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

Classes for simulating cruise segments.

class fastoad.models.performances.mission.segments.registered.cruise.CruiseSegment(name: str = '', target: ~fastoad.model_base.flight_point.FlightPoint = <object object>, isa_offset: float = 0.0, propulsion: ~fastoad.model_base.propulsion.IPropulsion = <object object>, polar: ~fastoad.models.performances.mission.polar.Polar = <object object>, polar_modifier: ~fastoad.models.performances.mission.polar_modifier.AbstractPolarModifier = <factory>, reference_area: float = <object object>, time_step: float = 60.0, maximum_CL: float = None, altitude_bounds: tuple = (-500.0, 40000.0), mach_bounds: tuple = (-1e-06, 5.0), interrupt_if_getting_further_from_target: bool = True, engine_setting: ~fastoad.constants.EngineSetting = EngineSetting.CLIMB, load_factor: float = 1.0)

Bases: AbstractRegulatedThrustSegment, AbstractLiftFromWeightSegment

Class for computing cruise flight segment at constant altitude and speed.

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.

get_distance_to_target(flight_points: List[FlightPoint], target: FlightPoint) → float

Computes a “distance” from last flight point to target.

Computed does not need to have a real meaning. The important point is that it must be signed so that algorithm knows on which “side” of the target we are. And of course, it should be 0. if flight point is on target.

Parameters:

• flight_points – list of all currently computed flight_points

• target – segment target (will not contain relative values)

Returns:

15. if target is attained, a non-null value otherwise

CONSTANT_VALUE = 'constant'

Using this value will tell to keep the associated parameter constant.

altitude_bounds: tuple = (-500.0, 40000.0)

Minimum and maximum authorized altitude values. If computed altitude gets beyond these limits, computation will be interrupted and a warning message will be issued in logger.

complete_flight_point(flight_point: FlightPoint)

Computes data for provided flight point.

Assumes that it is already defined for time, altitude, mass, ground distance and speed (TAS, EAS, or Mach).

Parameters:

flight_point – the flight point that will be completed in-place

static complete_flight_point_from(flight_point: FlightPoint, source: FlightPoint)

Sets undefined values in flight_point using the ones from source.

The particular case of speeds is taken into account: if at least one speed parameter is defined, all other speed parameters are considered defined, because they will be deduced when needed.

Parameters:

• flight_point –

• source –

compute_from(start: FlightPoint) → 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.

Important

When subclasssing, if you need to overload compute_from(), you should consider overriding compute_from_start_to_target() instead. Therefore, you will take benefit of the preprocessing of start and target flight points that is done in compute_from().

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 column names match fields of FlightPoint

compute_from_start_to_target(start: FlightPoint, target: FlightPoint) → DataFrame

Here should come the implementation for computing flight points between start and target flight points.

Parameters:

• start –

• target – Definition of segment target

Returns:

a pandas DataFrame where column names match fields of FlightPoint

compute_lift(flight_point: FlightPoint, reference_force: float, polar: Polar)

Fills values for CL, and lift in provided flight_point.

Parameters:

• flight_point –

• reference_force – CL = lift / reference_force

• polar – unused here, but can be used when overloading this method

compute_next_flight_point(flight_points: List[FlightPoint], time_step: float) → FlightPoint

Computes time, altitude, speed, mass and ground distance of next flight point.

Parameters:

• flight_points – previous flight points

• time_step – time step for computing next point

Returns:

the computed next flight point

compute_propulsion(flight_point: FlightPoint)

Computes propulsion data.

Provided flight point is modified in place.

Generally, this method should end with:

self.propulsion.compute_flight_points(flight_point)

Parameters:

flight_point –

static consume_fuel(flight_point: FlightPoint, previous: FlightPoint, fuel_consumption: float = None, mass_ratio: float = None)

This method should be used whenever fuel consumption has to be stored.

It ensures that “mass” and “consumed_fuel” fields will be kept consistent.

Mass can be modified using the ‘fuel_consumption” argument, or the ‘mass_ratio’ argument. One of them should be provided.

Parameters:

• flight_point – the FlightPoint instance where “mass” and “consumed_fuel” fields will get new values

• previous – FlightPoint instance that will be the base for the computation

• fuel_consumption – consumed fuel, in kg, between ‘previous’ and ‘flight_point’. Positive when fuel is consumed.

• mass_ratio – the ratio flight_point.mass/previous.mass

engine_setting: EngineSetting = 2

The EngineSetting value associated to the segment. Can be used in the propulsion model.

get_gamma_and_acceleration(flight_point: FlightPoint) → Tuple[float, float]

Computes slope angle (gamma) and acceleration.

Parameters:

flight_point – parameters after propulsion model has been called (i.e. mass, thrust and drag are available)

Returns:

slope angle in radians and acceleration in m**2/s

get_next_alpha(previous_point: FlightPoint, time_step: float) → float

Determine the next angle of attack.

Parameters:

• previous_point – the flight point from which next alpha is computed

• time_step – the duration between computed flight point and previous_point

interrupt_if_getting_further_from_target: bool = True

If True, computation will be interrupted if a parameter stops getting closer to target between two iterations (which can mean the provided thrust rate is not adapted).

isa_offset: float = 0.0

The temperature offset for ISA atmosphere model.

load_factor: float = 1.0

Lift is computed so it is equal to load_factor * weight

mach_bounds: tuple = (-1e-06, 5.0)

Minimum and maximum authorized mach values. If computed Mach gets beyond these limits, computation will be interrupted and a warning message will be issued in logger.

maximum_CL: float = None

name: str = ''

polar: Polar = <object object>

The Polar instance that will provide drag data.

propulsion: IPropulsion = <object object>

A IPropulsion instance that will be called at each time step.

reference_area: float = <object object>

The reference area, in m**2.

property target: FlightPoint

The base class of the class hierarchy.

When called, it accepts no arguments and returns a new featureless instance that has no instance attributes and cannot be given any.

time_step: float = 60.0

Used time step for computation (actual time step can be lower at some particular times of the flight path).

polar_modifier: AbstractPolarModifier

class fastoad.models.performances.mission.segments.registered.cruise.OptimalCruiseSegment(name: str = '', target: ~fastoad.model_base.flight_point.FlightPoint = <object object>, isa_offset: float = 0.0, propulsion: ~fastoad.model_base.propulsion.IPropulsion = <object object>, polar: ~fastoad.models.performances.mission.polar.Polar = <object object>, polar_modifier: ~fastoad.models.performances.mission.polar_modifier.AbstractPolarModifier = <factory>, reference_area: float = <object object>, time_step: float = 60.0, maximum_CL: float = None, altitude_bounds: tuple = (-500.0, 40000.0), mach_bounds: tuple = (-1e-06, 5.0), interrupt_if_getting_further_from_target: bool = True, engine_setting: ~fastoad.constants.EngineSetting = EngineSetting.CLIMB, load_factor: float = 1.0)

Bases: CruiseSegment

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

Altitude is set at every point to get the optimum CL according to current mass. Target is a specified ground_distance. The target definition indicates the ground_distance to be covered during the segment, independently of the initial value. Target should also specify a speed parameter set to “constant”, among mach, true_airspeed and equivalent_airspeed. If not, Mach will be assumed constant.

compute_from_start_to_target(start: FlightPoint, target: FlightPoint) → DataFrame

Here should come the implementation for computing flight points between start and target flight points.

Parameters:

• start –

• target – Definition of segment target

Returns:

a pandas DataFrame where column names match fields of FlightPoint

CONSTANT_VALUE = 'constant'

Using this value will tell to keep the associated parameter constant.

altitude_bounds: tuple = (-500.0, 40000.0)

Minimum and maximum authorized altitude values. If computed altitude gets beyond these limits, computation will be interrupted and a warning message will be issued in logger.

complete_flight_point(flight_point: FlightPoint)

Computes data for provided flight point.

Assumes that it is already defined for time, altitude, mass, ground distance and speed (TAS, EAS, or Mach).

Parameters:

flight_point – the flight point that will be completed in-place

static complete_flight_point_from(flight_point: FlightPoint, source: FlightPoint)

Sets undefined values in flight_point using the ones from source.

The particular case of speeds is taken into account: if at least one speed parameter is defined, all other speed parameters are considered defined, because they will be deduced when needed.

Parameters:

• flight_point –

• source –

compute_from(start: FlightPoint) → 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.

Important

When subclasssing, if you need to overload compute_from(), you should consider overriding compute_from_start_to_target() instead. Therefore, you will take benefit of the preprocessing of start and target flight points that is done in compute_from().

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 column names match fields of FlightPoint

compute_lift(flight_point: FlightPoint, reference_force: float, polar: Polar)

Fills values for CL, and lift in provided flight_point.

Parameters:

• flight_point –

• reference_force – CL = lift / reference_force

• polar – unused here, but can be used when overloading this method

compute_next_flight_point(flight_points: List[FlightPoint], time_step: float) → FlightPoint

Computes time, altitude, speed, mass and ground distance of next flight point.

Parameters:

• flight_points – previous flight points

• time_step – time step for computing next point

Returns:

the computed next flight point

compute_propulsion(flight_point: FlightPoint)

Computes propulsion data.

Provided flight point is modified in place.

Generally, this method should end with:

self.propulsion.compute_flight_points(flight_point)

Parameters:

flight_point –

static consume_fuel(flight_point: FlightPoint, previous: FlightPoint, fuel_consumption: float = None, mass_ratio: float = None)

This method should be used whenever fuel consumption has to be stored.

It ensures that “mass” and “consumed_fuel” fields will be kept consistent.

Mass can be modified using the ‘fuel_consumption” argument, or the ‘mass_ratio’ argument. One of them should be provided.

Parameters:

• flight_point – the FlightPoint instance where “mass” and “consumed_fuel” fields will get new values

• previous – FlightPoint instance that will be the base for the computation

• fuel_consumption – consumed fuel, in kg, between ‘previous’ and ‘flight_point’. Positive when fuel is consumed.

• mass_ratio – the ratio flight_point.mass/previous.mass

engine_setting: EngineSetting = 2

The EngineSetting value associated to the segment. Can be used in the propulsion model.

get_distance_to_target(flight_points: List[FlightPoint], target: FlightPoint) → float

Computes a “distance” from last flight point to target.

Computed does not need to have a real meaning. The important point is that it must be signed so that algorithm knows on which “side” of the target we are. And of course, it should be 0. if flight point is on target.

Parameters:

• flight_points – list of all currently computed flight_points

• target – segment target (will not contain relative values)

Returns:

15. if target is attained, a non-null value otherwise

get_gamma_and_acceleration(flight_point: FlightPoint) → Tuple[float, float]

Computes slope angle (gamma) and acceleration.

Parameters:

flight_point – parameters after propulsion model has been called (i.e. mass, thrust and drag are available)

Returns:

slope angle in radians and acceleration in m**2/s

get_next_alpha(previous_point: FlightPoint, time_step: float) → float

Determine the next angle of attack.

Parameters:

• previous_point – the flight point from which next alpha is computed

• time_step – the duration between computed flight point and previous_point

interrupt_if_getting_further_from_target: bool = True

If True, computation will be interrupted if a parameter stops getting closer to target between two iterations (which can mean the provided thrust rate is not adapted).

isa_offset: float = 0.0

The temperature offset for ISA atmosphere model.

load_factor: float = 1.0

Lift is computed so it is equal to load_factor * weight

mach_bounds: tuple = (-1e-06, 5.0)

Minimum and maximum authorized mach values. If computed Mach gets beyond these limits, computation will be interrupted and a warning message will be issued in logger.

maximum_CL: float = None

name: str = ''

polar: Polar = <object object>

The Polar instance that will provide drag data.

propulsion: IPropulsion = <object object>

A IPropulsion instance that will be called at each time step.

reference_area: float = <object object>

The reference area, in m**2.

property target: FlightPoint

The base class of the class hierarchy.

When called, it accepts no arguments and returns a new featureless instance that has no instance attributes and cannot be given any.

time_step: float = 60.0

Used time step for computation (actual time step can be lower at some particular times of the flight path).

polar_modifier: AbstractPolarModifier

class fastoad.models.performances.mission.segments.registered.cruise.ClimbAndCruiseSegment(name: str = '', target: ~fastoad.model_base.flight_point.FlightPoint = <object object>, isa_offset: float = 0.0, propulsion: ~fastoad.model_base.propulsion.IPropulsion = <object object>, polar: ~fastoad.models.performances.mission.polar.Polar = <object object>, polar_modifier: ~fastoad.models.performances.mission.polar_modifier.AbstractPolarModifier = <factory>, reference_area: float = <object object>, time_step: float = 60.0, maximum_CL: float = None, altitude_bounds: tuple = (-500.0, 40000.0), mach_bounds: tuple = (-1e-06, 5.0), interrupt_if_getting_further_from_target: bool = True, engine_setting: ~fastoad.constants.EngineSetting = EngineSetting.CLIMB, load_factor: float = 1.0, climb_segment: ~fastoad.models.performances.mission.segments.registered.altitude_change.AltitudeChangeSegment = None, maximum_flight_level: float = 500.0)

Bases: CruiseSegment

Class for computing cruise flight segment at constant altitude.

Target is a specified ground_distance. The target definition indicates the ground_distance to be covered during the segment, independently of the initial value. Target should also specify a speed parameter set to “constant”, among mach, true_airspeed and equivalent_airspeed. If not, Mach will be assumed constant.

Target altitude can also be set to OPTIMAL_FLIGHT_LEVEL. In that case, the cruise will be preceded by a climb segment and climb_segment must be set at instantiation.

(Target ground distance will be achieved by the sum of ground distances covered during climb and cruise)

In this case, climb will be done up to the IFR Flight Level (as multiple of 100 feet) that ensures minimum mass decrease, while being at most equal to maximum_flight_level.

climb_segment: AltitudeChangeSegment = None

The AltitudeChangeSegment that can be used if a preliminary climb is needed (its target will be ignored).

maximum_flight_level: float = 500.0

The maximum allowed flight level (i.e. multiple of 100 feet).

compute_from_start_to_target(start: FlightPoint, target: FlightPoint) → DataFrame

Here should come the implementation for computing flight points between start and target flight points.

Parameters:

• start –

• target – Definition of segment target

Returns:

a pandas DataFrame where column names match fields of FlightPoint

CONSTANT_VALUE = 'constant'

Using this value will tell to keep the associated parameter constant.

altitude_bounds: tuple = (-500.0, 40000.0)

Minimum and maximum authorized altitude values. If computed altitude gets beyond these limits, computation will be interrupted and a warning message will be issued in logger.

complete_flight_point(flight_point: FlightPoint)

Computes data for provided flight point.

Assumes that it is already defined for time, altitude, mass, ground distance and speed (TAS, EAS, or Mach).

Parameters:

flight_point – the flight point that will be completed in-place

static complete_flight_point_from(flight_point: FlightPoint, source: FlightPoint)

Sets undefined values in flight_point using the ones from source.

The particular case of speeds is taken into account: if at least one speed parameter is defined, all other speed parameters are considered defined, because they will be deduced when needed.

Parameters:

• flight_point –

• source –

compute_from(start: FlightPoint) → 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.

Important

When subclasssing, if you need to overload compute_from(), you should consider overriding compute_from_start_to_target() instead. Therefore, you will take benefit of the preprocessing of start and target flight points that is done in compute_from().

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 column names match fields of FlightPoint

compute_lift(flight_point: FlightPoint, reference_force: float, polar: Polar)

Fills values for CL, and lift in provided flight_point.

Parameters:

• flight_point –

• reference_force – CL = lift / reference_force

• polar – unused here, but can be used when overloading this method

compute_next_flight_point(flight_points: List[FlightPoint], time_step: float) → FlightPoint

Computes time, altitude, speed, mass and ground distance of next flight point.

Parameters:

• flight_points – previous flight points

• time_step – time step for computing next point

Returns:

the computed next flight point

compute_propulsion(flight_point: FlightPoint)

Computes propulsion data.

Provided flight point is modified in place.

Generally, this method should end with:

self.propulsion.compute_flight_points(flight_point)

Parameters:

flight_point –

static consume_fuel(flight_point: FlightPoint, previous: FlightPoint, fuel_consumption: float = None, mass_ratio: float = None)

This method should be used whenever fuel consumption has to be stored.

It ensures that “mass” and “consumed_fuel” fields will be kept consistent.

Mass can be modified using the ‘fuel_consumption” argument, or the ‘mass_ratio’ argument. One of them should be provided.

Parameters:

• flight_point – the FlightPoint instance where “mass” and “consumed_fuel” fields will get new values

• previous – FlightPoint instance that will be the base for the computation

• fuel_consumption – consumed fuel, in kg, between ‘previous’ and ‘flight_point’. Positive when fuel is consumed.

• mass_ratio – the ratio flight_point.mass/previous.mass

engine_setting: EngineSetting = 2

The EngineSetting value associated to the segment. Can be used in the propulsion model.

get_distance_to_target(flight_points: List[FlightPoint], target: FlightPoint) → float

Computes a “distance” from last flight point to target.

Computed does not need to have a real meaning. The important point is that it must be signed so that algorithm knows on which “side” of the target we are. And of course, it should be 0. if flight point is on target.

Parameters:

• flight_points – list of all currently computed flight_points

• target – segment target (will not contain relative values)

Returns:

15. if target is attained, a non-null value otherwise

get_gamma_and_acceleration(flight_point: FlightPoint) → Tuple[float, float]

Computes slope angle (gamma) and acceleration.

Parameters:

flight_point – parameters after propulsion model has been called (i.e. mass, thrust and drag are available)

Returns:

slope angle in radians and acceleration in m**2/s

get_next_alpha(previous_point: FlightPoint, time_step: float) → float

Determine the next angle of attack.

Parameters:

• previous_point – the flight point from which next alpha is computed

• time_step – the duration between computed flight point and previous_point

interrupt_if_getting_further_from_target: bool = True

If True, computation will be interrupted if a parameter stops getting closer to target between two iterations (which can mean the provided thrust rate is not adapted).

isa_offset: float = 0.0

The temperature offset for ISA atmosphere model.

load_factor: float = 1.0

Lift is computed so it is equal to load_factor * weight

mach_bounds: tuple = (-1e-06, 5.0)

Minimum and maximum authorized mach values. If computed Mach gets beyond these limits, computation will be interrupted and a warning message will be issued in logger.

maximum_CL: float = None

name: str = ''

polar: Polar = <object object>

The Polar instance that will provide drag data.

propulsion: IPropulsion = <object object>

A IPropulsion instance that will be called at each time step.

reference_area: float = <object object>

The reference area, in m**2.

property target: FlightPoint

The base class of the class hierarchy.

When called, it accepts no arguments and returns a new featureless instance that has no instance attributes and cannot be given any.

time_step: float = 60.0

Used time step for computation (actual time step can be lower at some particular times of the flight path).

polar_modifier: AbstractPolarModifier

class fastoad.models.performances.mission.segments.registered.cruise.BreguetCruiseSegment(name: str = '', target: ~fastoad.model_base.flight_point.FlightPoint = <object object>, isa_offset: float = 0.0, propulsion: ~fastoad.model_base.propulsion.IPropulsion = <object object>, polar: ~fastoad.models.performances.mission.polar.Polar = <object object>, polar_modifier: ~fastoad.models.performances.mission.polar_modifier.AbstractPolarModifier = <factory>, reference_area: float = 1.0, time_step: float = 60.0, maximum_CL: float = None, altitude_bounds: tuple = (-500.0, 40000.0), mach_bounds: tuple = (-1e-06, 5.0), interrupt_if_getting_further_from_target: bool = True, engine_setting: ~fastoad.constants.EngineSetting = EngineSetting.CLIMB, load_factor: float = 1.0, use_max_lift_drag_ratio: bool = False)

Bases: CruiseSegment

Class for computing cruise flight segment at constant altitude using Breguet-Leduc formula.

As formula relies on SFC, the propulsion model must be able to fill FlightPoint.sfc when FlightPoint.thrust is provided.

use_max_lift_drag_ratio: bool = False

if True, max lift/drag ratio will be used instead of the one computed with polar using CL deduced from mass and altitude. In this case, reference_area parameter will be unused

reference_area: float = 1.0

The reference area, in m**2. Used only if use_max_lift_drag_ratio is False.

compute_from_start_to_target(start: FlightPoint, target: FlightPoint) → DataFrame

Here should come the implementation for computing flight points between start and target flight points.

Parameters:

• start –

• target – Definition of segment target

Returns:

a pandas DataFrame where column names match fields of FlightPoint

CONSTANT_VALUE = 'constant'

Using this value will tell to keep the associated parameter constant.

altitude_bounds: tuple = (-500.0, 40000.0)

Minimum and maximum authorized altitude values. If computed altitude gets beyond these limits, computation will be interrupted and a warning message will be issued in logger.

complete_flight_point(flight_point: FlightPoint)

Computes data for provided flight point.

Assumes that it is already defined for time, altitude, mass, ground distance and speed (TAS, EAS, or Mach).

Parameters:

flight_point – the flight point that will be completed in-place

static complete_flight_point_from(flight_point: FlightPoint, source: FlightPoint)

Sets undefined values in flight_point using the ones from source.

The particular case of speeds is taken into account: if at least one speed parameter is defined, all other speed parameters are considered defined, because they will be deduced when needed.

Parameters:

• flight_point –

• source –

compute_from(start: FlightPoint) → 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.

Important

When subclasssing, if you need to overload compute_from(), you should consider overriding compute_from_start_to_target() instead. Therefore, you will take benefit of the preprocessing of start and target flight points that is done in compute_from().

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 column names match fields of FlightPoint

compute_lift(flight_point: FlightPoint, reference_force: float, polar: Polar)

Fills values for CL, and lift in provided flight_point.

Parameters:

• flight_point –

• reference_force – CL = lift / reference_force

• polar – unused here, but can be used when overloading this method

compute_next_flight_point(flight_points: List[FlightPoint], time_step: float) → FlightPoint

Computes time, altitude, speed, mass and ground distance of next flight point.

Parameters:

• flight_points – previous flight points

• time_step – time step for computing next point

Returns:

the computed next flight point

compute_propulsion(flight_point: FlightPoint)

Computes propulsion data.

Provided flight point is modified in place.

Generally, this method should end with:

self.propulsion.compute_flight_points(flight_point)

Parameters:

flight_point –

static consume_fuel(flight_point: FlightPoint, previous: FlightPoint, fuel_consumption: float = None, mass_ratio: float = None)

This method should be used whenever fuel consumption has to be stored.

It ensures that “mass” and “consumed_fuel” fields will be kept consistent.

Mass can be modified using the ‘fuel_consumption” argument, or the ‘mass_ratio’ argument. One of them should be provided.

Parameters:

• flight_point – the FlightPoint instance where “mass” and “consumed_fuel” fields will get new values

• previous – FlightPoint instance that will be the base for the computation

• fuel_consumption – consumed fuel, in kg, between ‘previous’ and ‘flight_point’. Positive when fuel is consumed.

• mass_ratio – the ratio flight_point.mass/previous.mass

engine_setting: EngineSetting = 2

The EngineSetting value associated to the segment. Can be used in the propulsion model.

get_distance_to_target(flight_points: List[FlightPoint], target: FlightPoint) → float

Computes a “distance” from last flight point to target.

Computed does not need to have a real meaning. The important point is that it must be signed so that algorithm knows on which “side” of the target we are. And of course, it should be 0. if flight point is on target.

Parameters:

• flight_points – list of all currently computed flight_points

• target – segment target (will not contain relative values)

Returns:

15. if target is attained, a non-null value otherwise

get_gamma_and_acceleration(flight_point: FlightPoint) → Tuple[float, float]

Computes slope angle (gamma) and acceleration.

Parameters:

flight_point – parameters after propulsion model has been called (i.e. mass, thrust and drag are available)

Returns:

slope angle in radians and acceleration in m**2/s

get_next_alpha(previous_point: FlightPoint, time_step: float) → float

Determine the next angle of attack.

Parameters:

• previous_point – the flight point from which next alpha is computed

• time_step – the duration between computed flight point and previous_point

interrupt_if_getting_further_from_target: bool = True

If True, computation will be interrupted if a parameter stops getting closer to target between two iterations (which can mean the provided thrust rate is not adapted).

isa_offset: float = 0.0

The temperature offset for ISA atmosphere model.

load_factor: float = 1.0

Lift is computed so it is equal to load_factor * weight

mach_bounds: tuple = (-1e-06, 5.0)

Minimum and maximum authorized mach values. If computed Mach gets beyond these limits, computation will be interrupted and a warning message will be issued in logger.

maximum_CL: float = None

name: str = ''

polar: Polar = <object object>

The Polar instance that will provide drag data.

propulsion: IPropulsion = <object object>

A IPropulsion instance that will be called at each time step.

property target: FlightPoint

The base class of the class hierarchy.

When called, it accepts no arguments and returns a new featureless instance that has no instance attributes and cannot be given any.

time_step: float = 60.0

Used time step for computation (actual time step can be lower at some particular times of the flight path).

polar_modifier: AbstractPolarModifier