True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum Calculator

✖Angular Momentum of Parabolic 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 Parabolic Orbit [h_p]			+10% -10%
✖Radial Position in Parabolic Orbit refers to the distance of the satellite along the radial or straight-line direction connecting the satellite and the center of the body.ⓘ Radial Position in Parabolic Orbit [r_p]			+10% -10%

✖True Anomaly in Parabolic 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 Parabolic Orbit given Radial Position and Angular Momentum [θ_p]

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True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum Solution

STEP 0: Pre-Calculation Summary

Formula Used

True Anomaly in Parabolic Orbit = acos(Angular Momentum of Parabolic Orbit^2/([GM.Earth]*Radial Position in Parabolic Orbit)-1)
θ_p = acos(h_p^2/([GM.Earth]*r_p)-1)
This formula uses 1 Constants, 2 Functions, 3 Variables

Constants Used

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

Functions Used

cos - Cosine of an angle is the ratio of the side adjacent to the angle to the hypotenuse of the triangle., cos(Angle)
acos - The inverse cosine function, is the inverse function of the cosine function. It is the function that takes a ratio as an input and returns the angle whose cosine is equal to that ratio., acos(Number)

Variables Used

True Anomaly in Parabolic Orbit - (Measured in Radian) - True Anomaly in Parabolic 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 Parabolic Orbit - (Measured in Squaer Meter per Second) - Angular Momentum of Parabolic 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.
Radial Position in Parabolic Orbit - (Measured in Meter) - Radial Position in Parabolic Orbit refers to the distance of the satellite along the radial or straight-line direction connecting the satellite and the center of the body.

STEP 1: Convert Input(s) to Base Unit

Angular Momentum of Parabolic Orbit: 73508 Square Kilometer per Second --> 73508000000 Squaer Meter per Second (Check conversion here)
Radial Position in Parabolic Orbit: 23479 Kilometer --> 23479000 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

θ_p = acos(h_p^2/([GM.Earth]*r_p)-1) --> acos(73508000000^2/([GM.Earth]*23479000)-1)

Evaluating ... ...

θ_p = 2.00714507179796

STEP 3: Convert Result to Output's Unit

2.00714507179796 Radian -->115.000941484527 Degree (Check conversion here)

FINAL ANSWER

115.000941484527 ≈ 115.0009 Degree <-- True Anomaly in Parabolic Orbit

(Calculation completed in 00.004 seconds)

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Home » Physics » Orbital Mechanics » The Two Body Problem » Parabolic Orbits » Aerospace » Parabolic Orbit Parameters » True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum

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Created by Harsh Raj

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

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< Parabolic Orbit Parameters Calculators

X Coordinate of Parabolic Trajectory given Parameter of Orbit

LaTeX Go X Coordinate Value = Parameter of Parabolic Orbit*(cos(True Anomaly in Parabolic Orbit)/(1+cos(True Anomaly in Parabolic Orbit)))

Y Coordinate of Parabolic Trajectory given Parameter of Orbit

LaTeX Go Y Coordinate Value = Parameter of Parabolic Orbit*sin(True Anomaly in Parabolic Orbit)/(1+cos(True Anomaly in Parabolic Orbit))

Escape Velocity given Radius of Parabolic Trajectory

LaTeX Go Escape Velocity in Parabolic Orbit = sqrt((2*[GM.Earth])/Radial Position in Parabolic Orbit)

Radial Position in Parabolic Orbit given Escape Velocity

LaTeX Go Radial Position in Parabolic Orbit = (2*[GM.Earth])/Escape Velocity in Parabolic Orbit^2

True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum Formula

LaTeX Go

True Anomaly in Parabolic Orbit = acos(Angular Momentum of Parabolic Orbit^2/([GM.Earth]*Radial Position in Parabolic Orbit)-1)
θ_p = acos(h_p^2/([GM.Earth]*r_p)-1)

What is specific angular momentum ?

Specific angular momentum is a concept used in celestial mechanics to describe the rotational motion of an object in orbit around a central body. It is defined as the cross product of the position vector of the object with its velocity vector.

How to Calculate True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum?

True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum calculator uses True Anomaly in Parabolic Orbit = acos(Angular Momentum of Parabolic Orbit^2/([GM.Earth]*Radial Position in Parabolic Orbit)-1) to calculate the True Anomaly in Parabolic Orbit, The True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum formula is defined as current angular position of the object within its parabolic orbit, this formula allows for the calculation of the true anomaly based on two essential parameters: radial position and angular momentum. True Anomaly in Parabolic Orbit is denoted by θ_p symbol.

How to calculate True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum using this online calculator? To use this online calculator for True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum, enter Angular Momentum of Parabolic Orbit (h_p) & Radial Position in Parabolic Orbit (r_p) and hit the calculate button. Here is how the True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum calculation can be explained with given input values -> 4333.819 = acos(73508000000^2/([GM.Earth]*23479000)-1).

FAQ

What is True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum?

The True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum formula is defined as current angular position of the object within its parabolic orbit, this formula allows for the calculation of the true anomaly based on two essential parameters: radial position and angular momentum and is represented as θ_p = acos(h_p^2/([GM.Earth]*r_p)-1) or True Anomaly in Parabolic Orbit = acos(Angular Momentum of Parabolic Orbit^2/([GM.Earth]*Radial Position in Parabolic Orbit)-1). Angular Momentum of Parabolic 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 & Radial Position in Parabolic Orbit refers to the distance of the satellite along the radial or straight-line direction connecting the satellite and the center of the body.

How to calculate True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum?

The True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum formula is defined as current angular position of the object within its parabolic orbit, this formula allows for the calculation of the true anomaly based on two essential parameters: radial position and angular momentum is calculated using True Anomaly in Parabolic Orbit = acos(Angular Momentum of Parabolic Orbit^2/([GM.Earth]*Radial Position in Parabolic Orbit)-1). To calculate True Anomaly in Parabolic Orbit given Radial Position and Angular Momentum, you need Angular Momentum of Parabolic Orbit (h_p) & Radial Position in Parabolic Orbit (r_p). With our tool, you need to enter the respective value for Angular Momentum of Parabolic Orbit & Radial Position in Parabolic 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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