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Modified orbital eccentricity in Yukawa potential: a detailed analysis

Continuing from my previous post on Yukawa potential here, I explore deeper into the intricacies of orbital mechanics under the influence of non-Newtonian potentials, particularly focusing on the Yukawa potential. This exploration is crucial for understanding how subtle forces can alter the behaviors of celestial bodies in space.

Introduction

In classical mechanics, as described by Newton’s law of gravitation, celestial orbits are typically elliptical with the central body at one of the foci. The shape of the orbit is defined by its eccentricity e, which is a measure of how much the orbit deviates from being circular. For an elliptical orbit, the radius r as a function of the angle \theta is expressed by:

r = \frac{b}{1 + e \cos(\theta)}

where b is a semi-major axis of the ellipse, and e is the eccentricity of the orbit.

Modified eccentricity in Yukawa potential

In the context of the Yukawa potential, which modifies the classical inverse-square law of gravitation, the orbital dynamics exhibit similar characteristics but with a crucial difference in the eccentricity. Assuming a significant value of K_2 in the Yukawa potential, the orbits remain nearly elliptical but with a modified eccentricity e^{'}. The modified radius as a function of angle heta can be defined as:

r = \frac{b}{1 + e^{'} \cos(\theta)}

Here, e^{'} represents the modified eccentricity due to the Yukawa potential. The relationship between e^{'} and the original eccentricity e is pivotal for predicting the orbital paths under modified gravitational forces.

Observations at perihelion and aphelion

The perihelion r_p and aphelion r_a of an orbit are the nearest and farthest points, respectively, to the central mass. For an orbit affected by the Yukawa potential, these points are crucial for determining e^{'}. At perihelion (\theta = 0) and aphelion (\theta = \pi), the radius equations become:

  • At perihelion:

r_p = \frac{b}{1 + e^{'}}

  • At aphelion:

r_a = \frac{b}{1 - e^{'}}

These equations facilitate the calculation of the semi-major axis and the modified eccentricity by using observational data from actual orbital paths.

For more insights into this topic, you can find the details here.