Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity Calculator

✖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.ⓘ Angular Momentum of Hyperbolic Orbit [h_h]			+10% -10%
✖Eccentricity of Hyperbolic Orbit describes how much the orbit differs from a perfect circle, and this value typically falls between 1 and infinity.ⓘ Eccentricity of Hyperbolic Orbit [e_h]			+10% -10%

✖Semi Major Axis of Hyperbolic Orbit is a fundamental parameter that characterizes the size and shape of the hyperbolic trajectory. It represents half the length of the major axis of the orbit.ⓘ Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity [a_h]

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Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity Solution

STEP 0: Pre-Calculation Summary

Formula Used

Semi Major Axis of Hyperbolic Orbit = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(Eccentricity of Hyperbolic Orbit^2-1))
a_h = h_h^2/([GM.Earth]*(e_h^2-1))
This formula uses 1 Constants, 3 Variables

Constants Used

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

Variables Used

Semi Major Axis of Hyperbolic Orbit - (Measured in Meter) - Semi Major Axis of Hyperbolic Orbit is a fundamental parameter that characterizes the size and shape of the hyperbolic trajectory. It represents half the length of the major axis of the orbit.
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

a_h = h_h^2/([GM.Earth]*(e_h^2-1)) --> 65700000000^2/([GM.Earth]*(1.339^2-1))

Evaluating ... ...

a_h = 13657243.2077571

STEP 3: Convert Result to Output's Unit

13657243.2077571 Meter -->13657.2432077571 Kilometer (Check conversion here)

FINAL ANSWER

13657.2432077571 ≈ 13657.24 Kilometer <-- Semi Major Axis of Hyperbolic Orbit

(Calculation completed in 00.020 seconds)

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

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< Hperbolic Orbit Parameters Calculators

Radial Position in Hyperbolic Orbit given Angular Momentum, True Anomaly, and Eccentricity

LaTeX Go Radial Position in Hyperbolic Orbit = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(1+Eccentricity of Hyperbolic Orbit*cos(True Anomaly)))

Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity

LaTeX Go Semi Major Axis of Hyperbolic Orbit = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(Eccentricity of Hyperbolic Orbit^2-1))

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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)

Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity Formula

LaTeX Go

Semi Major Axis of Hyperbolic Orbit = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(Eccentricity of Hyperbolic Orbit^2-1))
a_h = h_h^2/([GM.Earth]*(e_h^2-1))

What is Semi-Major Axis of Hyperbolic Orbit ?

In a hyperbolic orbit, the semi-major axis is a bit different from that in elliptical orbits. The semi-major axis in an elliptical orbit represents half of the longest diameter of the ellipse. However, in a hyperbolic orbit, the trajectory doesn't form a closed curve like an ellipse; instead, it's open-ended.

How to Calculate Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity?

Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity calculator uses Semi Major Axis of Hyperbolic Orbit = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(Eccentricity of Hyperbolic Orbit^2-1)) to calculate the Semi Major Axis of Hyperbolic Orbit, The Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity formula is defined as a mathematical expression used to calculate the semi-major axis of an object in a hyperbolic orbit, the semi-major axis is a fundamental parameter that characterizes the size and shape of the hyperbolic orbit, this formula allows for the calculation of the semi-major axis based on two crucial parameters: angular momentum and eccentricity. Semi Major Axis of Hyperbolic Orbit is denoted by a_h symbol.

How to calculate Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity using this online calculator? To use this online calculator for Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity, enter Angular Momentum of Hyperbolic Orbit (h_h) & Eccentricity of Hyperbolic Orbit (e_h) and hit the calculate button. Here is how the Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity calculation can be explained with given input values -> 13.65724 = 65700000000^2/([GM.Earth]*(1.339^2-1)).

FAQ

What is Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity?

The Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity formula is defined as a mathematical expression used to calculate the semi-major axis of an object in a hyperbolic orbit, the semi-major axis is a fundamental parameter that characterizes the size and shape of the hyperbolic orbit, this formula allows for the calculation of the semi-major axis based on two crucial parameters: angular momentum and eccentricity and is represented as a_h = h_h^2/([GM.Earth]*(e_h^2-1)) or Semi Major Axis of Hyperbolic Orbit = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(Eccentricity of Hyperbolic Orbit^2-1)). 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 Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity?

The Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity formula is defined as a mathematical expression used to calculate the semi-major axis of an object in a hyperbolic orbit, the semi-major axis is a fundamental parameter that characterizes the size and shape of the hyperbolic orbit, this formula allows for the calculation of the semi-major axis based on two crucial parameters: angular momentum and eccentricity is calculated using Semi Major Axis of Hyperbolic Orbit = Angular Momentum of Hyperbolic Orbit^2/([GM.Earth]*(Eccentricity of Hyperbolic Orbit^2-1)). To calculate Semi-Major Axis of Hyperbolic Orbit given Angular Momentum and Eccentricity, you need Angular Momentum of Hyperbolic Orbit (h_h) & Eccentricity of Hyperbolic Orbit (e_h). 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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