Flight segments

Flight segments are the Python-implemented, base building blocks for the mission definition.

They can be used as parts in phase definition.

A segment simulation starts at the flight parameters (altitude, speed, mass…) reached at the end of the previous simulated segment. The segment simulation ends when its target is reached (or if it cannot be reached).

Sections:

Segment types 

In the following, the description of each segment type links to the documentation of the Python implementation. All parameters of the Python constructor can be set in the mission file (except for propulsion and reference_area that are set within the mission module). Most of these parameters are scalars and can be set as described here. The segment target is a special parameter, detailed in further section. Other special parameters are detailed in last section.

Available segments are:

`start` segment 

New in version 1.4.0.

Parameters

isa_offset / name / target

start is a special segment to be used at the beginning of the mission definition to specify the starting point of the mission, preferably by defining variables so it can be controlled from FAST-OAD input file.

With no start specified, the mission is assumed to start at altitude 0.0, speed 0.0.

Note

The start segment allows to define the aircraft mass at the beginning of the mission. Yet it is possible to define aircraft mass at some intermediate phase (e.g. takeoff) using the mass_input segment.

Important

In any case, a variable for input mass has to be defined once and only once in the whole mission.

Example:

phases:
  start_phase:
    - segment: start
      target:
        true_airspeed: 0.0                # hard-coded value
        altitude:
          value: my:altitude:variable     # variable definition WITH associated default value
          unit: ft
          default: 100.0
        mass:
          value: my:mass:variable         # variable definition WITHOUT associated default value
          unit: kg                        # (will have to be set by another module or by FAST-OAD
                                        #  input file)

...

missions:
  main_mission:
    parts:
      - phase: start_phase
      - ...

See also

Python documentation: Start

`mass_input` segment 

New in version 1.4.0.

Parameters

isa_offset / name / target

The start segment allows to define aircraft mass at the beginning of the mission, but it is sometimes needed to define the aircraft mass at some point in the mission. The typical example would be the need to specify a takeoff weight that is expected to be achieved after the taxi-out phase.

The mass_input segment is designed to address this need. It will ensure this mass is achieved at the specify instant in the mission by setting the start mass input accordingly.

Example:

# For setting mass at the end of taxi-out:
phases:
  taxi-out:
    parts:
      - segment: taxi
        ...
      - segment: mass_input
        target:
          mass:
            value: my:MTOW:variable
            unit: kg

Warning

Currently, FAST-OAD assumes the fuel consumption before the mass_input segment is independent of aircraft mass, which is considered true in a phase such as taxi. Assuming otherwise would require to solve an additional inner loop. Since it does not correspond to any use case we currently know of, it has been decided to stick to the simple case.

See also

Python documentation: MassTargetSegment

`speed_change` segment 

Parameters

altitude_bounds / engine_setting / interrupt_if_getting_further_from_target / isa_offset / load_factor / mach_bounds / maximum_CL / name / polar / polar_modifier / propulsion / reference_area / target / thrust_rate / time_step

A speed_change segment simulates an acceleration or deceleration flight part, at constant altitude and thrust rate. It ends when the target speed (mach, true_airspeed or equivalent_airspeed) is reached.

Example:

segment: speed_change
polar: data:aerodynamics:aircraft:takeoff   # High-lift devices are ON
engine_setting: takeoff
thrust_rate: 1.0                            # Full throttle
target:
  # altitude: constant                      # Assumed by default
  equivalent_airspeed:                      # Acceleration up to EAS = 250 knots
    value: 250
    unit: kn

See also

Python documentation: SpeedChangeSegment

`altitude_change` segment 

Parameters

altitude_bounds / engine_setting / interrupt_if_getting_further_from_target / isa_offset / load_factor / mach_bounds / maximum_CL / maximum_flight_level / name / polar / polar_modifier / propulsion / reference_area / target / thrust_rate / time_step

An altitude_change segment simulates a climb or descent flight part at constant thrust rate. Typically, it ends when the target altitude is reached.

But also, a target speed, or CL, can be set, while keeping another speed constant (e.g. climbing up to Mach 0.8 while keeping equivalent_airspeed constant).

Examples:

segment: altitude_change
polar: data:aerodynamics:aircraft:cruise    # High speed aerodynamic polar
engine_setting: idle
thrust_rate: 0.15                           # Idle throttle
target:                                     # Descent down to 10000. feet at constant EAS
  altitude:
    value: 10000.
    unit: ft
  equivalent_airspeed: constant

segment: altitude_change
polar: data:aerodynamics:aircraft:cruise    # High speed aerodynamic polar
engine_setting: climb
thrust_rate: 0.93                           # Climb throttle
target:                                     # Climb up to Mach 0.78 at constant EAS
  equivalent_airspeed: constant
  mach: 0.78

segment: altitude_change
polar: data:aerodynamics:aircraft:cruise    # High speed aerodynamic polar
engine_setting: climb
thrust_rate: 0.93                           # Climb throttle
target:                                     # Climb at constant Mach up to the flight
  mach: constant                            #  level that provides maximum lift/drag
  altitude:                                 #  at current mass.
    value: optimal_flight_level
maximum_CL: 0.6                             # Limitation on lift coefficient.
                                            # The altitude will be limited to the closest
                                            # flight level within the CL limitation.

segment: altitude_change
polar: data:aerodynamics:aircraft:cruise    # High speed aerodynamic polar
engine_setting: climb
thrust_rate: 0.93                           # Climb throttle
target:
  mach: constant                            # Climb at constant Mach until target CL
  CL: 0.55                                  # is reached.

See also

Python documentation: AltitudeChangeSegment

`cruise` segment 

Parameters

altitude_bounds / climb_segment / engine_setting / interrupt_if_getting_further_from_target / isa_offset / load_factor / mach_bounds / maximum_CL / maximum_flight_level / name / polar / polar_modifier / propulsion / reference_area / target / time_step

A cruise segment simulates a flight part at constant speed and altitude, and regulated thrust rate (drag is compensated).

Optionally, target altitude can be set to optimal_flight_level. In such case, cruise will be preceded by a climb segment that will put the aircraft at the altitude that will minimize the fuel consumption for the whole segment (including the prepending climb). This option is available because the altitude_change segment segment can reach an altitude that will optimize the lift/drag ratio at current mass, but the obtained altitude will not guaranty an optimal fuel consumption for the whole cruise.

It ends when the target ground distance is covered (including the distance covered during prepending climb, if any).

Examples:

segment: cruise
polar: data:aerodynamics:aircraft:cruise    # High speed aerodynamic polar
engine_setting: cruise
target:
  # altitude: constant                      # Not needed, because assumed by default
  ground_distance:                          # Cruise for 2000 nautical miles
    value: 2000
    unit: NM

segment: cruise
polar: data:aerodynamics:aircraft:cruise    # High speed aerodynamic polar
engine_setting: cruise
target:
  altitude: optimal_flight_level            # Commands a prepending climb, id needed
  ground_distance:                          # Cruise for 2000 nautical miles
    value: 2000
    unit: NM

See also

Python documentation: ClimbAndCruiseSegment

`optimal_cruise` segment 

Parameters

altitude_bounds / engine_setting / interrupt_if_getting_further_from_target / isa_offset / load_factor / mach_bounds / maximum_CL / name / polar / polar_modifier / propulsion / reference_area / target / time_step

An optimal_cruise segment simulates a cruise climb, i.e. a cruise where the aircraft climbs gradually to keep being at altitude of maximum lift/drag ratio.

The optimal_cruise segment can be realised at a constant lift coefficient using the parameter maximum_CL.

It assumed the segment actually starts at altitude of maximum lift/drag ratio or the altitude given by maximum_CL, which can be achieved with an altitude_change segment segment with optimal_altitude as target altitude and maximum_CL as parameter.

The common way to optimize the fuel consumption for commercial aircraft is a step climb cruise. Such segment will be implemented in the future.

Example:

segment: optimal_cruise
polar: data:aerodynamics:aircraft:cruise    # High speed aerodynamic polar
engine_setting: cruise
maximum_CL: 0.6
target:
  ground_distance:                          # Cruise for 2000 nautical miles
    value: 2000
    unit: NM

See also

Python documentation: OptimalCruiseSegment

`holding` segment 

Parameters

altitude_bounds / engine_setting / interrupt_if_getting_further_from_target / isa_offset / load_factor / mach_bounds / maximum_CL / name / polar / polar_modifier / propulsion / reference_area / target / time_step

A holding segment simulates a flight part at constant speed and altitude, and regulated thrust rate (drag is compensated). It ends when the target time is covered.

Example:

segment: holding
polar: data:aerodynamics:aircraft:cruise    # High speed aerodynamic polar
target:
  # altitude: constant                      # Not needed, because assumed by default
  time:
    value: 20                               # 20 minutes holding
    unit: min

See also

Python documentation: HoldSegment

`taxi` segment 

Parameters

altitude_bounds / engine_setting / interrupt_if_getting_further_from_target / isa_offset / mach_bounds / maximum_CL / name / polar / polar_modifier / propulsion / reference_area / target / thrust_rate / time_step / true_airspeed

A taxi segment simulates the mission parts between gate and takeoff or landing, at constant thrust rate. It ends when the target time is covered.

Example:

segment: taxi
thrust_rate: 0.3
target:
  time:
    value: 300              # taxi for 300 seconds (5 minutes)

See also

Python documentation: TaxiSegment

`transition` segment 

Parameters

altitude_bounds / engine_setting / interrupt_if_getting_further_from_target / isa_offset / mach_bounds / maximum_CL / name / polar / polar_modifier / propulsion / reference_area / target / thrust_rate / time_step / true_airspeed

A transition segment is intended to “fill the gaps” when some flight part is not available for computation or is needed to be assessed without spending CPU time.

It can be used in various ways:

Target definition 

The most simple way is specifying a target with absolute and/or relative parameters. The second and last point of the flight segment will simply uses these values.

Example:

segment: transition # Rough simulation of a takeoff
target:
  delta_time: 60            # 60 seconds after start point
  delta_altitude:           # 35 ft above start point
    value: 35
    unit: ft
  delta_mass: -80.0         # 80kg lost from start point (implicitly 80kg consumed fuel)
  true_airspeed: 85         # 85m/s at end of segment.

Usage of a mass ratio 

As seen above, it is possible to force a mass evolution of a certain amount by specifying delta_mass.

It is also possible to specify a mass ratio. This can be done outside the target, as a segment parameter.

Example:

segment: transition # Rough climb simulation
mass_ratio: 0.97            # Aircraft end mass will be 97% of total start mass
target:
  altitude: 10000.
  mach: 0.78
  delta_ground_distance:    # 250 km after start point.
    value: 250
    unit: km

Reserve mass ratio 

Another segment parameter is reserve_mass_ratio. When using this parameter, another flight point is added to computed segment, where the aircraft mass is decreased by a fraction of the mass that remains at the end of the segment (including this reserve consumption).

Typically, it will be used as last segment to compute a reserve based on the Zero-Fuel-Weight mass.

Example:

segment: transition # Rough reserve simulation
reserve_mass_ratio: 0.06
target:
  altitude: 0.
  mach: 0.

Mass change without fuel consumption 

New in version 1.8.2.

Using delta_mass allows to simulate a fuel consumption equivalent to the mass loss.

For cases where mass variation should be simulated without fuel consumption, it is possible to set to False the parameter fuel_is_consumed.

Example:

segment: transition
target:
  delta_mass: -100.
  fuel_is_consumed: False

See also

Python documentation: DummyTransitionSegment

`ground_speed_change` segment 

New in version 1.5.0.

This segment is used specifically during accelerating or decelerating parts while still on the ground. The friction force with the ground is accounted in the equation of movements. Whilst on the ground, the key wheels_friction is used to define the friction coefficient. The segment ends when the target velocity is reached.

Example:

segment: ground_speed_change
wheels_friction: 0.03
target:
  equivalent_airspeed:
    value: data:mission:operational:takeoff:Vr

See also

Python documentation: GroundSpeedChangeSegment

`rotation` segment 

New in version 1.5.0.

This segment is used to represent a rotation while still on the ground. This segment is specifically used for takeoff. The specific keys are (in addition to wheel friction coefficient):

rotation_rate in (rad/s) is the rotation speed used to realise the manoeuvre (by default 3deg/s, compliant with CS-25 )

alpha_limit (in rad) is the maximum angle of attack possible before tail strike (by default 13.5deg).

The segment ends when lift equals weight. Therefore, no target needs to be set.

Example:

segment: rotation
wheels_friction: 0.03
rotation_rate:
  value: 0.0523
alpha_limit:
  value: 0.3489

See also

Python documentation: RotationSegment

`end_of_takeoff` segment 

New in version 1.5.0.

This segment is used at the end of the takeoff phase, between lift off and before reaching the safety altitude. The target sets the safety altitude. Because this phase is quite dynamic, it is a good practice to lower the time step at least to 0.05s for a good accuracy on takeoff distance.

Example:

segment: end_of_takeoff
time_step: 0.05
target:
  delta_altitude:
    value: 35
    unit: ft

See also

Python documentation: EndOfTakeoffSegment

`takeoff` segment 

New in version 1.5.0.

This segment is the sequence of ground_speed_change segment, rotation segment and end_of_takeoff segment.

The parameters for this segment are the same as for its 3 components, except that:

time_step is used only for ground_speed_change segment and rotation segment.

time step for end_of_takeoff segment is driven by the additional parameter end_time_step

target speed at end of ground_speed_change segment is driven by the additional parameter rotation_equivalent_airspeed

the target of takeoff segment is the target of end_of_takeoff segment, meaning it sets the safety altitude.

Example:

segment: takeoff
wheels_friction: 0.03
rotation_equivalent_airspeed:
  value: data:mission:operational:takeoff:Vr
rotation_rate:
  value: 0.0523
  units: rad/s
rotation_alpha_limit:
  value: 0.3489
  units: rad
end_time_step: 0.05
target:
  delta_altitude:
    value: 35
    unit: ft

See also

Python documentation: TakeOffSequence

Special segment parameters 

Most of segment parameters must be set with a unique value, which can be done in several ways, as described here.

There are some special parameters that are detailed below.

`target` parameter 

Applies to

altitude_change / breguet / cruise / end_of_takeoff / ground_speed_change / holding / mass_input / optimal_cruise / rotation / speed_change / start / takeoff / taxi / transition

The target of a flight segment is a set of parameters that drives the end of the segment simulation.

Possible target parameters are the available fields of FlightPoint. The actually useful parameters depend on the segment.

Each parameter can be set the usual way, generally with a numeric value or a variable name, but it can also be a string. The most common string value is constant that tells the parameter value should be kept constant and equal to the start value. In any case, please refer to the documentation of the flight segment.

Absolute and relative values

Amost all target parameters are considered as absolute values, i.e. the target is considered reached if the named parameter gets equal to the provided value.

They can also be specified as relative values, meaning that the target is considered reached if the named parameter gets equal to the provided value added to start value. To do so, the parameter name will be preceded by delta_.

Examples:

target:
  altitude: # Target will be reached at 35000 ft.
    value: 35000
    unit: ft

target:
  delta_altitude: # Target will be 5000 ft above the start altitude of the segment.
    value: 5000
    unit: ft

Important

There are 2 exceptions : ground_distance and time are always considered as relative values. Therefore, delta_ground_distance and delta_time will have the same effect.

`engine_setting` parameter 

Applies to

altitude_change / breguet / cruise / end_of_takeoff / ground_speed_change / holding / optimal_cruise / rotation / speed_change / takeoff / taxi

Expected value for engine_setting are takeoff, climb , cruise or idle

This setting can be used by a model like the “rubber engine” propulsion model (see class RubberEngine). It roughly links the “turbine inlet temperature” (a.k.a. T4) to the flight conditions.

If another propulsion model is used, this parameter may become irrelevant, and then can be omitted.

`polar` parameter(s)

Applies to

altitude_change / breguet / cruise / end_of_takeoff / ground_speed_change / holding / optimal_cruise / rotation / speed_change / takeoff / taxi

The aerodynamic polar defines the relation between lift and drag coefficients (respectively CL and CD). This parameter is composed of two vectors of same size, one for CL, and one for CD.

The polar parameter has 2 sub-keys that are CL and CD.

A basic example would be:

segment: cruise
polar:
  CL: [0.0, 0.5, 1.0]
  CD: [0.01, 0.03, 0.12]

But generally, polar values will be obtained through variable names, because they will be computed during the process, or provided in the input file. This should give:

segment: cruise
polar:
  CL: data:aerodynamics:aircraft:cruise:CL
  CD: data:aerodynamics:aircraft:cruise:CD

Additionally, a convenience feature is proposes, which assumes CL and CD are provided by variables with same names, except one ends with :CL and the other one by :CD. In such case, providing only the common prefix is enough.

Therefore, the next example is equivalent to the previous one:

segment: cruise
polar: data:aerodynamics:aircraft:cruise