fastoad.models.performances.mission.segments.transition module¶

Class for very simple transition in some flight phases.

class fastoad.models.performances.mission.segments.transition.DummyTransitionSegment(target: fastoad.model_base.flight_point.FlightPoint, propulsion: Optional[fastoad.model_base.propulsion.IPropulsion] = None, polar: Optional[fastoad.models.performances.mission.polar.Polar] = None, reference_area: float = 1.0, time_step: float = 0.2, engine_setting: fastoad.constants.EngineSetting = <EngineSetting.CLIMB: 2>, altitude_bounds: tuple = (-500.0, 40000.0), mach_bounds: tuple = (0.0, 5.0), name: str = '', interrupt_if_getting_further_from_target: bool = True, mass_ratio: float = 1.0, reserve_mass_ratio: float = 0.0)[source]¶

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

Computes a transient flight part in a very quick and dummy way.

compute_from() will return only 2 or 3 flight points.

The second flight point is the end of transition and its mass is the start mass multiplied by mass_ratio. Other parameters are equal to those provided in target.

If reserve_mass_ratio is non-zero, a third flight point, with parameters equal to flight_point(2), except for mass where:

mass(2) - reserve_mass_ratio * mass(3) = mass(3).

In different words, mass(3) would be the Zero Fuel Weight (ZFW) and reserve can be expressed as a percentage of ZFW.

mass_ratio: float = 1.0¶: The ratio (aircraft mass at END of segment)/(aircraft mass at START of segment)

reserve_mass_ratio: float = 0.0¶: The ratio (fuel mass)/(aircraft mass at END of segment) that will be consumed at end of segment.

propulsion: fastoad.model_base.propulsion.IPropulsion = None¶: Unused

reference_area: float = 1.0¶: Unused

polar: fastoad.models.performances.mission.polar.Polar = None¶: Unused

compute_from(start: fastoad.model_base.flight_point.FlightPoint) → pandas.core.frame.DataFrame[source]¶

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 names match fields of FlightPoint()