True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity Solution

STEP 0: Pre-Calculation Summary
Formula Used
True Anomaly = 2*atan(sqrt((Eccentricity of Hyperbolic Orbit+1)/(Eccentricity of Hyperbolic Orbit-1))*tanh(Eccentric Anomaly in Hyperbolic Orbit/2))
θ = 2*atan(sqrt((eh+1)/(eh-1))*tanh(F/2))
This formula uses 4 Functions, 3 Variables
Functions Used
tan - Trigonometric tangent function, tan(Angle)
atan - Inverse trigonometric tangent function, atan(Number)
sqrt - Square root function, sqrt(Number)
tanh - Hyperbolic tangent function, tanh(Number)
Variables Used
True Anomaly - (Measured in Radian) - True Anomaly 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.
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.
Eccentric Anomaly in Hyperbolic Orbit - (Measured in Radian) - Eccentric Anomaly in Hyperbolic Orbit is an angular parameter that characterizes the position of an object within its hyperbolic trajectory.
STEP 1: Convert Input(s) to Base Unit
Eccentricity of Hyperbolic Orbit: 1.339 --> No Conversion Required
Eccentric Anomaly in Hyperbolic Orbit: 2.3 Radian --> 2.3 Radian No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
θ = 2*atan(sqrt((eh+1)/(eh-1))*tanh(F/2)) --> 2*atan(sqrt((1.339+1)/(1.339-1))*tanh(2.3/2))
Evaluating ... ...
θ = 2.27018065686813
STEP 3: Convert Result to Output's Unit
2.27018065686813 Radian -->130.071770370805 Degree (Check conversion here)
130.071770370805 130.0718 Degree <-- True Anomaly
(Calculation completed in 00.004 seconds)
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< 5 Orbital Position as Function of Time Calculators

Time since Periapsis in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly
Time since Periapsis = Angular Momentum of Orbit^3/([GM.Earth]^2*(Eccentricity of Hyperbolic Orbit^2-1)^(3/2))*(Eccentricity of Hyperbolic Orbit*sinh(Eccentric Anomaly in Hyperbolic Orbit)-Eccentric Anomaly in Hyperbolic Orbit)
True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity
True Anomaly = 2*atan(sqrt((Eccentricity of Hyperbolic Orbit+1)/(Eccentricity of Hyperbolic Orbit-1))*tanh(Eccentric Anomaly in Hyperbolic Orbit/2))
Hyperbolic Eccentric Anomaly given Eccentricity and True Anomaly
Eccentric Anomaly in Hyperbolic Orbit = 2*atanh(sqrt((Eccentricity of Hyperbolic Orbit-1)/(Eccentricity of Hyperbolic Orbit+1))*tan(True Anomaly/2))
Mean Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly
Mean Anomaly in Hyperbolic Orbit = Eccentricity of Hyperbolic Orbit*sinh(Eccentric Anomaly in Hyperbolic Orbit)-Eccentric Anomaly in Hyperbolic Orbit
Time since Periapsis in Hyperbolic Orbit given Mean Anomaly
Time since Periapsis = Angular Momentum of Orbit^3/([GM.Earth]^2*(Eccentricity of Hyperbolic Orbit^2-1)^(3/2))*Mean Anomaly in Hyperbolic Orbit

True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity Formula

True Anomaly = 2*atan(sqrt((Eccentricity of Hyperbolic Orbit+1)/(Eccentricity of Hyperbolic Orbit-1))*tanh(Eccentric Anomaly in Hyperbolic Orbit/2))
θ = 2*atan(sqrt((eh+1)/(eh-1))*tanh(F/2))

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 in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity?

True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity calculator uses True Anomaly = 2*atan(sqrt((Eccentricity of Hyperbolic Orbit+1)/(Eccentricity of Hyperbolic Orbit-1))*tanh(Eccentric Anomaly in Hyperbolic Orbit/2)) to calculate the True Anomaly, The True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity formula is defined as the current angular position of the object within the hyperbolic orbit based on eccentric anomaly and eccentricity. True Anomaly is denoted by θ symbol.

How to calculate True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity using this online calculator? To use this online calculator for True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity, enter Eccentricity of Hyperbolic Orbit (eh) & Eccentric Anomaly in Hyperbolic Orbit (F) and hit the calculate button. Here is how the True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity calculation can be explained with given input values -> 7452.563 = 2*atan(sqrt((1.339+1)/(1.339-1))*tanh(2.3/2)).

FAQ

What is True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity?
The True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity formula is defined as the current angular position of the object within the hyperbolic orbit based on eccentric anomaly and eccentricity and is represented as θ = 2*atan(sqrt((eh+1)/(eh-1))*tanh(F/2)) or True Anomaly = 2*atan(sqrt((Eccentricity of Hyperbolic Orbit+1)/(Eccentricity of Hyperbolic Orbit-1))*tanh(Eccentric Anomaly in Hyperbolic Orbit/2)). Eccentricity of Hyperbolic Orbit describes how much the orbit differs from a perfect circle, and this value typically falls between 1 and infinity & Eccentric Anomaly in Hyperbolic Orbit is an angular parameter that characterizes the position of an object within its hyperbolic trajectory.
How to calculate True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity?
The True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity formula is defined as the current angular position of the object within the hyperbolic orbit based on eccentric anomaly and eccentricity is calculated using True Anomaly = 2*atan(sqrt((Eccentricity of Hyperbolic Orbit+1)/(Eccentricity of Hyperbolic Orbit-1))*tanh(Eccentric Anomaly in Hyperbolic Orbit/2)). To calculate True Anomaly in Hyperbolic Orbit given Hyperbolic Eccentric Anomaly and Eccentricity, you need Eccentricity of Hyperbolic Orbit (eh) & Eccentric Anomaly in Hyperbolic Orbit (F). With our tool, you need to enter the respective value for Eccentricity of Hyperbolic Orbit & Eccentric Anomaly in 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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