Formula Used:
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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. It is a fundamental parameter in orbital mechanics that describes the position of an object along its parabolic trajectory.
The calculator uses the following formula:
Where:
Explanation: This formula calculates the true anomaly for a parabolic orbit using the object's angular momentum and radial distance from the central body.
Details: Accurate true anomaly calculation is crucial for determining the position of satellites and spacecraft in parabolic orbits, which is essential for orbital maneuver planning, trajectory analysis, and mission operations.
Tips: Enter angular momentum in m²/s and radial position in meters. Both values must be positive numbers. The calculator will return the true anomaly in degrees.
Q1: What is a parabolic orbit?
A: A parabolic orbit is a special case of an open orbit where the eccentricity equals exactly 1. Objects in parabolic orbits have exactly escape velocity and will never return.
Q2: Why is Earth's gravitational constant used?
A: The formula uses Earth's specific gravitational parameter because the calculation is designed for objects orbiting Earth. For other celestial bodies, the appropriate GM value should be used.
Q3: What range of values can true anomaly take?
A: For parabolic orbits, true anomaly can range from -180° to +180°, with 0° at periapsis.
Q4: When might this calculation return an error?
A: The calculation may return an error if the computed value for the acos function falls outside the valid range of [-1, 1], which can occur with invalid input values.
Q5: How accurate is this calculation?
A: The calculation is mathematically exact for the given formula, assuming precise input values and using the defined gravitational constant for Earth.