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

✖Eccentricity of Elliptical Orbit is a measure of how stretched or elongated the orbit's shape is.ⓘ Eccentricity of Elliptical Orbit [e_e]			+10% -10%
✖True Anomaly in Elliptical Orbit measures the angle between the object's current position and the perigee (the point of closest approach to the central body) when viewed from the focus of the orbit.ⓘ True Anomaly in Elliptical Orbit [θ_e]			+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 of Elliptic Orbit [h_e]			+10% -10%

✖Radial Velocity of Satellite is the component of its velocity that is directed along the line of sight from an observer on the Earth's surface.ⓘ Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum [v_r]

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

STEP 0: Pre-Calculation Summary

Formula Used

Radial Velocity of Satellite = [GM.Earth]*Eccentricity of Elliptical Orbit*sin(True Anomaly in Elliptical Orbit)/Angular Momentum of Elliptic Orbit
v_r = [GM.Earth]*e_e*sin(θ_e)/h_e
This formula uses 1 Constants, 1 Functions, 4 Variables

Constants Used

[GM.Earth] - Earth’s Geocentric Gravitational Constant Value Taken As 3.986004418E+14

Functions Used

sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)

Variables Used

Radial Velocity of Satellite - (Measured in Meter per Second) - Radial Velocity of Satellite is the component of its velocity that is directed along the line of sight from an observer on the Earth's surface.
Eccentricity of Elliptical Orbit - Eccentricity of Elliptical Orbit is a measure of how stretched or elongated the orbit's shape is.
True Anomaly in Elliptical Orbit - (Measured in Radian) - True Anomaly in Elliptical Orbit measures the angle between the object's current position and the perigee (the point of closest approach to the central body) when viewed from the focus of the orbit.
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.

STEP 1: Convert Input(s) to Base Unit

Eccentricity of Elliptical Orbit: 0.6 --> No Conversion Required
True Anomaly in Elliptical Orbit: 135.11 Degree --> 2.3581143523691 Radian (Check conversion here)
Angular Momentum of Elliptic Orbit: 65750 Square Kilometer per Second --> 65750000000 Squaer Meter per Second (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

v_r = [GM.Earth]*e_e*sin(θ_e)/h_e --> [GM.Earth]*0.6*sin(2.3581143523691)/65750000000

Evaluating ... ...

v_r = 2567.10056776404

STEP 3: Convert Result to Output's Unit

2567.10056776404 Meter per Second -->2.56710056776404 Kilometer per Second (Check conversion here)

FINAL ANSWER

2.56710056776404 ≈ 2.567101 Kilometer per Second <-- Radial Velocity of Satellite

(Calculation completed in 00.004 seconds)

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Indian Institute of Technology, Kharagpur (IIT KGP), West Bengal

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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

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

LaTeX Go

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

What is Elliptic Orbit ?

An elliptical orbit is a type of orbit in celestial mechanics where an object, such as a satellite or a planet, follows a path that is elliptical in shape around another body, such as a star or a planet. In an elliptical orbit, the object moves in a closed path around the central body, with the central body located at one of the two foci of the ellipse.

How to Calculate Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum?

Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum calculator uses Radial Velocity of Satellite = [GM.Earth]*Eccentricity of Elliptical Orbit*sin(True Anomaly in Elliptical Orbit)/Angular Momentum of Elliptic Orbit to calculate the Radial Velocity of Satellite, Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum formula is defined as a measure of the velocity of an object in an elliptical orbit around a central body, providing insight into the object's motion and position in the orbit. Radial Velocity of Satellite is denoted by v_r symbol.

How to calculate Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum using this online calculator? To use this online calculator for Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum, enter Eccentricity of Elliptical Orbit (e_e), True Anomaly in Elliptical Orbit (θ_e) & Angular Momentum of Elliptic Orbit (h_e) and hit the calculate button. Here is how the Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum calculation can be explained with given input values -> 0.002567 = [GM.Earth]*0.6*sin(2.3581143523691)/65750000000.

FAQ

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

Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum formula is defined as a measure of the velocity of an object in an elliptical orbit around a central body, providing insight into the object's motion and position in the orbit and is represented as v_r = [GM.Earth]*e_e*sin(θ_e)/h_e or 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 is a measure of how stretched or elongated the orbit's shape is, True Anomaly in Elliptical Orbit measures the angle between the object's current position and the perigee (the point of closest approach to the central body) when viewed from the focus of the 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.

How to calculate Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum?

Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum formula is defined as a measure of the velocity of an object in an elliptical orbit around a central body, providing insight into the object's motion and position in the orbit is calculated using Radial Velocity of Satellite = [GM.Earth]*Eccentricity of Elliptical Orbit*sin(True Anomaly in Elliptical Orbit)/Angular Momentum of Elliptic Orbit. To calculate Radial Velocity in Elliptic Orbit given True Anomaly, Eccentricity, and Angular Momentum, you need Eccentricity of Elliptical Orbit (e_e), True Anomaly in Elliptical Orbit (θ_e) & Angular Momentum of Elliptic Orbit (h_e). With our tool, you need to enter the respective value for Eccentricity of Elliptical Orbit, True Anomaly in Elliptical Orbit & Angular Momentum of Elliptic Orbit 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 Radial Velocity of Satellite?

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

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

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