ostk.astrodynamics.flight.system.SatelliteSystem

class SatelliteSystem(

self: ostk.astrodynamics.flight.system.SatelliteSystem,

mass: ostk.physics.unit.Mass,

satellite_geometry: ostk.mathematics.geometry.d3.object.Composite,

inertia_tensor: numpy.ndarray[numpy.float64[3, 3]],

cross_sectional_surface_area: ostk.core.type.Real,

drag_coefficient: ostk.core.type.Real,

propulsion_system: ostk.astrodynamics.flight.system.PropulsionSystem = undefined,

)

Bases: System

A Satellite System.

Constructor.

Parameters:

• mass (Mass) -- The mass of the satellite system.

• satellite_geometry (Composite) -- The geometry of the satellite system.

• inertia_tensor (np.ndarray) -- The inertia tensor of the satellite system.

• cross_sectional_surface_area (float) -- The cross-sectional surface area of the satellite system.

• drag_coefficient (float) -- The drag coefficient of the satellite system.

• propulsion_system (PropulsionSystem) -- The propulsion system of the satellite system.

Methods

default	Create a default satellite system.
get_cross_sectional_surface_area	Get the cross-sectional surface area of the satellite system.
get_drag_coefficient	Get the drag coefficient of the satellite system.
get_geometry	Get the geometry of the system.
get_inertia_tensor	Get the inertia tensor of the satellite system.
get_mass	Get the mass of the system.
get_propulsion_system	Get the propulsion system of the satellite system.
is_defined	Check if the satellite system is defined.
undefined	Create an undefined satellite system.

static default() → ostk.astrodynamics.flight.system.SatelliteSystem

Create a default satellite system.

Returns:

The default satellite system.

Return type:

SatelliteSystem

get_cross_sectional_surface_area(

self: ostk.astrodynamics.flight.system.SatelliteSystem,

) → ostk.core.type.Real

Get the cross-sectional surface area of the satellite system.

Returns:

The cross-sectional surface area of the satellite system.

Return type:

float

get_drag_coefficient(

self: ostk.astrodynamics.flight.system.SatelliteSystem,

) → ostk.core.type.Real

Get the drag coefficient of the satellite system.

Returns:

The drag coefficient of the satellite system.

Return type:

float

get_geometry(

self: ostk.astrodynamics.flight.System,

) → ostk.mathematics.geometry.d3.object.Composite

Get the geometry of the system.

Returns:

The geometry of the system.

Return type:

Composite

get_inertia_tensor(

self: ostk.astrodynamics.flight.system.SatelliteSystem,

) → numpy.ndarray[numpy.float64[3, 3]]

Get the inertia tensor of the satellite system.

Returns:

The inertia tensor of the satellite system.

Return type:

Matrix3d

get_mass(

self: ostk.astrodynamics.flight.System,

) → ostk.physics.unit.Mass

Get the mass of the system.

Returns:

The mass of the system.

Return type:

Mass

get_propulsion_system(

self: ostk.astrodynamics.flight.system.SatelliteSystem,

) → ostk.astrodynamics.flight.system.PropulsionSystem

Get the propulsion system of the satellite system.

Returns:

The propulsion system of the satellite system.

Return type:

PropulsionSystem

is_defined(

self: ostk.astrodynamics.flight.system.SatelliteSystem,

) → bool

Check if the satellite system is defined.

Returns:

True if the satellite system is defined, False otherwise.

Return type:

bool

static undefined() → ostk.astrodynamics.flight.system.SatelliteSystem

Create an undefined satellite system.

Returns:

The undefined satellite system.

Return type:

SatelliteSystem