ostk.astrodynamics.flight.Maneuver¶

class Maneuver( self: ostk.astrodynamics.flight.Maneuver, states: list[ostk.astrodynamics.trajectory.State], )¶

Bases: pybind11_object

Spacecraft Maneuver class. Store an acceleration and mass flow rate profile of a spacecraft maneuver.

Constructor.

Parameters:: states (list[State]) -- An list of states, must be sorted, must include the CartesianPosition, CartesianVelocity, CartesianAcceleration and MassFlowRate subsets.

Methods

`calculate_average_specific_impulse`	Calculate the average specific impulse of the maneuver.
`calculate_average_thrust`	Calculate the average thrust of the maneuver.
`calculate_delta_mass`	Calculate the delta mass of the maneuver.
`calculate_delta_v`	Calculate the delta-v of the maneuver.
`constant_mass_flow_rate_profile`	Create a maneuver from a constant mass flow rate profile.
`get_interval`	Get the interval of the maneuver.
`get_states`	Get the states.
`is_defined`	Check if the maneuver is defined.
`to_tabulated_dynamics`	Convert the maneuver to tabulated dynamics.

calculate_average_specific_impulse( self: ostk.astrodynamics.flight.Maneuver, initial_spacecraft_mass: ostk.physics.unit.Mass, ) → ostk.core.type.Real¶

Calculate the average specific impulse of the maneuver.

Parameters:: initial_spacecraft_mass (Mass) -- The initial mass of the spacecraft.
Returns:: The average specific impulse (s).
Return type:: float

calculate_average_thrust( self: ostk.astrodynamics.flight.Maneuver, initial_spacecraft_mass: ostk.physics.unit.Mass, ) → ostk.core.type.Real¶

Calculate the average thrust of the maneuver.

Parameters:: initial_spacecraft_mass (Mass) -- The initial mass of the spacecraft.
Returns:: The average thrust (N).
Return type:: float

calculate_delta_mass( self: ostk.astrodynamics.flight.Maneuver, ) → ostk.physics.unit.Mass¶

Calculate the delta mass of the maneuver.

Returns:: The delta mass (always positive) (kg).
Return type:: Mass

calculate_delta_v( self: ostk.astrodynamics.flight.Maneuver, ) → ostk.core.type.Real¶

Calculate the delta-v of the maneuver.

Returns:: The delta-v value (m/s).
Return type:: float

static constant_mass_flow_rate_profile( states: list[ostk.astrodynamics.trajectory.State], mass_flow_rate: ostk.core.type.Real, ) → ostk.astrodynamics.flight.Maneuver¶

Create a maneuver from a constant mass flow rate profile.

Parameters:

instants (list[Instant]) -- An array of instants, must be sorted.
acceleration_profile (list[numpy.ndarray]) -- An acceleration profile of the maneuver, one numpy.ndarray per instant.
frame (Frame) -- A frame in which the acceleration profile is defined.
mass_flow_rate (float) -- The constant mass flow rate (negative number expected).

Returns:

The created maneuver.

Return type:

Maneuver

get_interval( self: ostk.astrodynamics.flight.Maneuver, ) → ostk.physics.time.Interval¶

Get the interval of the maneuver.

Returns:: The interval.
Return type:: Interval

get_states( self: ostk.astrodynamics.flight.Maneuver, ) → list[ostk.astrodynamics.trajectory.State]¶

Get the states.

Returns:: The states.
Return type:: list[State]

is_defined(self: ostk.astrodynamics.flight.Maneuver) → bool¶

Check if the maneuver is defined.

Returns:: True if the maneuver is defined, False otherwise. (Always returns true).
Return type:: bool

to_tabulated_dynamics( self: ostk.astrodynamics.flight.Maneuver, frame: ostk.physics.coordinate.Frame = GCRF, interpolation_type: ostk.mathematics.curve_fitting.Interpolator.Type = <Type.BarycentricRational: 0>, ) → ostk::astrodynamics::dynamics::Tabulated¶

Convert the maneuver to tabulated dynamics.

Parameters:

frame (Frame, optional) -- The frame in which the acceleration profile is defined. Defaults to the default acceleration frame.
interpolation_type (Interpolator.Type, optional) -- The interpolation type to use. Defaults to the default interpolation type.

Returns:

The tabulated dynamics.

Return type:

Tabulated