profiles.py

class openconcept.mission.profiles.MissionWithReserve(**kwargs)

Bases: TrajectoryGroup

This analysis group is set up to compute all the major parameters of a fixed wing mission, including climb, cruise, and descent as well as Part 25 reserve fuel phases. The 5% of block fuel is not accounted for here.

To use this analysis, pass in an aircraft model following OpenConcept interface. Namely, the model should consume the following: - flight conditions (fltcond|q/rho/p/T/Utrue/Ueas/…) - aircraft design parameters (ac|*) - lift coefficient (fltcond|CL; either solved from steady flight or assumed during ground roll) - throttle - propulsor_failed (value 0 when failed, 1 when not failed)

and produce top-level outputs: - thrust - drag - weight

the following parameters need to either be defined as design variables or given as top-level analysis outputs from the airplane model: - ac|geom|S_ref - ac|aero|CL_max_flaps30 - ac|weights|MTOW

Inputs:

  • ac|* (various) – All relevant airplane design variables to pass to the airplane model

  • takeoff|h (float) – Takeoff obstacle clearance height (default 50 ft)

  • cruise|h0 (float) – Initial cruise altitude (default 28000 ft)

  • payload (float) – Mission payload (default 1000 lbm)

  • mission_range (float) – Design range (deault 1250 NM)

Options:

  • aircraft_model (class) – An aircraft model class with the standard OpenConcept interfaces promoted correctly

  • num_nodes (int) – Number of analysis points per phase. Higher is more accurate but more expensive

class openconcept.mission.profiles.BasicMission(**kwargs)

Bases: TrajectoryGroup

This analysis group is set up to compute all the major parameters of a fixed wing mission, including climb, cruise, and descent but no Part 25 reserves To use this analysis, pass in an aircraft model following OpenConcept interface. Namely, the model should consume the following: - flight conditions (fltcond|q/rho/p/T/Utrue/Ueas/…) - aircraft design parameters (ac|*) - lift coefficient (fltcond|CL; either solved from steady flight or assumed during ground roll) - throttle - propulsor_failed (value 0 when failed, 1 when not failed) and produce top-level outputs: - thrust - drag - weight the following parameters need to either be defined as design variables or given as top-level analysis outputs from the airplane model: - ac|geom|S_ref - ac|aero|CL_max_flaps30 - ac|weights|MTOW

Inputs:

  • ac|* (various) – All relevant airplane design variables to pass to the airplane model

  • takeoff|h (float) – Takeoff obstacle clearance height (default 50 ft)

  • cruise|h0 (float) – Initial cruise altitude (default 28000 ft)

  • payload (float) – Mission payload (default 1000 lbm)

  • mission_range (float) – Design range (deault 1250 NM)

Options:

  • aircraft_model (class) – An aircraft model class with the standard OpenConcept interfaces promoted correctly

  • num_nodes (int) – Number of analysis points per phase. Higher is more accurate but more expensive

class openconcept.mission.profiles.FullMissionAnalysis(**kwargs)

Bases: TrajectoryGroup

This analysis group is set up to compute all the major parameters of a fixed wing mission, including balanced-field takeoff, climb, cruise, and descent.

To use this analysis, pass in an aircraft model following OpenConcept interface. Namely, the model should consume the following: - flight conditions (fltcond|q/rho/p/T/Utrue/Ueas/…) - aircraft design parameters (ac|*) - lift coefficient (fltcond|CL; either solved from steady flight or assumed during ground roll) - throttle - propulsor_failed (value 0 when failed, 1 when not failed)

and produce top-level outputs: - thrust - drag - weight

the following parameters need to either be defined as design variables or given as top-level analysis outputs from the airplane model: - ac|geom|S_ref - ac|aero|CL_max_flaps30 - ac|weights|MTOW

Inputs:

  • ac|* (various) – All relevant airplane design variables to pass to the airplane model

  • takeoff|h (float) – Takeoff obstacle clearance height (default 50 ft)

  • cruise|h0 (float) – Initial cruise altitude (default 28000 ft)

  • payload (float) – Mission payload (default 1000 lbm)

  • mission_range (float) – Design range (deault 1250 NM)

Outputs:

takeoff|v1 (float) – Decision speed

Options:

  • aircraft_model (class) – An aircraft model class with the standard OpenConcept interfaces promoted correctly

  • num_nodes (int) – Number of analysis points per phase. Higher is more accurate but more expensive

  • transition_method (str) – Analysis method to compute distance, altitude, and time during transition Default “simplified” is the Raymer circular arc method and is more robust Option “ode” is a 2DOF ODE integration method which is arguably just as inaccurate and less robust