ostk.astrodynamics.trajectory.orbit.model.ModifiedEquinoctial¶

class ModifiedEquinoctial( self: ostk.astrodynamics.trajectory.orbit.model.ModifiedEquinoctial, semi_latus_rectum: ostk.physics.unit.Length, eccentricity_x: ostk.core.type.Real, eccentricity_y: ostk.core.type.Real, node_x: ostk.core.type.Real, node_y: ostk.core.type.Real, true_longitude: ostk.physics.unit.Angle, )¶

Bases: pybind11_object

Modified Equinoctial Orbital Elements (ModifiedEquinoctial).

The Modified Equinoctial Orbital Elements (ModifiedEquinoctial) provide a non-singular representation of an orbit, useful for a wide range of eccentricities and inclinations (except for i = 180 deg).

Elements: p: semi-latus rectum (m) f: x-component of eccentricity vector (e * cos(RAAN + AOP)) g: y-component of eccentricity vector (e * sin(RAAN + AOP)) h: x-component of node vector (tan(i/2) * cos(RAAN)) k: y-component of node vector (tan(i/2) * sin(RAAN)) L: true longitude (RAAN + AOP + True Anomaly) (rad)

Constructor.

Parameters:

semi_latus_rectum (Length) -- Semi-latus rectum.
eccentricity_x (float) -- x-component of eccentricity vector.
eccentricity_y (float) -- y-component of eccentricity vector.
node_x (float) -- x-component of node vector.
node_y (float) -- y-component of node vector.
true_longitude (Angle) -- True longitude.

Methods

`cartesian`	Create ModifiedEquinoctial from Cartesian state (position, velocity).
`coe`	Create Modified Equinoctial elements from Classical Orbital Elements (COE).
`get_cartesian_state`	Get Cartesian state (position, velocity) from ModifiedEquinoctial.
`get_eccentricity_x`	Get x-component of eccentricity vector (f).
`get_eccentricity_y`	Get y-component of eccentricity vector (g).
`get_node_x`	Get x-component of node vector (h).
`get_node_y`	Get y-component of node vector (k).
`get_semi_latus_rectum`	Get semi-latus rectum (p).
`get_si_vector`	Get ModifiedEquinoctial elements as a 6D vector in SI units.
`get_true_longitude`	Get true longitude (L).
`is_defined`	Check if ModifiedEquinoctial is defined.
`undefined`	Create an undefined ModifiedEquinoctial object.

static cartesian( cartesian_state: tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity], gravitational_parameter: ostk.physics.unit.Derived, ) → ostk.astrodynamics.trajectory.orbit.model.ModifiedEquinoctial¶

Create ModifiedEquinoctial from Cartesian state (position, velocity).

Parameters:

cartesian_state (tuple[Position, Velocity]) -- Cartesian state (Position, Velocity). Must be in an inertial frame.
gravitational_parameter (Derived) -- Gravitational parameter of the central body.

Returns:

ModifiedEquinoctial object.

Return type:

ModifiedEquinoctial

static coe( coe: ostk.astrodynamics.trajectory.orbit.model.kepler.COE, ) → ostk.astrodynamics.trajectory.orbit.model.ModifiedEquinoctial¶

Create Modified Equinoctial elements from Classical Orbital Elements (COE).

Parameters:: coe (COE) -- Classical Orbital Elements.
Returns:: Modified Equinoctial Elements.
Return type:: ModifiedEquinoctial

get_cartesian_state( self: ostk.astrodynamics.trajectory.orbit.model.ModifiedEquinoctial, gravitational_parameter: ostk.physics.unit.Derived, frame: ostk.physics.coordinate.Frame, ) → tuple[ostk.physics.coordinate.Position, ostk.physics.coordinate.Velocity]¶

Get Cartesian state (position, velocity) from ModifiedEquinoctial.

Parameters:

gravitational_parameter (Derived) -- Gravitational parameter of the central body.
frame (Frame) -- The reference frame for the output Cartesian state. Must be an inertial frame.

Returns:

Position and Velocity.

Return type: