Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii

Formula

`"a"_{"e"} = ("r"_{"e,apogee"}+"r"_{"e,perigee"})/2`

Example

`"16944km"=("27110km"+"6778km")/2`

Calculator

LaTeX

Reset

👍

Download Elliptical Orbits Formulas PDF PDF Image

Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii Solution

STEP 0: Pre-Calculation Summary

Formula Used

Semi Major Axis of Elliptic Orbit = (Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit)/2
a_e = (r_e,apogee+r_e,perigee)/2
This formula uses 3 Variables

Variables Used

Semi Major Axis of Elliptic Orbit - (Measured in Meter) - Semi Major Axis of Elliptic Orbit is half of the major axis, which is the longest diameter of the ellipse describing the orbit.
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.
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.

STEP 1: Convert Input(s) to Base Unit

Apogee Radius in Elliptic Orbit: 27110 Kilometer --> 27110000 Meter (Check conversion here)
Perigee Radius in Elliptic Orbit: 6778 Kilometer --> 6778000 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

a_e = (r_e,apogee+r_e,perigee)/2 --> (27110000+6778000)/2

Evaluating ... ...

a_e = 16944000

STEP 3: Convert Result to Output's Unit

16944000 Meter -->16944 Kilometer (Check conversion here)

FINAL ANSWER

16944 Kilometer <-- Semi Major Axis of Elliptic Orbit

(Calculation completed in 00.020 seconds)

You are here -

Home » Physics » Orbital Mechanics » The Two Body Problem » Elliptical Orbits » Elliptical Orbit Parameters » Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii

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!

< 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)

Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii Formula

Semi Major Axis of Elliptic Orbit = (Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit)/2
a_e = (r_e,apogee+r_e,perigee)/2

What does elliptical orbit mean?

The definition of an elliptical orbit is an oval-shaped path, like a slightly elongated circle. This is due to the gravitational interactions among the Sun, planets, and other celestial bodies that move in elliptical paths.

How to Calculate Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii?

Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii calculator uses Semi Major Axis of Elliptic Orbit = (Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit)/2 to calculate the Semi Major Axis of Elliptic Orbit, The Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii formula is defined as half of the major axis, which is the longest diameter of the ellipse describing the orbit. Semi Major Axis of Elliptic Orbit is denoted by a_e symbol.

How to calculate Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii using this online calculator? To use this online calculator for Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii, enter Apogee Radius in Elliptic Orbit (r_e,apogee) & Perigee Radius in Elliptic Orbit (r_e,perigee) and hit the calculate button. Here is how the Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii calculation can be explained with given input values -> 16.944 = (27110000+6778000)/2.

FAQ

What is Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii?

The Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii formula is defined as half of the major axis, which is the longest diameter of the ellipse describing the orbit and is represented as a_e = (r_e,apogee+r_e,perigee)/2 or Semi Major Axis of Elliptic Orbit = (Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit)/2. Apogee Radius in Elliptic Orbit represents the maximum distance between an orbiting body and the object it orbits & 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.

How to calculate Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii?

The Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii formula is defined as half of the major axis, which is the longest diameter of the ellipse describing the orbit is calculated using Semi Major Axis of Elliptic Orbit = (Apogee Radius in Elliptic Orbit+Perigee Radius in Elliptic Orbit)/2. To calculate Semimajor Axis of Elliptic Orbit given Apogee and Perigee Radii, you need Apogee Radius in Elliptic Orbit (r_e,apogee) & Perigee Radius in Elliptic Orbit (r_e,perigee). With our tool, you need to enter the respective value for Apogee Radius in Elliptic Orbit & Perigee 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