ostk.astrodynamics.flight.system.SatelliteSystemBuilder¶

class SatelliteSystemBuilder(self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder)¶

Bases: pybind11_object

A Satellite System Builder, meant to simplify creation of a SatelliteSystem, by allowing you to only specify the parameters you want. There are two ways of doing this:

Chaining together your desired parameters like so:

satellite_system = SatelliteSystemBuilder().with_dry_mass(X).with_area(Y).build()

Using the default SatelliteSystem and changing one parameters like so:

satellite_system = SatelliteSystemBuilder.default().with_dry_mass(X)

Constructor.

Methods

`build`	Build a new satellite system.
`default`	Create a satellite system builder with default values.
`with_cross_sectional_surface_area`	Set the dry mass.
`with_drag_coefficient`	Set the drag coefficient.
`with_dry_mass`	Set the dry mass.
`with_geometry`	Set the geometry.
`with_inertia_tensor`	Set the inertia tensor.
`with_propulsion_system`	Set the propulsion system.

build( self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder, ) → ostk.astrodynamics.flight.system.SatelliteSystem¶

Build a new satellite system.

Returns:: A new satellite system.
Return type:: SatelliteSystem

static default() → ostk.astrodynamics.flight.system.SatelliteSystemBuilder¶

Create a satellite system builder with default values.

Returns:: The satellite system builder with default values.
Return type:: SatelliteSystem

with_cross_sectional_surface_area( self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder, cross_sectional_surface_area: ostk.core.type.Real, ) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder¶

Set the dry mass.

Parameters:: cross_sectional_surface_area (float) -- The cross-sectional surface area.
Returns:: The builder.
Return type:: SatelliteSystemBuilder

with_drag_coefficient( self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder, drag_coefficient: ostk.core.type.Real, ) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder¶

Set the drag coefficient.

Parameters:: drag_coefficient (float) -- The drag coefficient.
Returns:: The builder.
Return type:: SatelliteSystemBuilder

with_dry_mass( self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder, dry_mass: ostk.physics.unit.Mass, ) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder¶

Set the dry mass.

Parameters:: dry_mass (Mass) -- The dry mass.
Returns:: The builder.
Return type:: SatelliteSystemBuilder

with_geometry( self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder, geometry: ostk.mathematics.geometry.d3.object.Composite, ) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder¶

Set the geometry.

Parameters:: geometry (Composite) -- The geometry.
Returns:: The builder.
Return type:: SatelliteSystemBuilder

with_inertia_tensor( self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder, inertia_tensor: numpy.ndarray[numpy.float64[3, 3]], ) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder¶

Set the inertia tensor.

Parameters:: inertia_tensor (Matrix3d) -- The inertia tensor.
Returns:: The builder.
Return type:: SatelliteSystemBuilder

with_propulsion_system( self: ostk.astrodynamics.flight.system.SatelliteSystemBuilder, propulsion_system: ostk.astrodynamics.flight.system.PropulsionSystem, ) → ostk.astrodynamics.flight.system.SatelliteSystemBuilder¶

Set the propulsion system.

Parameters:: propulsion_system (PropulsionSystem) -- The propulsion system.
Returns:: The builder.
Return type:: SatelliteSystemBuilder