dyad.Orbit

class dyad.Orbit(m, a, e, Omega=0.0, i=0.0, omega=0.0)[source]

A class representing an elliptical orbit

Represents the bound orbit of a body in a gravitational central potential.

Parameters:

Attributes:

angular_momentum: Get the body’s specific angular momentum
angular_momentum_magnitude: Get the magnitude of the body’s specific angular momentum
apoapsis: Get the apoapsis of the orbit
area: Get the area contained by the orbit
argument_of_pericentre: Get the orbit’s argument of pericentre
central_mass: Get the central mass
eccentricity: Get the orbit’s eccentricity
eccentricity_vector: Get the eccentricity vector of the orbit
energy: Get the body’s specific total energy
inclination: Get the inclination of the orbit
longitude_of_ascending_node: Get the longitude of the ascending node of the orbit
lrl_vector: Get the Laplace-Runge-Lenz vector of the orbit
periapsis: Get the periapsis of the orbit
period: Get the orbital period
semilatus_rectum: Get the orbit’s semilatus rectum
semimajor_axis: Get the orbit’s semimajor axis
semiminor_axis: Get the orbit’s semiminor axis

Methods

`delaunay_elements`([theta])	Get the Delaunay elements of the orbit
`eccentric_anomaly`(theta)	Return the body's eccentric anomaly
`kinetic_energy`(theta)	Return the body's specific kinetic energy
`mean_anomaly`(theta)	Return the body's mean anomaly
`modified_delaunay_elements`([theta])	Get the modified Delaunay elements of the orbit
`orbital_elements`([theta])	Get the orbital elements of the orbit
`potential`(theta)	Return the gravitational potential at the body's position
`radius`(theta)	Return the body's radius
`speed`(theta)	Return the body's speed
`state`(theta)	Return the orbital state vector in Cartesian coordinates

Examples

Scalar parameters defining a single orbit in the perifocal plane.

>>> dyad.Orbit(1., 1., 0.)
<dyad._core.Orbit object at 0x...>

Scalar parameters defining a single orbit in the observer’s frame.

>>> dyad.Orbit(1., 1., 0., 1., 1., 1.)
<dyad._core.Orbit object at 0x...>

Array-like parameters defining multiple orbits.

>>> m, a, e = [1., 1.], [1., 1.], [0., 0.]
>>> dyad.Orbit(m, a, e)
<dyad._core.Orbit object at 0x...>

Methods

`__init__`(m, a, e[, Omega, i, omega])
`delaunay_elements`([theta])	Get the Delaunay elements of the orbit
`eccentric_anomaly`(theta)	Return the body's eccentric anomaly
`kinetic_energy`(theta)	Return the body's specific kinetic energy
`mean_anomaly`(theta)	Return the body's mean anomaly
`modified_delaunay_elements`([theta])	Get the modified Delaunay elements of the orbit
`orbital_elements`([theta])	Get the orbital elements of the orbit
`potential`(theta)	Return the gravitational potential at the body's position
`radius`(theta)	Return the body's radius
`speed`(theta)	Return the body's speed
`state`(theta)	Return the orbital state vector in Cartesian coordinates

Attributes

`angular_momentum`	Get the body's specific angular momentum
`angular_momentum_magnitude`	Get the magnitude of the body's specific angular momentum
`apoapsis`	Get the apoapsis of the orbit
`area`	Get the area contained by the orbit
`argument_of_pericentre`	Get the orbit's argument of pericentre
`central_mass`	Get the central mass
`eccentricity`	Get the orbit's eccentricity
`eccentricity_vector`	Get the eccentricity vector of the orbit
`energy`	Get the body's specific total energy
`inclination`	Get the inclination of the orbit
`longitude_of_ascending_node`	Get the longitude of the ascending node of the orbit
`lrl_vector`	Get the Laplace-Runge-Lenz vector of the orbit
`periapsis`	Get the periapsis of the orbit
`period`	Get the orbital period
`semilatus_rectum`	Get the orbit's semilatus rectum
`semimajor_axis`	Get the orbit's semimajor axis
`semiminor_axis`	Get the orbit's semiminor axis