fastoad.models.performances.mission.segments.cruise module

Classes for simulating cruise segments.

class fastoad.models.performances.mission.segments.cruise.CruiseSegment(*args, **kwargs)

Bases: fastoad.models.performances.mission.segments.base.RegulatedThrustSegment

Class for computing cruise flight segment at constant altitude.

Mach is considered constant, equal to Mach at starting point. Altitude is constant. Target is a specified ground_distance. The target definition indicates the ground_distance to be covered during the segment, independently of the initial value.

Only keyword arguments are accepted.

Parameters

• target – the target flight point, defined for any relevant parameter

• propulsion – the propulsion model

• reference_area – the reference area for aerodynamic forces

• polar – the aerodynamic polar

compute_from(start: fastoad.base.flight_point.FlightPoint) → pandas.core.frame.DataFrame

Computes the flight path segment from provided start point.

Computation ends when target is attained, or if the computation stops getting closer to target. For instance, a climb computation with too low thrust will only return one flight point, that is the provided start point.

Parameters

start – the initial flight point, defined for altitude, mass and speed (true_airspeed, equivalent_airspeed or mach). Can also be defined for time and/or ground_distance.

Returns

a pandas DataFrame where columns are given by FlightPoint.labels

class fastoad.models.performances.mission.segments.cruise.OptimalCruiseSegment(*args, **kwargs)

Bases: fastoad.models.performances.mission.segments.cruise.CruiseSegment

Class for computing cruise flight segment at maximum lift/drag ratio.

Mach is considered constant, equal to Mach at starting point. Altitude is set at every point to get the optimum CL according to current mass.

Only keyword arguments are accepted.

Parameters

• target – the target flight point, defined for any relevant parameter

• propulsion – the propulsion model

• reference_area – the reference area for aerodynamic forces

• polar – the aerodynamic polar

compute_from(start: fastoad.base.flight_point.FlightPoint) → pandas.core.frame.DataFrame

Computes the flight path segment from provided start point.

Computation ends when target is attained, or if the computation stops getting closer to target. For instance, a climb computation with too low thrust will only return one flight point, that is the provided start point.

Parameters

start – the initial flight point, defined for altitude, mass and speed (true_airspeed, equivalent_airspeed or mach). Can also be defined for time and/or ground_distance.

Returns

a pandas DataFrame where columns are given by FlightPoint.labels