## True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity Solution

STEP 0: Pre-Calculation Summary
Formula Used
True Anomaly of Asymptote in Hyperbolic Orbit = acos(-1/Eccentricity of Hyperbolic Orbit)
θinf = acos(-1/eh)
This formula uses 2 Functions, 2 Variables
Functions Used
cos - Trigonometric cosine function, cos(Angle)
acos - Inverse trigonometric cosine function, acos(Number)
Variables Used
True Anomaly of Asymptote in Hyperbolic Orbit - (Measured in Radian) - The True Anomaly of Asymptote in Hyperbolic Orbit represents the angular measure of the position of an object within its hyperbolic trajectory relative to the asymptote.
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
Eccentricity of Hyperbolic Orbit: 1.339 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
θinf = acos(-1/eh) --> acos(-1/1.339)
Evaluating ... ...
θinf = 2.41407271939116
STEP 3: Convert Result to Output's Unit
2.41407271939116 Radian -->138.316178258809 Degree (Check conversion here)
138.316178258809 138.3162 Degree <-- True Anomaly of Asymptote in Hyperbolic Orbit
(Calculation completed in 00.004 seconds)
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## Credits

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Indian Institute of Technology, Kharagpur (IIT KGP), Kharagpur, West Bengal
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## < 6 Hyperbolic Orbits Calculators

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

## True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity Formula

True Anomaly of Asymptote in Hyperbolic Orbit = acos(-1/Eccentricity of Hyperbolic Orbit)
θinf = acos(-1/eh)

## Why are parabolic trajectories also called escape trajectories?

If the body of some mass m is launched on a parabolic trajectory, it will coast to infinity, arriving there with zero velocity relative to central body. It will not return. Parabolic paths are therefore called escape trajectories.

## How to Calculate True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity?

True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity calculator uses True Anomaly of Asymptote in Hyperbolic Orbit = acos(-1/Eccentricity of Hyperbolic Orbit) to calculate the True Anomaly of Asymptote in Hyperbolic Orbit, The True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity formula is defined as the angular position of satellite when it is on the asymptote of the orbit. True Anomaly of Asymptote in Hyperbolic Orbit is denoted by θinf symbol.

How to calculate True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity using this online calculator? To use this online calculator for True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity, enter Eccentricity of Hyperbolic Orbit (eh) and hit the calculate button. Here is how the True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity calculation can be explained with given input values -> 7924.933 = acos(-1/1.339).

### FAQ

What is True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity?
The True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity formula is defined as the angular position of satellite when it is on the asymptote of the orbit and is represented as θinf = acos(-1/eh) or True Anomaly of Asymptote in Hyperbolic Orbit = acos(-1/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.
How to calculate True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity?
The True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity formula is defined as the angular position of satellite when it is on the asymptote of the orbit is calculated using True Anomaly of Asymptote in Hyperbolic Orbit = acos(-1/Eccentricity of Hyperbolic Orbit). To calculate True Anomaly of Asymptote in Hyperbolic Orbit given Eccentricity, you need Eccentricity of Hyperbolic Orbit (eh). With our tool, you need to enter the respective value for 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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