Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity Solution

STEP 0: Pre-Calculation Summary
Formula Used
Perigee Radius = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(1+Eccentricity of Hyperbolic Orbit))
rperigee = hh^2/([GM.Earth]*(1+eh))
This formula uses 1 Constants, 3 Variables
Constants Used
[GM.Earth] - Earth’s Geocentric Gravitational Constant Value Taken As 3.986004418E+14
Variables Used
Perigee Radius - (Measured in Meter) - Perigee Radius 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.
Angular Momentum of Hyperbolic Orbit - (Measured in Squaer Meter per Second) - Angular Momentum of Hyperbolic 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.
Eccentricity of Hyperbolic Orbit - Eccentricity of Hyperbolic Orbit describes how much the orbit differs from a perfect circle, and this value typically falls between 1 and infinity.
STEP 1: Convert Input(s) to Base Unit
Angular Momentum of Hyperbolic Orbit: 65700 Square Kilometer per Second --> 65700000000 Squaer Meter per Second (Check conversion ​here)
Eccentricity of Hyperbolic Orbit: 1.339 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
rperigee = hh^2/([GM.Earth]*(1+eh)) --> 65700000000^2/([GM.Earth]*(1+1.339))
Evaluating ... ...
rperigee = 4629805.44742964
STEP 3: Convert Result to Output's Unit
4629805.44742964 Meter -->4629.80544742964 Kilometer (Check conversion ​here)
FINAL ANSWER
4629.80544742964 4629.805 Kilometer <-- Perigee Radius
(Calculation completed in 00.020 seconds)

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Hperbolic Orbit Parameters Calculators

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​ LaTeX ​ Go Radial Position in Hyperbolic Orbit = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(1+Eccentricity of Hyperbolic Orbit*cos(True Anomaly)))
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​ LaTeX ​ Go Semi Major Axis of Hyperbolic Orbit = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(Eccentricity of Hyperbolic Orbit^2-1))
Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity
​ LaTeX ​ Go Perigee Radius = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(1+Eccentricity of Hyperbolic Orbit))
Turn Angle given Eccentricity
​ LaTeX ​ Go Turn Angle = 2*asin(1/Eccentricity of Hyperbolic Orbit)

Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity Formula

​LaTeX ​Go
Perigee Radius = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(1+Eccentricity of Hyperbolic Orbit))
rperigee = hh^2/([GM.Earth]*(1+eh))

What is Gravitational Attraction ?

Gravitational attraction refers to the force of attraction between two objects with mass due to gravity. This force is described by Isaac Newton's law of universal gravitation, which states that every particle of matter in the universe attracts every other particle with a force that is directly proportional to the product of their masses and inversely proportional to the square of the distance between their centers.

How to Calculate Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity?

Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity calculator uses Perigee Radius = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(1+Eccentricity of Hyperbolic Orbit)) to calculate the Perigee Radius, The Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity formula is defined as the distance from the center of the central body to the closest point of the hyperbolic orbit, this formula allows for the calculation of the perigee radius based on two critical parameters: angular momentum and eccentricity. Perigee Radius is denoted by rperigee symbol.

How to calculate Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity using this online calculator? To use this online calculator for Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity, enter Angular Momentum of Hyperbolic Orbit (hh) & Eccentricity of Hyperbolic Orbit (eh) and hit the calculate button. Here is how the Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity calculation can be explained with given input values -> 4.629805 = 65700000000^2/([GM.Earth]*(1+1.339)).

FAQ

What is Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity?
The Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity formula is defined as the distance from the center of the central body to the closest point of the hyperbolic orbit, this formula allows for the calculation of the perigee radius based on two critical parameters: angular momentum and eccentricity and is represented as rperigee = hh^2/([GM.Earth]*(1+eh)) or Perigee Radius = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(1+Eccentricity of Hyperbolic Orbit)). Angular Momentum of Hyperbolic 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 & Eccentricity of Hyperbolic Orbit describes how much the orbit differs from a perfect circle, and this value typically falls between 1 and infinity.
How to calculate Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity?
The Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity formula is defined as the distance from the center of the central body to the closest point of the hyperbolic orbit, this formula allows for the calculation of the perigee radius based on two critical parameters: angular momentum and eccentricity is calculated using Perigee Radius = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(1+Eccentricity of Hyperbolic Orbit)). To calculate Perigee Radius of Hyperbolic Orbit given Angular Momentum and Eccentricity, you need Angular Momentum of Hyperbolic Orbit (hh) & Eccentricity of Hyperbolic Orbit (eh). With our tool, you need to enter the respective value for Angular Momentum of Hyperbolic Orbit & Eccentricity of Hyperbolic 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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